NUREG/CR-3037

P N L-4532

User's Manual for FIRIN

A Computer Code to

Airborne Releases in

Estimate Accidental Fire and Radioactive

Nuclear Fuel Cycle Facilities

Prepared by M.K. Chan, M.Y. Ballinger, P.C. Owczarski

Pacific Northwest Laboratory Operated by Battelle Memorial Institute

Prepared for

U.S. Nuclear Regulatory Cornmission
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NUREG/CR-3037

PNLA4532

RZ

User's Manual for FIRIN

A Computer Code to Estimate Accidental Fire and

Airborne Releases in Nuclear Fuel Cycle Facilities

Radioactive

Manuscript Completed: January 1989

Date Published: February 1989

Prepared by

M.K. Chan, M.Y. Ballinger, P.C. Owczarski

Pacific Northwest Laboratory Richland, WA 99352

Prepared for

Division of Fuel Cycle and Material Safety Office of Nuclear Materials Safety and Safeguards U.S. Nuclear Regulatory Commission

Washington, DC 206555

NRC FIN B2481
For sage by the Superintendent of Documents. U.S. Government Printing Office

Washington, D.C. 2040
SUMMARY

This manual describes the technical bases and use of the computer code

FIRIN. This code was developed to estimate the source term release of smoke

and radioactive particles from potential fires in nuclear fuel cycle

facilities. FIRIN is a product of a broader study, Fuel Cycle Accident

Analysis, which Pacific Northwest Laboratory conducted for the U.S. Nuclear

Regulatory Commission.

The technical bases of FIRIN consist of a nonradioactive fire source term

model, compartment effects modeling, and radioactive source term models. These

three elements interact with each other in the code affecting the course of the

fire.

This report also serves as a complete FIRIN user's manual. Included are

the FIRIN code description with methods/algorithms of calculation and subroutines, code operating instructions with input requirements, and output

descri ptions.

iii

CONTENTS

2.0 MODEL DESCRIPTION................................. 2.1

2.1 ASSUMPTIONS AND FEATURES ....... ***,***................ ... 2.1

2.2 FIRE SOURCE TERM MODELS. .............................. 2.2

2.2.2 Heats RLease Rate ....................... .................. 2.4

2.2.3 Combustion Product Generation Rate ...................... 2.6

2.2.4 Burning Modes... ........... . . ........ 2.7

2.2.5 Fire Particulate Material Characteristics.... o........... 2.8

2.3 COMPARTMENT EFFECTS .......................... 2.10

2.3.1 Heat Transfer in the Fire Compartment ................... 2.11

2.3.2 Mass Balance in the Fire Compartment .................... 2.24

2.3.3 Heat Balance in the Fire Compartment...e......o....e..... 2.26

2.3o4 Thermal Decomposition of Concrete.. .... ooo...o..o.oo .... 2.28

2.3o5 Fluid Flows.. .... o..... ....... o.....ooo....o......o.o.... 2.30

2.3o6 Particle Depletion.... ..... ooo............ ...... o.o..ooo. 2.36

2.4 RADIOACTIVE SOURCE TERM MODELS.o................... o.....e~**99 2.42

2.4.1 Burning of Contaminated Combustibles.. ..................0 2.43

2.4o2 Heating of Noncombustible Contaminated Surfaces.....'.... 2.49

2.4o3 Heating of Unpressurized Radioactive Liquids ..... .. o ... 2.51

2.4o4 Pressurized Releases..... ..... o.... oo........ o........ 0. 2.54

2.4i5 Burning Radioactive Pyrophoric Metals............ ..... oo 2.55

V
CONTENTS (contd)

3.0 THE FIRIN COMPUTER PROGRAM ............................. 3i.1

3.1 PROGRAMSTRUCTURE ***** ***********.*.........3.1

3.2. DATA STRUCTURE ....................... ..... 3.4

3.2.1 Fuel Material Data ..................................... 3.4

3.2.2 Construction Material Data ............................. 3.7

3.2.3 Other Data .............................................. 3.9

3.3 NUMERICAL ALGORITHMS .... ... ................. .. 3.10

3.4 SUBROUTI NE FUNCTIONS .......................... 3.11

3.*5 INPUT AND OUTPUT .......................... ... 3.11

3 .5 .1 I np ut F ormat .. . .. . .. .. 0 .. a 0 0 * 0 .. 0 0 0. .. 0 0 0 0 .. 0 e. 0 0 3 .12

3.5.2 Output Information .... ................... 3.25

3.6 PROGRAM LIMITATIONS ......... .~.......... 3.28

4.0 SAMPLE PROBLEMS .......................... .... 4.1

4 .1 BASIC SCENARIO ................................ 4a*

4.3 PROBLEM TWO - ONE BURN ORDER .................. 9... .e. . 9e... 4.5

4.4 PROBLEM THREE -AUTOIGNITION ENERGY OPTION .................... 4.6

4.5 PROBLEM FOUR -EQUIPMENT AT RISK .............................. 4.6

4.6 PROBLEM FIVE -ALTERNATE FLOW PATH ..................... 4.12

APPENDIX A - EXPERIMENTAL DATA FOR BURNING CONTAMINATED

COMBUSTI BLE SOLID 1.... . .*................. A.*1

APPENDIX B - FUEL AND CONSTRUCTION MATERIAL PROPERTIES

vi
CONTENTS (contd)

APPENDIX C - FIRIN CODE.LISTING .............................. C.1-

APPENDIX D - FIRIN PARAMETER DEFINITIONS ........... .......... Del

APPENDIX E - OUTPUT FILES FROM PROBLEM ONE................... E.1l

vi i.
FIGURES.

3.1 FIRIN--Overview Flow Chart ......... ..... 9..... 9...........~.. ..... 3.2

3.2 BLOCK 1--Fire Source Terms Computation ............................ 3.3

3.3, BLOCK 2--Heat and Mass Transfer Considerations .................... 3.5

3.4 BLOCK 3--Radioactive Source Terms Computation ........... 3.6

4.1 Accumulated Mass of Radioactive Material to Environs

from P~roblems.,One and Five ..................... 4.18

TAB LES

2.1 Combustion Efficiency., Xa!P99jP****o............. *** ** , .. *... ....... *2.6

2.2 Particle, Size and Particle-Size Distribution of

Fuel Materials...................................................... 2.9

2.3 Smoke Particle-Size C~aatrsis................ 2.10

2.4 Experimental Parameters ................. ... ....... ...... .... .... ... 2.44

2.5 Radioactive Source Term Equations for Burning

Contaminated Combustible Sol ids ................... ....... 2.45

2.6 Radioactive.Particle Size Distribution from Burning

Contaminated Combustible Liquids .................................. 2.49

2.7 Characteristics and Range of Releases from

Radioactive Powders Studies . . . . ................................. 2.50

2.8 Radioactive Releases from Heating Partially Oxidized

2.9 Releases from Heating of Unpressurized Radioactive

2.10 Fraction of Radioactive Material Released from Boiling

2.11 Releases from Heating Residue Following Boiling of

2.12 Releases from Burning Radioactive Pyrophoric Metals ............... 2.56

viii
TABLES (contd)

3.1 Fuel Material and Ventilation Conditions for the

Fire Compartments ................................. 3.7

3.2 Data Base for Physical/Chemical and Pyrolysis/Combustion

Properties of Fuel Material s ....................... . 3.8'

3.3 Noncombustible Material Options for the Fire Compartment ..... ~ 3.9

3.4ý Data Base for Physical: Properties of Noncombustible

3.5 Subroutines for Estimating Radioactive Releases ................. 3.11

3.6 Unit Files for Input and Output Data ................... .. 3.12

3.7 Input Data ......... ............ . .. 3..... 3*13

3.8 Parameters in Output Files ..... *.............. . 3.26

4.1 Combustibles for Sample Problems ............................ 4.2

4.2a Input for Problem One ............................. 4.3

4 .2b PRINT.DAT from Problem One . ............................... .... 4.4

4.3a Input for Problem Two ............................ 4.5

4 .3b PRINTODAT from Problem Two .. ................ ... 4.7

4.4a Input for Problem Three ........................................... 4.8

40.4b PRINT.DAT from Problem Three ....... ..... ........... 4.9

4 .5a Input for Problem Four .. ... ......... 4.12

4.*5b PR INT .DAT from P robl em Four ..... o.............o. .......... 9****** 4. 14

4.6a Input for Problem Five ............................ 4.16

4 .6b PR INT. DAT from P robl em Five ..... ................................. 0 4o*17

ix
I-
1.0 INTRODUCTION

Source terms generated by potential accidental fires in nuclear fuel cycle

facilities can be estimated using the computer code FIRIN developed by Pacific

Northwest Laboratory (PNL). The primary thrust of the work is to estimate the

mass generation rate and size distribution of radioactive particles that become

airborne in a fire accident. These releases can be calculated using FIRIN.

Other information calculated by.FIRIN includes (but is not limited to) fire

source mass loss rates, energy generation rates, and transient conditions such

as temperature and pressure in the fire compartment. Los Alamos National

Laboratory has developed the computer code FIRAC to analyze fire-induced flow

and thermal and material transport in the building ventilation system.

FIRIN is designed to provide mass and energy input to FIRAC. Using bot h

codes, a user can analyze radioactive source terms up to the facility atmosphere interface. Used alone, FIRIN predicts this release within the fire

compartment.

Radioactive release factors incorporated in the code are primarily those

developed in experimental work at PNL. Combustion product data were developed

from a literature review (Chan and Mishima 1982) for combustibles that are

commonly found in nuclear fuel cycle faciliti~es and from experimental work

performed at Factory Mutual Research (Steciak, Tewarson, and Newmian 1983).

This manual is designed to instruct the FIRIN user, who is assumed to be a

knowledgeable engineer/scientist required to make a safety assessment of a

specific facility. The user is assumed to be familiar with basic programming,

heat transfers, and the facility for which the fire accident is simulated.

Chapter 2.0 is a description of the technical basis of the models in the

code. Background information, such as program and data structure, numerical

algorithms, subroutine functions, input requirements, and output interpretation, are included in Chapter 3.0. Operational instructions are given using

illustrative sample problems in Chapter 4.0.

1.1

2.0 MODEL DESCRIPTION

This chapter describes the models used in the FIRIN computer code. The

major assumptions and features used in developing the models are discussed.

This is followed by sections describing fire source term models, compartment

effects, and rad ioactive source tern models.

2.1 ASSUMPTIONS AND FEATURES

Certain assumptions were made about the fire during FIRIN development:

" Fire growth is approximated by using the concepts of burning order and

ignition energy in FIRIN., Applying these concepts allows the user to

examine the effects of fire severity ranging from a small fire involving

only one combustible to a large fire that involves all combustibles found

in the compartment.

" The burning order concept requires that the user estimates the consumption

,order of combustible materials in the fire scenario of interest. This

concept permits the user to set bounds for the severity of compartment

fires.

" The ignition energy concept (an option) features autoignition of

combustibles at risk, if the heat flux levels generated by the initial

burning combustibles are sufficient. Ignition energy data for the

combustibles (Tewarson 1982) are stored in FIRIN., The-user selects the

initial ignition point and other combustibles at risk other than the

initial buring material inside the fire compartment.

" Each burning element is assumed to burn at a constant rate when exposed to

a constant oxygen and heat flux environment. These rates are found in the

Factory Mutual Data Base (Tewarson 1982) and are experimentally

determined.

" Flaming combustion is the principal burning mode in FIRIN. Limited

smoldering combustion data are available and are used in other burn modes.

Ample oxygen is available during the initial burning; as less oxygen is

available during later stages of the fire, the burning mode is reduced in

an approximate manner.

" Burning rates (or mass loss rates) are a function of the oxygen provided

by room ventilation flow, type of combustible, and exposed surface area of

combustible.

" FIRIN provides output suitable for input to FIRAC (e.g., mass and size

distribution of smoke and radioactive particles attacking the filters as a

function of time).

2.1
*Wal~l and., equipment heat absorption..models are incorporated into FIRIN.

This feature provides a more realistic estimate of *the net energy input

required for FIRAC. Additionally, these models-cAn be'used to predict

equipment heating and overpressurizing, and subsequent rupturing.

*The potential for water vapor formation is high because concrete loses

water at 900 to 9000C. When heated to 6000C, the water in a 1/4-in.

concrete wall surrounding a 10-ft x 10-ft x 10-ft room (less ceiling)

produces~about sev~en room volumes of water-vapor. -This phenomena, not

found in other fire models, is i ncluded in FIRIN. Reactor containment

modelers have .produced the information needed to c'ouple this water and

carbon dioxide source to thew all heat transfer model. -This water,'vapor

could either raise the room pressure or substantial~ly increase ventilation

flowl'. It could also be a'substantial source' 'of condensate in cooler

regions of.1the ventilation system.

" Flame *radiation is estimated in laboratory-ýscale experiments for each type

of combustible material by increasing the oxygen concentration in air

(Tewarson 1982). When burning a combustible mixture, the component

.material with the greatest flame radiation is used for calculating burn

rates of individual components inFIRIN.

" the following particle depletion mechanisms are included: gravity

settling, Brownian diffusion, diffusiophoresis,*and thermaphoresis.

2.2 FIRE SOURCE TERM MODELS

Source terms required to characterize a fire include mass loss rates, heat

release rates,'and combustion product generation rates. Using the steady-state

heat balance on the surface of a burning element, Tewarson-et al. (1976, '1980)

derived rate equations for these fire source, terms.ý The rate equations are

developed As a function of material properties and fire conditions. The

following sections discuss these source term rateý,equations. The model

equations used in FIRIN are identified, and required input parameters are given

for computing fire source terms. In addition, a simple model is developed to

approximate changes in. pyrolysis/combustion properties caused by ventilation

conditions. FIRIN calculates the fire source terms to, correspond to the

available oxygen.

2,,2.1 Mass Loss Rate (M")

-,The-mass loss rate of-various combustible materialst depends on the'

available net-heat flux received by the material ~n~a fire and the heat

2.2
required to generate a unit mass of combustible vapors. Thi's loss-rate is

calculated as follows'(Tewarso~n 1980a)':

M Sf

=q11/L (2-1)

where M"is the mass loss rate of 'the material-, q" is the' net heat flux

received by the fuel niaterial'per unit fulel-surf'ace area, and L is the heat

required to generate a unit mass of fuel vapors.ý In the rotation used,; a dot

above'th'e paramete'r indi cates per unit of time,'and q .uota ;t ion mark's .on the

upper right side of the parameter indicated per unit of area. * Thus4M has

units of grams/(s in2 a~nd is a rate of mass flux. Similarly q",is a rate of.

energy flux.

Mass loss rate for the two phenomena,,pyrolysis and combustion, is used in

FIRIN and defined as follows (Tewarson 1980b):'

9 mass loss rate in pyrolysis (14")

p

mo (qII q1 q)/L (2-2)

whr q stenet heat flux, q" is the external heat flux, and.4r is

the surface radiation heat loss

' mass loss rate. in combustion (j

b

Mb (q"' + qf` - )/L -(2-3)

where (q" + qfs qrg is the net heat flux, and the total flame heat flux

q If is included in the net heat transfer''because* of flaming combustion. The

total flame heat flux is the summation 'of flame' convective heat flux qfc and

radiative heat fluxq.

Physical/chemical and pyrolysis/combustion properties (ri-ght-hand side of'

both equations) 'I 'h c s c l u are stored in the FIRIN data base, except q, ic s alu

lated in the compartment effect models. The data base contains properties of

fuels of interest (i.e., combustible materials commonly found in nuclear fuel

2.3
cycle facilities). The fuel pyrolysis/combus -tion propert~i.es were developed.

from combustion experiments conducted by Factory Mutual Research Corporation

(Tewarson 1980b; Steciak, Tewarson, and. Newman 1983).' Appendix B tabulates the

valves used in FIRIN..

Mass loss rate in a fire is a function of fuel type and surface area;

therefore, this information is required input to-FIRIN. Fuel ma ss is the input

required to estimate the length of time a particular fuel- burns. Oxygen concentration also influences mass loss rate a~nd is calculated within FIRIN for

each time step.

2.2.4 Heat Release Rate (~

Heat release rates must be considered to-describe the rate of fire growth

and the size of the fire. Heat release rates in fires can be expressed as

follows (Tewarson'1980a):

Q" H1 M1 (2-4)

where Q~is the heat release rate, Hi is the heat of combustion, and MSis the

mass loss rate in combustion.

When all the fuel vapors burn completely, Hi of Equation (2-4) is defined

as heat of complete combustion of the fuel Ht. In an actual fire, where both

material pyrolysis and combustion-often coexist and oxygen is not always, available, fuel vapors generated from pyrolysis do not often burn completely.

Therefore, H is defined as the actual heat of combustion of fuel Ha and Q1-is

the actual heat release rate; thus, Equation (2-4) can be rewritten as

= H M"(2-5) .a a b

Furthermore, the ratio of actual-to-complete-heat: of combustion (Hat)i

defined as combustion efficiency of the fuel Xae Therefore,

;I= X H MIS (2-6) -a a t _b

2.4
or, from Equations (2-3) and (2--6)'9 the heat release rate is.-written as

a Xa (Ht/L)(cC' +f q 5 qr)(27

Equation (2-7) is the final expression, that is used in FIRIN to calculate

energy. release rates. The combustion efficiency Xa and the, heat of complete

combustion Ht for the-combustibles of interest are" also stored in the data base

in FIRrN.

Heat release rates (Tewarson 1980b) involve all of-the following'

parameters: a) combustion efficiency of combustible materials, b) ratio of

compl~ete combustion heat to-the h~eat required to generate a unit mass of,

vapors, and c) net heat flux absorbed by the surface. Tewarson studied the

dependence of heat release rates on thermal and over- or underve~ntilated fire

environments for various materials. He found that the combustion efficiency

for an overventilated fire environment becomes approximately constant for each

generic type of material tested. According to Tewarson, combustion efficiency

can decrease if

" the ratio of carbon relative to hydrogen, Oxygen., or other fuell

constituents in the vapors is decreased

" the gas-phase react 'ions are quenched or retarded by lack of available

oxygen, chemical retardants in the materials, or a decrease in temperature

* soot-forming reactions are preferred in the gas phase [i.e., polystyrene

(PS)].

Table 2.*1 lists combustion efficiencies for s~ome materials' (Chan and Mishima

1982).

2.5
TABLE 2. 1., .Combusti on, Eff ici ency, Xa

Nonaro matic Polymers(a) High (0.81 < Xa < 0.97)

Polymethyl methacrylate

Polypropylene

Aromatic Compounds(b) Medium (0.51 < Xa< 0.7)

Red Oak

Polystyrene

Chlorinated Compound Low (Xa -0.35)

Polyvinyl chloride

(a) Noncharring materials.

(b), Charring materials.,

Since the heat release rate. is a function of mass loss rate, both fuel

type and surface area are required input.

2.2.3 Combustion-Product Generation Rate(j

According to Tewar'son (1980b), the combustion product (i.e.,jcarbon

dioxide, carbon monoxide, water'. smoke, and low .volatile hydrocarbon)

generation rate is equal to the fractional yield of the product times the mass

loss rate. This is expressed as

Where

G3 = mass generation -rate of product j per unit surface area of the

combustible

j = subscript denoting conbustion product

Yj = the yield of product j, which can be expressed as a multiple

of the yield of product j expected from stoichiometry ki and

the product generation efficiency fj [Equation (2-9)]

= the mass -loss rate from pyrolysis or combustion

Y. f ik.

(2-8)

(2-9)

2.6
Thus, the product generation rate of certain species for pyrolysis can be

written as

G ftm =f(k./L)(q" (2-10)

Using Equation (2-3), the product generation rate for c ombustion is

Gi fj(kj/L)(q" + q" d~ (2-11)

like a~, depends on both material properties and fire conditions.

Equations (2-10) and (2-11) are the final expressions used in FIRIN for the

calculati~on of product-generation rates. The values of Yj' or (fjkj) for the

combustibles of interest are stored in the data base in FIRIN. Similar to

other combustion properties, only overventilated data are currently available.

Underventilated data are estimated. Since the product generation rate is also

a function of mass loss rate, the input requirement is the same as for the

other two rates discussed in the previous subsections.

2.2.4 Burning Modes

Flaming and smoldering combustion are the two burning modes considered in

FIRIN. In an overventilated fire with an oxygen level greater than 15%, fuels

are assumed to burn in a flaming mode. In an underventilated fire with an

oxygen level less than 11%, fuels are assumed to burn in a smoldering mode. -In

a semiventilated fire with an oxygen level between 11% and 15%, fuels are

assumed to burn in a mixed flaming and smoldering mode.

The pyrolysis/combustion properties are assumed to have a linear

relationship with oxygen levels. The model used is

sv ~ov 5 ~ov 'uv (-2

where Psv = pyrolysis/combustion properties, semiventilated fire

Pov = pyrolysis/combustion properties, overventilated fire

2.7
S =linarscal .ing factor, S = 15% - 02 linear15% - 11%

Pv= pyrolysis/combusti-on properties, underventilated

02 = oxygen level in fire, and 15% _<02 <11%.

Some of the P, values in the data base are estimated. Available Po

values were multipli~ed by an assumed fraction 0..2 to 0.8 (depending on the

pyrolysis and'c~ombustion'properties) to estimate needed values. The assumed

fractions were estimated using limited fuel data from both over- and underventilated experimental fire tests (Tewarson.1980a,b). The oxygen transient is

calculated from the fire compartment mass balance.

2.2.5 Fire Particulate Material Characteristics

Fire (smoke) particle characteristics of interest are the particle size,

size distribution, and number density as a function of time in a compartment

fire. In fire research, a few studies have been successful in predicting

particle size and number density by applying the Mie Scattering Theory (Chan

and Mishima 1982). Model equations for predicting these characteristics are

available in a diffusion flame study by Pagni and Bard (1978).(a) Currently,

too few data are available for FIRIN to fully use the existing models. Smoke

characteristic studies of this type are under way at the Factory Mutual

Research Corporation (Newman 1982).

Users can (at this level of approximation) also refer to Table 2.2 for

various steady-state smoke particle sizes (Chan and Mishima 1982). Ranges of

particulate mass median diameter (MMD) and standard deviation (a. g) for

cellulose and various polymers are tabulated in this table for both normal and

high ventilation air temperatures. These data were obtained from B. T. Zin n

and his colleagues.,at Georgia Institute of Technology (Bankston et al. 1978;

Zinn et al.,1978, 1980). Notice that in flaming combustion in both normal and

highly ventilated conditions, MMD and particle-size distribution data are

unavailable for the polymers [except polymethyl methacrylate (PMMA)J. Large,

sooty particles produced during flaming combustion tend to rapidly clog up the

(a) Pagn i, P. J., and J. Bard. 1978. "Particulate Volume Fractions in

Diffusion Fl~ames," p. 1011. Paper presented at the Seventeenth Symposium

(International) on Combustion, August,'20-25, 1978, Leeds, England.

2.8
ZTABLE 2.2. Particle Size and Particle-Size- Distribution of Fue-l Materials

Fuel,

Material

Douglas fir

Mass Media

Di ameter

0.5-0.9

0.4

*1.0

Polyniethyl- 0.7

methacrylate

Polystyrene 2.6

Polyethylene 1.5

Polypropylene 2.05

Polyvinyl 1.4

chlorideHydraulic -

fluid

n Standard

*Deviation

1.8-2.0

2.4

* 2.0

1.9

1.9

1.*75

1.8

Volume Surface

Mean Particle

Dia. at. Maxcimum

Optical Density

jj* rs (Urn),

0.75-0.8.

0.5-0..45

0.9

* 0.75-0.55

* 0.5-0.55

0.6

1.2

1-ý2-1.3

1.4

1.3>

1. 3-1.25

*1.1

1.3

1.3-1.35

1.,6

1.2

1.0

1.2

1.1-1M

1.23"

1.33-1.31

F or NF(

NF

F

"F

NF

F

NF

F

F

N F

FF

NF

F

F

NF

F

F

NF

F

F'

NFF,

a). Hw/cmiI)

3.2-6.2

2.*5-5,

6.2

5.

5

5

5'

5

5

5

5

5

5

5

5

5

5

5'

-5

5

5

Air Flow

Rate

(i/mi n)

142-428

28 3-425

425

425-283

425

425

425

425

425

.425

425

425

425

425

425

425

425

425

425

425

425

Envi ronmental Conditions

Normal temp. (25*C) and composition

Normal temp. (25*C)

Normal temp.; composition of, 80% N2, 5 to 10% 029 10% C02 , 5% CO

Air temp. of 250 to -2000C, normal composition

Air temp. of 25 0 to 2000C, normal composition

Normal temp.- (250C) and composition

Normal temp. (25*C)' and composition

Air t -emp. of .25q to 200*C; normal composition

Normal temp. (25 *C)

Normal temp. (25,*C)-

Air temp. of 25* to 2000C; normal composition

Normal temp.,(25*C)'

Normal temp. (25*C)

Air temp. of_.250: to 2000C; normal composition

Normal temp. (250C) and composition

Normal temp. (25*C) and composition

Air temp. of 250 to 200*C; normal composition

Normal temp. (25 C)-and composition

Normal'temp4 (25 C) and composition

Air temp. of-25 .to.200*C; normal composition

Normal temp. (25 *C) and composition

Air temp. of-25 to 200*C; normal composition

(a) F -.Flaming combustion

.NF =. Nonf laming combustion
cascade impactor plates used in taking samples." For PMMA the quantities of

smoke particles coll~ected were too small for reliable size-distribution

measurements.,. Mean particle diameter is measured in these conditions by in'

situ optical techniques.

Smoke particle-size distributions were also measured in comb ustion

experiments at PNL,. Paper, PMMA, and polychloroprene (PC) were burned and the

aerodynamic equivalent diameter (AED) of smoke particles were measured with'a

cascade impactor..ý Table 2-.3 lists the MMD and standard-deviation '~)Of these

smoke particles.

TABLE 2.3 Smoke Particle-Size Characteristics

Mass Median Standard

Material Diameter (um) Deito

Polymethyl methacrylate 0.80 to.1.68 2.6. to. 3.2

Polychloroprene 0.40 2.7

Paper . 0.47 3.1

At. the point measured (several feet from the flame in both the PNL and

Georgia Tech experiments), smoke particle size does not seem to be a function

of material burned. An ave rage MMD of approximately one micron and an average

Ugof 2 is used in FIRIN to estimate smoke particle sizes from all burning

materials.

2.3 COMPARTMENT EFFECTS

The severity of a fire insidetan enclosure can be affected by the constraint of the compartment barriers. *For nuclear fuel cycle facility fires,

the quantity of radioactive releases from mechanisms such as burning and heating of radioactive-contaminated material1s, and heating of- vessels and equipment

containing.-radioactive materials depends on the fire severity inside the compartmen t and ventilation'conditions. The compartment barriers not only contain

most of the mass and gases generated from the fire, they also trap a portion of

the thermal energy released during the combustion processes. Because of the

2.*10
inlet ventilation located near the c~eiling,,(commonly-found .in nucl~ear facilities), air contaminated with fire gases and smoke accumulating in the hot ceiling layer is pushed rapidly to the fire,-site,,-causing the early starvation of

oxygen supply to the fire. On the other hand, the trapped energy is available

to enhance the pyrolysis rate of the combustible materials at risk.

If the compartment barriers are 'made of concrete, the decomposition of

water vapor and carbon dioxide from the heated concrete could significantly

contribute to the overall mass. releases from the fire. The possibility of

these additional releases will be significant in a long-lasting fire inside a

small compartment. The overall airborne mass can challenge the filter and

ventilation s ystem of the building, which can lead to release of radioactive

particles to the. atmosphere.

To provide realistic estimates of'-both the radioactive and fire source

terms inside the fire compartment, thie above characteristics of barrier effects

and their interaction with the fire strength are modeled. The models developed

and selected are for heat transfer, heat and mass balances, concrete dec~omposition, fluid flow, and particle depletion inside the compartment. The following

sections describe these models and their relationships in FIRIN. The required

input parameters for the model'calculations* are also identified.

2.3.1 Heat Transfer in the Fire Compa rtment

Three major types of heat transfer phenomena considered for fire inside a

compartment are as follows:

1. direct radiative heat transfer

2. 'convective heat transfer,

3. conductive heat transfer.

Mathematical models for a1ll of these phenomena are given below,- including heat

transfer to and within. equipment(a) at risk inside the fire compartment. Some

equipment might contain, radioacti~ve, material1s in-various physical f orms that

(a) Equipment refers to .'machine'ry,,gloveboxes, vessels'. and other apparatus in

the fire compartment that could affect the source term by adding to source

term release and/or absorbing heat from the fire.

2.11
can be released into the fire environment as a consequence of heating processes. In modeling heat transfer within the compartment, we assume the fire is

anchored at or above the floor level and is located at the center of the

enclosure in order to acquire geometric simplicity.

2.3.1.1 Direct Radiative Heat Transfer

At the-initial stage of a fire inside a given compartment, the dominant

radiative heat transfer is from the flame itself. This flame radiative heat

loss is absorbed by the hot layer, walls, and equipment. Radiative heat

transfer is also occurring between the smoke layer and the ceiling in contact

with it.

As the hot layer descends, it becomes a major radiation heat source for

the combustible materials, compartment walls, floor,'and equipment. For a

nuclear fuel cycle facility fire, the growth-rate of a hot layer from the ceiling level is naturally greater than other fire compartments that have ventilation inlet near the floor level. The ceiling ventilation inlet of a nuclear

fuel cycle facility tends to mix and lower the hot layer fairly quickly to the

floor. This ceiling inlet and floor outlet ventilation system reduces the

duration of direct radiative heat transfer from the flames to the walls and

equipment. Because of the rapidly descending smoke layer, the quantity of

direct radiative heat transfer from the flames to the floor is neglected. This

also avoids the complication of handling radiation shape factors.

From Fire to Hot Layer. From radiation heat balance, the radiative heat

transfer to hot layer, .&rhl(kW), from the flame can be written as

Qr1' =Q - Qr (2-13)

where &r is the overall radiative heat loss from the flame, and &rcl is the

heat gain by the cooler materials in the cold layer. In modeling the fire

inside a compartment, we assumed a two-layer regime: a black gas (smokey)

layer on top, produced from the rising of the hot fire products and 2) a cooler

layer below the smokey layer that contains no contaminant gas, only air.

2.12
ý,is calculated by,

r 'Hz' ;bM" (2-14)

where Xr is the r'ad iat ive fraction of overall heat release, Hz is the heat of

combustion, and M"is the mass burn rate, g/s.

&rcl is approximated using the following expression in the code:

Qrc Q cr (2-15)

where Zcl is the thickness of the cold-layer and Zrm is the height of the fire

compartment. In using the ratio of Zcl and Zrm to obtain Orcl' we assumed that

the radiative heat release from the flame is uniformly distributed to both the

hot and cold layers. Combining Equations (2-13) and (2-15) gives

0Z

Q Q 1 c,(2-16) rh 1 V

Since the thickness of cold layer Zcl approaches zero at some points during the

fire, Qrhl becomes Qr as Zcl approaches zero. Zcl is determined from calculating the hot layer accumulation during the progress of the fire and by assuming

that the hot layer behaves like an ideal gas.

In FIRIN, the radiation from fire to hot layer is calculated in every time

step to demonstrate transient behavior. For each time step, Equation (2-17) is

used:

1

Q =Q At Q 1 cl Ati (2-17) rhl rhl r rm

where At is the size of the time step to be specified by the user. Qrhl and At

are expressed in units of WJ and seconds, respectively. Besides fuel type and

2.13
surface area, as mentioned in Section 2.2, size of time step and height of the

compartment are also required as input to FIRIN for calculating QrhlFrom Fire to Walls and Equipment. Before the smoke layer reaches the

floor level of the fire compartment, direct flame radiative heat transfer to

the nearby walls and equipment in the odd layer will occur. This assumption is

based on the earlier supposition that the fire is anchored at or above the

floor level in the center of the enclosure. T .o estimate the fraction of

radiation that will be intercepted by the equipment and the remaining fraction

that will be received by the walls, the following assumptions are made:

" At the fire vicinity, all the equipment at risk is located at the

periphery of the compartmept, surrounding the fire; therefore, the

overall effective surface area-for heat transfer is the summation

of the projected areas of all equipment from the incident rays of

the flame.

" The shape of all equipment is generalized into a cylindrical

geometry, and the effective area can be approximated by simply

multiplying the diameter by the height of the equipment. The shape

of all compartment types is also cylindrical.

" The radiative energy received by both the walls and equipment is

.uniformly distributed.- The i'ntensity of the radiation does not

change significantly with the distance.

For large fires, the smoke layer descends quickly and the radiative heat

transfer described here occurs over a short length of time, thus reducing error

associated with these assumptions.

The fraction of the overall radi ative heat transfer to the equipment in

the fire vicinity is estimated using the following equation:

A

Q re QrlXee (2-18)

ew

where ~re-is the flame radiation absorbed by equ'ipment'at'risk; `Aee and Aew are

the effective heat transfer areas of the equipment 'nd walls, respectively; and

the ratio of Aee/Aew represents the fraction of the overall area intercepted by

the equipment. Aee is a pproximated by summing-'the individual projected area of

the equipment and

2.14
A e = D eH e *for i= 1, 2,..j (2-19)

where j is the total number of pieces of equipment modeled (FIRIN consi~ders up.

to 40 pieces of equipment). De and He are the diameter and height of the

i-hequipment, respectively. Aew is calculatedas. f~oll1ows:,,

Aew = lDrZcl (2-20)

where the diameter of the room Dr is approximated by

D= c(2-21) c 

r

where Wc and Lc are the width and length of the fire compartment if it is

rectangular in shape. Combining Equations (2-18) through (2-21) gives the

final equation for Ore:

Q re1 .e (2-22)

Again, Zcl is the thickness of the cold layer. For each time step,

Qre Q re (A~t) (2-23)

where Qre is in units of kW. The remaining fraction of radiative~heat absorbed

by the walls is obtained by using the following expression:

Qrw =Qrcl -Qre (2- 241)

2.15
where Qrci is obtained using Equation (2'-15).; The required inputs to FIRIN for

the above radiative heat transfer ca~lculations are as follows: equipment

diameter and height, and the length and width of the fire compartment.

,From Hot Layer to'Floor, Walls, Ceiling,-and Equipment. Since rapid

descending of -the smoke layer-is the characteristic of nuclear facil-ity fijre~s,

this-*hot layer becomes, one of the major radiation heat s ources other than the_

flame itself.- When the hot layer (medium-i) is in contact with another object

(medium-a).,,such as a piece of equipment or thle compartmen~t barrier, the

radiative heat flow between the two-mediums can be expressed as follows (Holman

19;76);:

a, .14 T24)

Q r1,2le /c2 - 1 (2-25)-

where cy = Stefan-Boltzmann constant =.5.669 x 10-8 W/m2 OK4

A = contacting area of mediums 1 and 2 .(in2 )

Ti, T2 = temperature of mediums 1 and 2 (-K)

£1, e2 'x thermal emissivity of mediums 1 and 2.

As~suming a smoky fire, which is typical,in burning of combustible materials

commonly found in nuclear fuel cycle facilities (e.g., cellulosic materials,

plastic, and rubber materials), the smoke layer may behave like a black body

with el 0.9 (Berry 1980). The emissivity for mediuin-2 is mostly material

dependent. The FIRIN data base contains values of emissivity for various types

of construction materials.

Radiative heat transfer between the hot layer 'and its contacting 'surfacesis also determined for every time step [after 'substituting' el OA A.9n

Equation (2-25)]:

2.*16
44 oA(T. 1 T &t

1 2 (.2-26)

11/C2 + 0.111

The contacting area, A, is internally calculated in FIRIN from input information on compartment and equipment dimensions as identified earlier.- The''

temperature of hot layer, T71, determined from m ass and energy balance inside

the compartment and the model equation, is also 'Calculated-in FIRIN (see

Section 2.3.3). The equipment and ba'rri~er temperatures, T2, are calculated

internally by the-code. The only inp-ut requirements for'cal~culating Qrl,2 are

the initial temperatures of the equipment and the compartment before the fire..

2.3.1.2 Convective Heat Transfer

In a fire, a fraction of the overall-energy release from combustion is in

the form of convective heat, while the remaining fraction is radiative heat.

The convective heat is carried by the fire gases into the ceiling hot layer.

Whenever a solid body is exposed to this mov ing hot layer having a temperature

different from that of the body, heat is transferred between the fluid and the

solids.

The overall heat release from a fire, ~,is as follows:

a alHtmb' (2-27)

while the convective fraction-per unit area of combustible materials is

Qc X XAfQ;l (2-28)

where Xc is the convective fraction of overall, heat release-, and Af is the

effective burning surface areas of fuel materials, (m2.).

For each time step, convective heat release can be expressed as,

wc = XAfQ"(A&t) (2-29)

2.17
where Qc 'is in units of WJ. This convective heat is deposited into the hot

layer via the hot gases produced during combustion.

The values of X~ for various combustible materials of interest are stored

in the data base within the FIRIN code. They were obtained experimentally as a

function of fire conditions by Tewarson et al. (1980) at the Factory Mutual

Research Corporation. Fuel surface area and type of fuel are the only required

inputs for calculating convective heat release.

Besides radiation, the fluid motions in the hot layer promote convective

heat transfer to and from the objects that are immersed. The amount of energy

transferred is governed by Newton's law of cooling/heating (Holman 1976):

&C 1,2 =hA (T1 -T2) (2-30)

where h is the convective heat-transfer coefficient, A is the heat-transfer

area, T, is the temperature of hot layer, and T2 is the temperature of the

contacting object.

The heat-transfer coefficient is sometimes called the film conductance

because of its relation to the conduction process-in the thin, stationary layer

(boundary layer) of fluid adjacent to the immersed body. The primary

resistance to convective heat' transfer is normally controlled within the thin

layer where temperature effects are important. For complex systems, heattransfer coefficients are usually obtained experimentally. In the case of fire

gases,,the following empirical relationship for h is suggested (Berry 1980):

h - 0.005 (T 1 -T2) 1/3 (2-31)

h is in units of kW/m 2 _*K. A minimum h of 0.005 is used if T1-T2 < 10K. Combining Equations (2-30) and (2-31) gives

;cl,2 = 0.005 A (T1 - T2) 4/3 and (2-32)

2Z. 18
Qc, 09005A (Tl` 1 TT 2)4 (At) (2 33)

The input requirement for Qc1,2 calculation is similar to Qr1',2 calculation

described in Section 2.3.1.1.

2.3.1.3 Conductive Heat Transfer

Compartment barriers are temporary heat.:sinks for energy-generated from,-

burning materials in an enclosure fire. The resultant heat gai ned by the barriers will eventually diss~ipate to the ambient air. The mechanism that

transfers energy through a medium (i.e., the barrier's construction mat erials)

is called heat, conduction. A simple heat-transfer rate relationship within the

medium, using the Fourier law, is expressed as a function of local temperature

gradient, thermal properties of material, and heat-transfer area normal to the

gradient direction. The following subsections show the usage of the Fouri~er

law and other heat-transfer relations to develop conduction models for the fire

compartment and for the equipment within the compartment. A transient

numerical method is employed for approximation.

Within the Floor and Ceiling. In modeling heat conduction in the.

barriers, a one-dimensional time-varying form of the Fourier equation with

convective boundary conditions is app .lied. The one-dimensional Fourier

equation with internal energy conversion (,Holman 1976) is given as

-72T qk at (2-34)

ax2 a

assuming that thermal conductivity, k, can be taken as constant. The internal

energy term q!has a unit of heat rate per unit volume, and it is used here for

endothermic decomposition of concrete barriers'., Thermal diffusivity,cd, is the

ratio of the thermal conductivity to the thermal capacity of"'the materi~al,

kC (2-35)

2.19
where p and Cp are material density and heat capacity, respectively. The units

of a are in ft2/h or m2/s. In the application of transient numerical technique, the following finite-difference approximations are employed:

a 2T (T t 2T t + Tt

32 2 n+1 n n-1)

9T 1 Tt+1 -

jt- E(Tn T n) ,(2-36)

where Ax is the finite distance between two nodal points, n denotes a nodal

point, nd +1 is the temperature at node n+1 at time t. Definitions for

o .ther terms are similar. Inserting Equation (2-36) into Equation (2-34) and

solving for Ttnl, which has the unit of *K, results in a one-dimensional

explicit nodal equation expressed as

Tt+1 Tt +a,&t(Tt -2

Tn =n 2 (T1 n2T +Tt At q'(2-37)

(A&x) 2 n+ n ni) -q

The above equation is used in FIRIN. Note that Tt+1 is determined in a time

marching technique. The temperature of a node at a future time increment is

expressed in terms of the adjacent (in the x-direction) nodal temperatures at

the beginning of the time increment. As a stability requirement for numerical

solution, the inverse of aAt/(A&x) 2, shown in Equation (2-37), must be greater

than or equal to two; therefore, small time steps, At, are recommended.

Details on q" are given in Section 2.3.4 on thermal decomposition of c oncrete.

Equation (2-37) is appropriate for interior nodes of a body. For exterior

nodal points subjected to convection, the following two boundary conditions i~n

a one-dimensional case are required (by simple energy balance):

* Fire compartment side

-k =T hi (Th - Tbi Q. (2-38)

ax bibi +r

2.20,
*Cool side of the fire compartment (assuming Q" 0 0)

-kE

ax Tbe

=h (Tb - Tj) + Qre (2-39)

where -k axTb

ax~ibi

= heat flux (kW/m2) into the compartment barriers at the

interior surface; it can be approximated as -k (Tbi±1 -

Tbi/(A),where Tbi+1 is the temperature at node b1+

= heat flux (kW/m2) out of the compartment barriers at the

exterior surface; it can be approximated as -k (Tbel1 -

Tbe)/(tAx)

exterior surfaces of the fire compartment (kW/mc - OK)

Thi hot layer temperature (OK)

Tbi . The = temperatures of the interior surface and exterior surface of

the compartment barriers ('K)

%= ambient temperature at the outside of the compartment (OK)

Qr'i , re =net radiative flux to the interior surface from fire, and

from the exterior s rface of the compartment to the ambient,

respectively, (kW/m ).

By rearranging Equations (2-38) and (2-39) for Tbi and Tbe, respectively, we

have

T hi.Thl + kTbl+l/A&x + r

Tbi k/ Ax +h

T h eT.+ kTbel/t IM

Tbe k/Ax + he

(2-40)

(2-41)

The above two equations are used in FIRIN to determine temperatures of the

convective boundary nodes for the ceiling and floor. The overall conductive

heat rate. through the barriers, by energy balance, is the net convective and

radiative heat rates from hot layer and flames to the surfaces of the barriers. The sum of Equations (2-25) and (2-30) will give such net heat rate.

2.*21
All-thermal properties-of materials, except the convective heat-transfer

coefficient, that are required for heat calculations are-available in the data

base of FIRIN. The data are limited to the materials listed in Section -3.2.1

and are assumed to have linear temperature dependence. Convective heattransfer coefficients are determined using. the empirical temperature relationship given in Equation (2-31). The type of construction material as well as

thickness of the barr~iers are the input variables to .FIRI.N for calculating

Tt+, anTTe

n Tbi,.adTe

Within Compartment Walls. The descending ofta smoke l-ayer inside the fire

compartment affects the net.,quantity of heat-.flux entering the various sections

of the wall.. The section exposed to the cold layer will receive direct flame

radiation if the fire site is also in the-,cold layer, .whi-le the-section

immersed in the hot layer will receive both radiative heat flux and convective

heat transfer from hot gases.

The nume'rical heat conducti~on model for interior .nodes of the wall is

identical to the model developed for the floor and ceiling in the above section.1 The major difference appears in the energy balance for the convective

boundary nodes at the fire compartment side. Performing heat balance for these

nodes gives

-k = nt(2-42)

where 4~et is the net heat flux (kW/m2) to the wall surface via various heat

transfer mechanisms caused by the descending-hot layer. Assuming the two-layer

regime is applicable, &net (for the wall-eto thtis,,exposed to the cold

layer) can be expressed as

ne - Ji.#Acwat '(2-43)

where Qr is the direct radiative heat (kW) to the wall given in Equationy-R(-24), and Acw is the total surface area of the wall (-m2) section that is

2.*22
exposed to the cold layer. 'Because, the hot gases transfer convective-heat to

the wall section immersed in the smoke layer, 6net for this wall section is as

follows:

n~et (Qr12 + Qc12 /A hw) .(2-44)

where Qr12' Qc12 are the radiative and' convective heat rates, respectively,

from hot gases, denoted by subscript 1, to immersed object, denoted by'subscript 2 (kW). AhW'is the total surface area of the wall- secti~on' that is

immersed in the hot gases (in2).- The input requirements to FIRIN are material

type and thickness of the wall.- The hot/cold layer interface will be determined within the program to signal thetappropriate heat-transfer calculations

for the two vertical wall sections.;

Within Equipment Walls. In nuclear facilities, highly corrosion resistant

stainless-steel or a similar material is-commonly used as construction material

for equipment and vessels. Thi's material has negligible thermal resistance

through al f airly thi~n wall; theref ore, we assumed- that the temperature through-:

out the equipment wall is-constant..

Instead of using the conduction model given for the compartment barriers,

heat balance for the equipment walls can be performed in the following manner:

Qn =MCp (T t+1 T~/t (2-45)

where'Qe net heat rate-to equipment (kW/m2)

m =mass of equipment wall' (kg)'

C = heat capacity of wall material (kJ/kg - K)

Te =+ equipment wall temperature ~at time,.t+1 (OK)

t=e quipment wall temperature at time t (OK)

At = time step Increment(s)

2.*23
Depending on the elevation of the hot/cold lay~er interface, the value Of Qne is

also affected by the two-layer regime.. Qne can be obtained by summing the

direct flame radiative. heat rate and gases convective and radiative heat rates,

respectively. By rearranging Equation (2-45), Tte isepesdieem fT

as follows:

t+1 t Te T0 T+.Qnet/mCp (2-46)

The user- inputs to.FIRIN for the above calculations are equipment type,

material of construction, elevation (with respects to the floor level), size,

and. the weight of wall material.

2.3.2 Mass, Balance in the Fire Compartment

Models for species inventories 'of both hot and cold layers are developed

for nuclear fuel cycle facility fires. Assumptions, are made in the mass

balance calculotions that no mixing takes place between layers, and only air is

found in-the cold layer.; It. is urhrassumed that mixing within each layer

is uniform., The ideal gas law is employed to obtain total mass and molar

information for gas dynamic and heat-transfer calculations. The oxygen

concentration calculated from compartment mass balance equations provides

information for the adjustment of burning mode approximations discussed in

Section 2.2.4.

2.3.2i.1 Cold LayerSince the cold layer is assumed to~contain uncontaminated air, only oxygen

and nitrogen balances are necessary. A li~st of the components in the continuity equation for both the oxygen and, nitrogen balances in the cold layer

follows:

Rate of change of-moles of oxygen and. nitrogen-in~side the cold layer

depends on

" flow of oxygen and nitro~gen into the cold layer from inlet

ventilation

* flow of oxygen and nitrogen from the cold layer to outlet ventilation

2.*24
*consumption-Of oxygen.,in the fire

*entrainment of oxygen and nitrogen by fire plume away from'cold layer

.. flow of oxygen and nitrogen from the cold layer to new flow paths.

The flows of oxygen and nitrogen through the ventilations can be obtained by

multiplying molar density of air by ventilation rate during ea~ch time step.

The results are corrected to temperature a~nd. pres~sure of the cold layer. The

number of moles of oxygen consumed 'in the fire is back calculated using gaseous

generation rates in combustion, which are approximated using the fuel material

data and burning mode concepts' (Section h2'.2.4)'. 'Plume :an d n'ew1 fow 'p'at h*

entrain'ment is discussed, in'Section",2.3.5.

2.3.2.2 Hot Layer

Component balances in the hot layer -include carbion dioxi~de, carbon

.monoxide, water, HCl, nitrogen, oxygen, and methane. 'The ge'66eral" c'ontinuity

equation contains the follo6wing components:'

,Rate of change of moles of component inside the hot la'yer depends on

" flow-of the component into the hot -layer from inlet ventilation

*flow of-the -component f rom-the hot, layer to outlet-ventilation,

*decomposition of thcmoin conre budre e ar~ 'ito 'th~ eýhot`'

layer

" generation/consumption of the component in the fire

*ntanetof component, by -the ,f ire ýpluqme into the.hot l'ayer._-

*flow of th~e component' fr'om the -ht lAayer 'to6 niew" flTow paitihs.

Methane shows up in the inventory to represent unburned pyrolysate from fuel.

decomposition. Carbon dioxide and water can be generated from combustion and

from thermal decom'position6 of cddnc'rete'." H'ydro'chloric ac'id vapor :may"be found

in fuel cycle facility fires generated by the burning of wrapping materials

made of polyvinyl ch~loride (PVC). -

Material balance in the hot layer also includes both radioactive and combustion-generalted particles.' Various radoioactive source' term models are give'n

2.25
and discussed in Section 2.4. The generation rates of soot particles from

burning combustible materials commonly found.1n.fuel cycle facility are

described in'Section 2.2.3.

2.3.3 Heat Balance in the Fire Compartment

In order to calculate hot layer temperature, an overall heat balance in

the fire compartment must be performed. Using the principle of conservation of

energy, and assuming that potential- and kinetic-energy terms are negligible, a

simplified form of the internal energy and enthalrpy equation can be formulated

as follows:

Rate of change of internal bnergy of-hot layer depends on

" flow of enthalpy (direct flame radiation) into the hot layer boundary

" flow of enthalpy into/out of the hot layer boundary.

" energy (heat) added to the hot layer by combustion

" heat lost-to equipment at risk in~side the fire compartment

" enthalpy in the hot layer.

Rate of change of internal energy of hot layer after differentiation

=Cp, (pjVj TH11 -P 2V2TH12)/At EJkW (2-47)

where C, specific heat capacity of the hot. layer at constant pressure

p (kJ/kg-OK)

=mass efnsity of the hot :layer, at new and old time step .(kg/in3), respectively. (They are obtained from mass balance)

=1V volume of fire compartmeni occupied by the hot layer at present

and previous time step (m ),respectively

THl1,TH12 =hot layer temperature at presen t and previous time step (in3 ).

respectively (*K)

At =time step increment (s)

The flow of enthalpy into the. hot layer boundary after differentiation is equal

to the flame radiation to the hot layer (Qrht/,6t) which is given in

Equation (2-16).

.2.*26
The flow of enthalpy into/out of the hot layer boundary after.

differentiation equals heat gained/lost by convection and radiation from/to-the

ceiling, floor-ý and wall of the fire compartment + heat gained/los~t by

ventilation to/from the hot layer. The'.eqduation.is'

=(Qric +-Qriw -+' Qrf. ;+ Qcic;:+ Qciw .+ Qcif) / At. +.

*m(TH12 -T)_t (2-48)

where Qrlc'Qrlw'Qrlf =radiative heat transfer between hot layer and ceiling,

wall, and floor, respectively, (kJ) [see Eq. (2-25)]

QclcQclwQclf =convective heat transfer between+ hot layer and ceiling, wallV, ýand-'floodr respect ively, (kJ)see Equation (,2-30)]

m =mass of hot gases in smoke layer (kg) obtained from

mass balance,.

TH 12 =hot l ayer- temperature at -previous -time. step (OK)

Ti =initial temperature of the compartment before fire

(OK).

The energy (heat) added to the hot layer by combustion after differentiation

=convective heat from burning

Qc(2-49)

which is calcu~lat~ed-as shown in- Equ~atioqn J-2-29). The heat lIost to_ equipment at

risk inside the'fire compartment' after ditff erent~iation equ al1s' the heat lost by

hot layer con~vectlion ,and .radiation. to.~equi~pment

where Qrie is the hot layer radiation to equipme~nt,(.kJ) [see-Equation (2-25)),

a nd Qcie is the hot layer convection to equipment (kW) [see Equation (2-30)].

The enthalpy in hot layer after d-ifferýentia~tion'

2 * 27
=P 2V2Cp (THl2 ý-Ti) (-(2-51)

Combining all the above equations'and solving for Thll, we get

P2 2 __

TH11 = (.P2'2) TH12 + 1 Eh + jc+rw+ rf+Qi+Qi +cf

+ C~(Tl 2 -Ti) + Qc re-Qi~~VC p (THl2 - Ti)]

This equation is used in FIRIN to predict 'new' hot layer temperature as a

function of 'old' hot layer temperature, convective and radioactive heat

transfer, and enthalpy associated with ventilation flow. The major input

parameters, other than those given earlier for heat transfer calculations, are

initial compartment temperature and pressure, elevation of inlet and outlet

ventilation ducts, initi~al ventilation rate, and vertical elevation of the

fire..

2. 3.4 Thermal Decomposition of Concrete

Concrete is commonly used as the building material for nuclear fuel cycle

facilities. Typical concrete barriers found in this facility have thicknesses

ranging from 6 in. to several feet. During a fire, the gas released by thermal

decomposition of concrete has the potential of sufficiently increasing pressures to endanger the integrity of a facility ventilation and filteration system. Depending on the nature of the concrete, up to 30 wt% of the material may

be volatilized at elevated temperature (Powers 1977).

Thermogravimetric analyses of small calcareous concrete samples at Sandia

National Laboratories reveal the following three major weight-loss events over

the 200 to 12000C tempera ture range (Powers 1977):

" loss of evaporable water (55 wt% of concrete mass at 200 to 200'C)

" loss of chemically constituted water (ý5 wt% of concrete mass at

2000 to 6000C)

.* loss of carbon dioxide (-22 wt% of concrete mass at Ž 6500C).

2'028
The kinetic equations describing the above weight-loss events may be empirically fitted using first-order rate laws. Powers (1977) formulated these

Arrhenius rate equations in the following manner:

dY1

dI= (1-Y1) exp [(14.07 - 5.557)/T) (2-52)

-Y (1-Y ) exp:[(28.31,- 20560)/T]. (2-53)

dY3

=t (1-Y3) exp [(16.8 -19362)ý/T) (2-54)

where Y.i denotes the fraction of gas released and the subscripts 1,2,3 refer to

evaporable water (water), chemically bound water (water vapor), and carbon

dioxide, respectively. As before, T is the concrete temperature in degrees

kelvin. In the application of a finite difference technique on modeling mass

transfer in concrete, Beck and Knight (1980) approximated the above equations

with

y1t+l = - (1 -ylt) exp [-At (exp ((14.07 -5557)./T))] (2-55)

y2 t+1 1 -(1 -y2t) exp [-At (exp ((28.31 -210560)/T)))l (2-56)

Y3t+l=1 -1 0 -Y3t) exp [-At (exp ((16.8 - 19362)/T))] (2-57).

where Yt1is the fraction of evaporable water released at time t + 1.

Definitions for other Y terms are similar.

These equations are used in FIRIN to predict the material released from

heated concrete during a fire. The temperatures used in these equations are

the nodal temperatu res of the barriers (see Section 2.3.1.3). The required

2.*29
inputs for these calculations are thickness and-dimension ,s of-' the' barrier.

With concrete density. available i~n.the data base as the function of temperature, both mass and molar evolution rates of water, .water vapor,-and carbon

dioxide are. calculated for mass and -energy-balance, and.,gas dynamic

consideration.

Furthermore'. the iAnternal. energy, term for ýba rrier -conduct ion" can be

expressed-as the summation of energy-;absorption rat~es for the' three decomposing

.species:

qY. 1 H Y2 H Y3 (2-58Y

q1 '1PA1 . A 2 P 2 T-~ 3 3+-

where AH1 is the heat ,of ,degradatio~n to form i (.kJ/kg),, and pi, is the mass

density of i (kg/in3),.

The above equation assumes flow resistance of'vapori~zed water ~and carbon

dioxide equal to zero within concrete. Again, qt has ý'units of kW/m.

Currently, the. p~ values listed in FIRIN are,101,..101,. and 975 kg/rn3, for

water, water vapor, and carb~on diloxide, ,.,respectively,, whi~le the AHi values are,

2.79 x 103, 5.81 x 103,,and 4.18 x.103 kJ/kg,, respectiv-ely.

2.3.5 Fluid Flows

Three major mechanisms of-'flu6id motion-can -be.. identified in a typical fuel

cycle facility fire that would enable the transport of radioactive aerosols.

They are fluid flows caused by

o fire plume entrainment

o ventilation

o additional flow paths.

The characteristics of each mechanism are disc-ussed ,in the fol~lowing

sections. Model equations are derived and given for characteristics that

govern- the release of radioactive particles In' fires.

2.300%
2.3.5.1 Fire Plume Entrainment

A fire plume can be pictured as a continuous rising 'mass of hot gss

vapbrs, and particulate materials generated 'in the flame beneath it.' Because

of oxygen demand for combustion,.the fl-ame acts, as'a natural pump, which draws

in air from its vicinity.* Some of the drawn air will, be consumed in the* flame,

while the rest is entrained into the plume to mix and cool the hot gases. , In

an enclosure fire,-the hot layer or smoke layer is the resultant mass-from the

rising plume.

Frequently, fluid motion, near -a burning object has turbulent behavior

caused by the entrainment process. If the burning object or its vici nity is

contaminated with radioactive particles, they can be entrained into the hot

layer; therefore, characterizing this turbulent fluid motion is important in

order to predict radioactive source terms in. fuel cycle facility fires. At

PNL, parameters such as rate of entrainment and temperature have been

correlated with radioactive releases from burning objects contaminated with a

known quantity of radioactive materials.

FIRIN-uses the equationt derived-by Zukoski, Kubota, and Cetegen (1980) to

calculate entrainment of gases by the fire plume. According to Zukoski' s

theory, the plume mass flow rate, Mpt, can be calculated by

M ='r 0.21, P1Tz z. 1 (2-59)

where Apt =plume mass flow rate, g moles/s,

p =gas density, g mole/ni

q =gravitational constant, m/s2

z =flame height, mi

=* dimensionless heat addition parameterUsing the ideal gas law, the gas. density can be calculated by

P n-..P (2-60) V RYT

20- 31
where n':-=.number .of ýmoles of. gas,, g ýmol es

V =voumem 3 :

P =pressure, atm

V;= gas constant, (atnm m)/(g mole OKI

T =,temperature,_ 0K -

Equati~on (2-59) can ;be rertten -as

Mp 021.T' P z 2 .511/3 .(2-61)

The dimensionless heat parameter, Qis used in

relationships developed by Zukoski. Q* is defined as

Q /p, Cpý T. g~z 2)z

where _Q =heat, release rate, kW

Substituting (P/RT). for pý, this equation becomes

several empirical

(21-62)

Q/E (P CP/R) v' -z25

Zukoski noted that-.for a wide range of natural gas fire

height, z, followed the relationship

sites, the flIame

=0.23 0. (2-64)

This equation has b~eenused in-FIRIN as the best available' 'mean's of calculat-ing

flame he~ight for all .fin~al types int~he- FIRIN data~base.,

During each-t'ime 'step of'the fire, FIRIN calculates-the' h e ,at release rate'

based. on b~urn ,paramete'rLS described,-in Section 2'.2. Pressure and temperature of

,2,-. 32
the fire compartment are also internally calculated*.,Equ~ation 2-64, 2-63, and

2-61 are then used to determi~ne the flow ratelof-gasest in the-plume.

2.3.5.2 Ventilation

Most nuclear fuel cycle facil~ities luse forced a-ir ventilation. Outlet

ventilation is commnonly found near the-floor level, while inlet ventilation is

often located near the ceiling.- in a fire, flow: in thois- t ype .of "Orientation

tends to draw the smoke layer'down .hto the floor level qulte-rapidly., Major

nuclear fuel cycle facility fires may be underventilated because of oxygen

deficiency in the hot layer, which reaches the'fl-ame zone early in the fire.

The ventilation flows may carry radioactive aerosols with, comb~ustion aerosols

to the building exterior through the facility.,ventilation system.

High-efficiency particulate air.(HEPA) filters.'are conunonly used in the

facilities to prevent-the outside environment-from ,being exposed to airborne

radioactive particles. In a fire, exposure ..of a HEPA filter to; heat and smoke

.significantly changes the filter's operating c~haracteri~stics. Investigators at

New Mexico State University (NMSU) and LANL have ijnvestigAted the characteristics of HEPA filters plugging with combustion aerosols (Fenton et al. 1983).

Two fuels, polystyrene and polymethyl methacrylate, conunonly found in nuclear.

fuel cycle facilities as bagging materials and glove box viewing windows,-were

selected for their experiments to produce comhbustion aerosols. An empirical

model for ventilation flow-through the HEPA filter was formulated by applying

the preliminary experimental results from burning polystyrene.

Pressiure drop across a filter can be related-to flow rate as follows:

AP QR (2-65)

where AP is the change in pressure (or -pressure drop)., a~tm, Q is the fluid flow

rate (or ventilation rate), m3/s, and R is the filter-resistance.

The magnitude of this filter resistance de .pends. on ~aerosol type, aerosol

size distribution and concentration, water content,,fluid temperature, and

other factors, such as flow conditions i~n the fluid stream. Filter resistance

2.3.3
can be written as a-monotonically increasing function of the-total mass of particles' accumulated on-the filter (Fenton et al..1983)ý:

R= (1 +oM5 +am 2) R0 (2-66)

where $,and aare the filter resistance parameters determined by experimentation, Ms is the total mass of particles on the-filter, and R0 is the value of R

for a clean filter. The preliminary results from burning polystyrene at.

various burning rates give the average a value of 9.79 and a value of 0.01395

(Fenton et al. 1983). Rearranging the pressure drop equation for Q and

replacing R with-the above ecjuation gives.

Q = P/(1 + 9.79 Ms+ 0.01395 M )R 0 (2-.67)

Using this equati~on and the appropriate pressure drop, inlet and outlet ventilation rates Onand Oout) can be expressed as

~i P 2)1(1 + 9.79 Ms+ 0.01395 Ms2 R 0 (2-68)

out =(P 2 -P 3)/(' + 9.79 M5 + 0. 01395 Ns ) R 0 (2-69)

where P1 = pressure at inlet ventilation, atm

P2= transient compartment pressure, atm

P3 = pressure at outlet ventilation, atm

*Ro = (P1-P2i)/&i

P2i = initial compartment- pressure, Atm

&i= initial ventilation rate, m3/s.

The transient compartment pressure is calculated using the ideal gas law. MS

is obtained from the material balance of the hot layer and from accumulative

20*34
mass inventory on filter media assuming all particulate materials will be.

captured by the filter. The required inputs to FIRIN-are Q1 i, 1 Pj9,P~ and P3.

2.3.5.3 Additional Flow Paths

Openings other than ventilation duct's to a fire compartment are considered

to be additional flow paths where radioactive materials escape to the outside.

Gloveboxes are-examples. 'of compartments-where gloveports may be addit~ional flow

paths if the gloves, burn, in a fire.

Characterizing flows throu'gh thie'paths is anlavlaila .ble option as part of

FIRIN's capabilities. :Because a large quantity of mass clan escape through the

paths in the absence of filtering media, being. able to quantify the amount of

airborne radioactive materials released is important.- 'The required inputs are

number of additional flow paths, their failure times, size of openings, elevations of the paths, and the pressures at the exits of all specified paths.

Currently, FIRIN allows up to 20 flow paths.

_When FIRIN is used to~simulate nuclear facility fires,.both radioactive

and fire-generated particles (i.e., soot)-can be monitored for mass release

rates (in g/s) through the additional flow paths. The model equations are as

follows:

-Soot release rate, Osr (through additional flow paths)

=(hl)(/RT Isr hl).f (2-70)

-Radioactive release rate, Orr (through additional flow paths)

rr= J P N fp (2-71)

2.*35
.where Mshl, Mrhl =mass of soot and airborne radioactive materials in the hot

layer, (g)

Vhl =volume of hot layer, (in3)3

R=universal gas constant =.8.206 x 10-5 m atm

g mol e 0 K

Thl : hot layer temperature, *K

P2 =transi~ent compartment pressure, ýatm

Nfp =molar-rate of gases through a flow path,ý g mole/s.,

.FIRIN determines Mstand Mrht by material balance,, while Ttis calculated by

performing heat balance in the fire compartment. Vht is estimated in FIRIN

using the ideal gas law, and Afp is calculated based on-the concept o ,f flow

through an orifice corrected to temperature and pressure.

2.3.6 Particle Depletion

Mechanisms that were identified as being potentially important to the

depletion of aerosol particles are the following:

* sedimentation

" Brownian diffusion

" diffusiophoresis

" thermophoresis.

:Each mechanism was 'evaluated,, -and prelimi~nary -predic~tive equations were

derived to quantify the particle deposition caused by each mechanism. A simple

two-layer model was used to describe particle transport and deposition in the

'fire compartment. Each -layer was -considered ýwell-mixed. PRart-icles can enter

.the lower .(.cold) layer by ýgravity settling. FlIow.,entrai~ned -in the fire plume

can .carry the lower compartment-particles to'the upper (hot.) layer. Deposition

Mechanisms modeled in the -hot -layer are gravity sýet~tling, .thermophoresis,

diffuslophoresis and Brownian diffusion.. Becaus~e only the 'heavier' particles

are in the cold layer, deposition was restricted there to gravity settling. 'A

Laplace Transform solution was obtained for the unsteady-state particle

behavior over a time step At.

2.36
Sedimentation

The removal-rate constant for gravity se~ttling. is simply the product of

settling velocity and surface area:

Ks =VsAs (2-72)

where Vs particle settling velocity, rn/s

-As horizontal upward facing area, Min2

Particle sett~ling vel.ocity, V5., can be related to particle size and gas

properties by'mea~ns of Stokes' law:

p d 2gC

V5 (2-73)

where pp = effective particle density, kg/rn3

dp= effective parti cle diameter, m

g = acceleration due to gravity, rn/s2

Cm = Cunningham correction factor, dimensionless

P=gas vi~scosity, -kg/.m-s

-Combining the previous, two equations leads to

p d 2gC A

'K LE ms (2-74)

The settling a rea, As, is the floor of the compartment.

Stokes' 'law is .valid for Reynolds numbers up to -1 (Knudsen and Katz

19-58), w.h ich corresponds to an aerodynamic p~ar-t~icle diameter of ~-70 pim. If

.larger part~ic-les are present,, their settling velocities are computed using a

.modified equ~ation that would account for-the change in drag coefficient caused

,by the change in Reynolds number.

2.*37
Brownian Diffusionr

Particles exhibit' a'diffuisivity as a result of momentum exchanges with

surrounding gas molecules., For the case-where the gas is isothermal and has no

molecular weight gradients, the particle mobi~lity arises fromBrownian diffusion. Particles would experience a net flux toward surfaces because of concentration gradients; particle capture by the surface is assumed to reduce the

gas-phase concentration of particles to zero.

The efficiency of deposition depends both on the diffusivity and the fluid

flow pattern past a surface. For naturally convected flows, a mass transfer

coefficient can be predicted using a heat transfer/mass t ransfer analogy

(Knudsen and Hil ,liard 1969; Bird et al. 1966):

k 0.13 (Gr St) 13(2-75)

where kD mas's transfer coefficient, m/s

£=length of surface in direction of flow, m

Gr =Grashof number

Sc =Schmidt number = ji/pD.

The Grashof number characterizes the flow of naturally convected boundary

layers'. It may be expressed as

3

Gr -r AP-~~ (2-76)

where I = length of'surfa'c'e in direction of fl~ow, M

g = acceleration due to gravity, in/s2

v = kinematic viscosity of gas, m2/s

AiP = density diffe 5ence in fluid-bulk compared to fluid at the

surface, kg/in

p = bulk density, kg/in.

2.38.
The density difference, &p, is the total value that would result from both

temperature differences and differences in molecular weight.

Since the layers are assumed to be well-mixed , the density difference in

fluid bulk compared to fluid at the-surface is proportional to the difference

in temperature between the bulk fluid and surface fluid. Therefore,

T T T

p Tavg

Diffusiophoresis

The condensation of steam onto surfaces causes particle drift by two

mechanisms: 1) a net flow of gas occurs toward the cool surface, often termed

Stephan flow, which convects particles toward the surface; and 2) the gradient

in steam concentration results in a molecular weight gradient that causes

particles to experience a force in the direction of the gradient. For steam

air mixtures, these two mechanisms are opposing; however, the Stephan flow

dominates and the particles are convected to the surface and scrubbed by the

condensing steam.

The removal rate constant, KD, may be expressed as

KD = V DAD (2-78)

'where VD = particle deposition velocity, m/s

AD = surface area for diffusiophoretic deposition, inm

The net deposition velocity caused by both Stephan flow and the molecular

weight gradient may be related to particle and gas parameters by means of a

formula presented by Waldmann and Schmitt (1966):

VD Q7d~ 1 + CrX D dXj (279 T~ (2-79) 2 1

2.39
where VD =drift velocity of a particule caused, by condensation of steam

or ice, rn/s

a12 =a parameter whose value is dependent on the molecular

weights of the two gases present, dimensionless

X2= mole fraction of non-condensible gas

D= diffu~siv-ity of steam/air mixture,. m2/s

X =mole fraction of water vapor

y'= d'istance measured from the surface onto which

condensation occursý, m

w = a subscript referring to properties at the wall (surface)

onto which steam condenses.

The value of 012 depends on particle and gas parameters. For large

particles (diameter large compared to the mean freepath of the gas) Waldmann

and Schmidt (1966) present an empirical formula:

S 0.

95 m 1m d 2 (2-80) 12 m1 +m2 d1+d2

where inm molecular weight of the gases

d =atomic diameter of the gases

1,2 =subscripts referring to condensible and noncondensible gas,

respectively.

dX-Iy is the velocity of steam to the wall and may be calculated by

2 1w

- Hc (HlI w (2-81) S Pg

where. V5 = velocity of steam tothe wall1.j, m/ S

Hc = condensing heat transfer coefficient, J/m2soK

X = heat of condensation, J/g

2.40
-TH1 '= hot layer temperature, i 0KV

TW= wall temperature, OK.

Pg 9 gas density, g/m3

Thermophoresi s

Particles experience a radiometric force when they are sus~pended'in a gas

in which a temperature gradient exists., In general, the drift velocity is

directly proportional to the magnitude of the t~emp'er~at~ure :gradient (Waldmann

and Schmitt 1966; Goldsmith and May 1966; Gieseke 1972)::

VT cdT. (2-82)

where- VT =thermophoretic drift velocity, m/s

C1 a constant wh se value depends on particle and gas properties, m Is*0K

dT temperature gradient, 0K/m.

The removal rate constant, KT, resulting from thermophoresis is the

average of the products of deposition velocity and surface area:

K TAT (2-83)

where AT =,surface area for thermophoresis, in2.

The temperature gradient that-causes particle drift also causes the

transport of sensible heat fr om the gas phase. The rate of sensible heat loss

may be related to the temperature gradient in the gas adjacent to the surface:

heat loss rate 4~AT dT (-4

where k =thermal conductivity of gas, W/m.K.

2&41
The, heat loss rate is calculated In FIRIN. Therefore'.

dTI-heat loss rate .(2-85)

~~.-k A.

and

VT ~ C heat loss rate (-6

The numerical value of C1 depends on particle and gas properties;

predictive equations that account for important parameters are listed in

Waldmann and Schmitt 1966;' Goldsmith and May,1966; and Gieseke 1972. Rough

estimates of Ciaindicate that this quantity has a numerical value of

-1o- 3/0C.

The thermal diffusivity a is equal to k/.pCp. Therefore,.

V 0-3 HLR (2-87)

where HLR ,= heat loss rate, kW

Cp = specific heat' of air, J/kg-OK

p =density of gas, kg/in3

AT =surface area, inm

2.4 RADIOACTIVE SOURCE TERM MODELS

Several major mechanisms are identified as causing radioactive material

releases from fires in a nuclear fuel cycle facility. These mechanisms are

modeled using information generated in experimnents at PNL as well as from

current literature,. Models are built into the FIRIN code in the form of

su broutirnes enabling estimation of the mass, rate and size-distribution of

20*42
radioactive particles.-becomin'g air~borne* in a fire. The models and eventcontrolling parameters involved are discussed in the following sections..

Radioactive releases mechanisms from' fires include the following:

" burning of contaminated combustibles

" heating of noncombustible contaminated surfaces

" heating of unpressurized radioactive. liquids

* pressurized releases of radioactive materials

" burning radioactive pyrophoric metals.

2.4.1 Burning of Contaminated Combustibles

Radioactive particles may become ai~rborne in nuclear fuel cycle materials

from burning contaminated combustibles. Waste materials such as rags, gloves,

plastic bags, and combustible portions of gloveboxes can contribute to the fuel

loading as combustible solids. Liquids such as solvent extraction fluids and

cleaning fluids may also be involved in a fire.

2.4.1.1 Solids

A series of 25 experiments were performed to provide data for the radioactive aerosol source term subroutine of the FIRIN fuel cycle facility compartment fire code (Halverson and Ballinger 1984). The experiments involved burning various combustible materials with radioactive contamination of several

forms. The data collected in the experiments. included cumulative radioactive

aerosol release, cumulative smoke release, and mass loss rate of the

combustible material.

Table 2.4 lists the combustible materials, contaminant materials, and the

various parameters that were varied during th e experiments.

The' radioactive sourc.e term '(ST) r Ieleas .e Was correlated with the parameters that were var Iied in the'experfments*. Experimental data can be found in

Appendix A. The correlationes were'ca'rried out using the MINITAB statistical

package. Linear 'regressions were* run 'on the data, and the regression that fit

the data best was'chosen 'at the FIRMN model'. The' goodness of fit was determined by comparing the R2 values obtained in the regression analysis. The

2.ý4 3.
TABLE 2.4. Experimental Parameters

Combustible Materials

Cellulose

Polychi oroprene

Polystyrene

Polymethyl methacryl ate

Contami nant Material s

Depleted uranium dioxide (DUO) powder

Uranyl nitrate hexhydrate (UNH) solution

Uranyl nitrate hexahydrate salt

Other Parameters

External heat flux

Oxygen concentration

Airflow

Contaminant concentration

Ignition system

higher the R2, the better the fit. Standard t-tests were used to determine the

significance of the regression constants. Those constants that are statistically no different from zero are set at zero to simplify the regression

equation.

A separate equation (in some cases, more than one equation) is used to

describe RST release from each type of combustible material. These equations

are shown in Table 2.5.- The cellulose and PC release predictions are given an

upper limit of 0.01 and 0.05, respectively. Polystyrene and.PMMA are assumed

to be spike releases occurring in the time step in which the combusti~ble starts

to burn.

Other combustible solids in the FIRIN data base are PVC and wood. Polyvinyl chloride releases are assumed similar to PC, since both materials are

charring polymers. The cellulose equations are used for wood. If combustible

2.44
TABLE 2.5. Radioactive Source Term Equations for Burning Contaminant Combustible Solids

Combustible Material Contaminant Form Equation

Cellulose

Polychl oroprene

Polystyrene

Polymethyl methacryl ate

Air-dried UNH

UNH liquid

DUO powder-flaming combustion

DUO powder-smoldering combustion

UNH liquid

DUO powder, air-dried UNH

.A

U1r

Mr

Ar

Mr

Ar

Mr

Ar

Mr

= 7.40E-7 x Wr x Ab x QT

= 6.08E-8 x 'Wr x Ab x QT

= 1.18E-9 x ki xAb x V x UC x QT

= 5.64E-6 x Mb x Wr

= 0.104 x Wr X

- 0.0227.x Wr x S

= 0.02 X Wr'

-0.007 x Wr

-0.'02 x Wr

-0.05 x Wr

LJNH liquid

Air-dried UNH

UNH liquid

C". DUO powder

Ar

Mr

Mb

QT

ýr

UC

V

Wr

= mass release, rate of radioactive particles, g/s

= mass release of radioactive particles, g

= mass loss rate of fuel, g/s

= external heat flu Ix to the combustible, kW

= smoke release rate, g/s

= uranium concentration, gU/g combustible

= air velocity, cm/s

= mass of radioactive material, g
materials other than those *in the FIRIN, data base are input to: the- code, a'''

radioactive source tern release of 1% is used, and the rate of release assumed

to be proportional to the mass burn rate.

The size distribution of radioactive particles made :airborne was also

measured. for some of the experiments.. This information is used in FIRIN to

characterize the size of accident aerosols from. burning. contaminated solids.

If combustible materials other than those in the FIRIN data base' are input to

the code, FIRIN assumes the radioactive aerosol produced is-:similar in size to

that of ball-milled uranium given -in Mishima and,.Schwendiman .(1973a).

2.4.1.2 Liquids

Fires involving solvent extraction fluids or combustibl'e-liquids' used to

clean or maintain process eiquipment in a nuclear fuel cycle facility may cause

radioactive materials in contact with or in solution with the, burning fuel to

be released.. Experiments at PNL,' Savannah River, Germany, and France have

examined the release of radio~active materials from'pool fi'res.

Halverson et al. .(1987) report small-scale experiments at PNL in which a

solvent/acid combination was burned. Either the oirganic, the acid, or both

were contaminated with uranium before burning. The radioactive release' was

larger in the burns that gave off more smoke, suggesting that uranium is

carried up with the smoke or that the smoke producing mechanisms (i.e., a

higher more viole~nt burn rate involving'the*TBP in solution) also produce

uranium aerosols. Another explanation is that the UNH is chemically tied to

the TBP as a coordination complex., Wh~en. this complex. burns., UNH is directly

involved in the combustion process. A maximum of 5% smoke. was given off in

these tests with up to 7% uranium release.

Experiments reported by Jordan and Lindne'r,(1983, '1985) indicate uranium

release is a function of uranium concentration' which' in turn is a 'function of

burn rate. Therefore, in these experiments, burn rate influences uranium

release. A lower uranium concentration used 'in'th'e burn tests may be the

reason the Jordan and Lindner experiments obtained a maximum of 1.5% uranium

2.46
release compared to up to 7% uranium released in the PNL experiments. About

14% smoke was given off when 70/30 kerosene-TBP was burned, and TBP 'was

identified as the major smoke producer.

Malet et al. (1983) describe-pool fire tests carried out at the Cadarache

Nuclear Research Center in France.. Less than 1% of the contaminants-(cerium

and thorium) reached the filters in the small-scale fire tests and le'ss than,

0.1% in the largeý-scale tests. Although a very'small amount of the co'ntaminant

is reported to be left in-the organic residue-after the burn, the complexity of

analysis techniques and uncertainties in mass balance preclude the use'of thes e

data in estimating the amount airborne.

Earlier experiments at PNL (Mishima and Schwendi~man 19.73b; Sutter,

Mishima, and Schwendiman 1974) burned contami~nated sol~vent. Small-scale

experiments resulted in a,0-1% or less release of all contaminants except. or

iodine of which 85% was made airborne. The large-scale test resulted ,in a

release of 0.2% strontium. Harper and Jolly (1964) also reported 1% or less

release from contaminated pool. fires.

As much as 11% uranium w~s made airborne when gasoline was spilled over

contaminats and burned outdoors (Mishima and Schwendirnan 1973a). In the tests,

surface type and airflow rate greatly influenced releases. These experiments

simulatedo~utdoor ,transportation .accidents and are not as applicable to

contaminated combustible liquid fires inside nuclearzfuel cycle facilities as

the other data cited.

The only data on'release of volatiles from bur'ning cýontamin~ated,"combustiýble liquids are 64-84% release of iodine in the small-scale experiments

reported by Mishima and Schwendiman (1973b). If the'maximuim release (84%) is

assumed to occur uniformly throughout the burn,.the followi~ng equation-may be

used to predict release from volatiles:

mass rate (g/s) =0.84 Wr/t (2-88)

where Wr is the grams of radioactive volatiles in the solvent and

t mass of. fuel (g) (-9 =mass Moss rate (g/s) (-9

2.47
For all other contaminants, Halverson et al. .(1987) provide the most complete

and conservative data.

These data show that uranium release is greatly influenced by smoke

release. At the start of.a fire involving ke'rosene/TB.P mixtures, the more

volatile component, kerosene, burns first and TBP concentrates as the burn

progresses. However, toward the end of the fi re or-if the fire burns more

rapidly causing turbulence in the solvent, TBP -burns, producing most of the

smoke. Radioactive contaminants appear to be~carried; up with the smoke during

this smoke production process. At high burn rates radioactive particles may be

spewed up by the boiling or frothing of contaminated ac~id under the burning

solvent. A linear regression on the data provides the relationship:

Fraction Uranium = 1.38 Fraction Smoke - 0.0033 (2-90)

Taking the derivative with respect to time, the constant drops out (making the

equation' slightly more conservative), and the source term equation becomes:

dFU. 1 3 dFS (-1 dt8 2-1

For each time step, FIRIN calculates the mass rate of uranium released based on

the release rate of smoke, by

U releas~e'rate (g/s) =1.38 ýsmoke release rate (/s)

g combustibl~e liquid (,2-92)

x g Uranium in liquid

The mass;-of co'mbustble liquid and mass of-uranilum at-risk, either in solutionor in con'tact -with th'e combustible liq uid,, are input .to the-code. FIRIN

calc'ulates smoke releas Ie rate-an d, using the above equation, Iuranium rele Iase

rate.

The size distribution of radioactive aerosols was measured in one of the

PNL experiments reported'by Halvers-on et al. (1987). An airborne, mass median

diameter of 0.6 and geome~tric standard deviation of 3.1' resulted., Table 2.6

lists- the data used-in FIRIN for sizes of radioactive airborne particles from

burning contaminated combustible liquids.

2.48
TAB LE 2.6. R Iadioactive .Particle Size Distribution f ro-m

Burning Contaminated Combustible Liquids'',

(Halverson et al. 1987)

Particle. Size, (p) % of Particles

<0.1 5

0.1 - 0.3 21

0.3ý-0.5 15

0.5 - 0.7 20

0.7 - 0.9 11

0.9-1. 6'

1.1-2.8

2-6 10.8

6-10 2.9

10-20 -0.3

>20 0.0

2.4.2 Heating of Noncombustible Contaminated Surfaces

Fires heating contaminated surfaces cause radioactive particles to be

released because of induced air currents caused by the fire, changes in the

contaminant moisture content, and changes in radioactive particle adhesion to

surfaces and other particles.

Experiments in which powders were heated to varying temperatures at

different airflow rates (Mishimha,' Schwendiman, and URadasch 1968a) show that the

quantity of radioactive material released varies with the t -empera'tu're of the

surface, velocity of air entrain~ing particles, and characteristics of the

powder (e.g., size distribution and agglomeration tendencies).

A plutonium nitrate solution was dried and the residual solids heated in

other experiments (M ishima, Schwendiman and Radasch 1968b). .Th~e release rate

of radioactive particles from, thi.s .set of experiments varied with temperature

of the surface and velocity of air--.entrai~ni~ng particles but was much les~sfor

all conditions than the powder giving the greatest releases in the powder

experiments.

Because the effect of powder.characteristics such as bulk density,

particle density, moisture content, size distribution, and agglomeration

tendencies on the release rate is difficult to determine from-the data at hand

2.49
and may be difficult to estimate as 'input by the-user of the code, the model

draws on the data from the powder giving the greatest releases at the various

temperatures and flow rates (partially oxidized oxalate). Table 2.7 shows that

the maximum release from different powders differs by one and one half orders

of magnitude and that all releases are less than 1% of the total mass of

material at risk.

Table 2.8 lists the data from which the model for this mechanism is

derived. The best fit of the data shows the mass rate as a function of the

square of the air temperature as shown in the equation below:

mass r'ate (g/s) = (9.85 x 10-8)T2 Wr (2-93)

where T is the temperature of the surface on which contaminant rests, 0C, and

Wr is the total mass of radioactive material, g. T is determined by FIRIN

calculations. FIRIN requires Wr as input.

Particles entrained have a size distribution generally*26% to 68% of that

of their precursor (Mishima, Schwendiman, and Radasch 1968a). The size varies

with the airflow rate and the powder beh avior at high temperatures. Particle

size of'original powders is expected to range from 15 to 50 on MMD; therefore,

airborne particles may range from 3.9 to 34 umn MMD with-a range of 8-to 36 jiný

TABLE 2.7. Characteristics and Range of Releases from Radioactive

Powders Studied

Material

Pu oxalate

Pu 0F4

PuO2

Pu partially'

oxidized oxidate

NuO

Pu(i03(4) air dried

U02

Original Particle Size

50 uim MMD

26 van MMD, 38 an MMD agglomerates

15-44 Pim

32 ian MMD

Range of Releases

(%/h)

0.38 - 0.90*

6.1 x10- - 0.025

0.051 - 0M2

5.3 x 10-6 - 0.024

2 x 10-8 _ 0.12

0.32

15-150 Pim AED

2.*50
TABLE 2.8. Radioactive Releases from Heating. Partially..

Oxidized Pl utoniu .m Oxalate

Release.-

Fraction T emperature Velocity

(%/s) (00m/s) K

1.42E-5 25 10~

1.58E-5 400 100

2.04E-4 700 100

6.94E-5 1000 10

1.72E-4 1000 50

2.28E-4 1000 0

The particle-size distribution shown in Mishima, Schwendiman, and Radasch

(1968a) is used in the code as the probable size~for particles entrained from a

noncombustible contaminated surface in a fire.

2.4.3 Heating of Unpressurized Radioactive Liquids

Radioactive liquids in an open container release a small percentage of

radioactive particles along with vapors when the liquid is heated. This

situation may occur in a nuclear-fuel cycle facility fire. Experiments

designed to study this release mechanism (Mishima,- Schwendiman, and Radasch

1968b) show that three stages can occur during a fi~re, each contributing to the

radioactive source term. These three stages, preboiling, boiling, and heating

of residue, are discussed below. . . ,

2.4.3.1 Preboiling

In the preboiling phase, releases are low; less than 4,x 10O54wt%*is made

airborne over a 1-h period for the greatest release measured (100 cm/s and

90%C). A general increase in source term-generation rate with temperature can

be seen as well as a slight increase with velocity. The equation for the

preboiling phase of heating a liquid'is derived.-from the data in Table 2'.9.,-

The best fit is a polynomial equation showing the release rate as a function of

temperature of the liquid squared:

Preboiling mass rate (g/s) =9.57 x 10-15 T1

2 Wr (2_94)

2.51
TABLE 2.9. Releases from Heating of Unpressurized Radioactive Liquid

Release Liquid Velocity

Rate Temperature of Air

(%/S) (0(cm/s)

1E-11 25 10

1E-11 25 10

2.9E-12 25 50

7.4E-9 90 50

2.3E-13 25 100

1.8E-9 75 100

1.06E-8 .90 100

where TI is the temperature of the liquid, 0C, and Wr is the the total mass of

radioactive material'in the liquid, g. Liquids are assumed to be in the

preboiling phase until they reach a boiling rate of 0.4 mt./min.

2.4.3.2 Boiling

At temperatures greater than 950 to 1000C, nitrate solutions boil. The

amount of contaminant made airborne during the boiling phase depends on the

intensity of the boil, which may be estimated by the boil-off rate. Simmering

liquids with a boil-off rate of 0.4 mk/min give off fewer radioactive particles

than liquids under a vigorous boil,. The equation used to model release rates

from nitrate solutions draws on data measured by Mishima, Schwendiman, and

'Radasch (,1968b) on releases of plutonium nitrate solutions. A linear

regression on the data shown in Table.2..10 provides the relationship between

mass rate and boil-off rate. This equation is given below:

mass rate (g/s) =(5.74 x 10-9 RB -3.42 x 10-9 Wr) (2-95)

where RB is the boil-off rate, m9g/min, and Wr is the total mass of radioactive

material in the liquid, g.

This equation gives a negative release for RB less than 0.6 mx/min. To

correct this, the fraction airborne is assumed to be 5 x 10-10 /s at boiling

rates of 0.4 to 0.6 mx/min. This value was the measured value at 0.6 mx/min in

2.52
TABLE 2.10. Fraction of Radioactive Material Released

from Boiling Liquids (Mishima 1968b)

Boil-off rate wt% Made Time Fraction Released

(m/i)Airborne (min) UIs)

0.5 1.3 x 10-4 150 1.44 x 10-10

0.6 4.5 x 10-4 151 4.97 x100

0.66 5.8 x 10-3 121 7.99 x10

0.73 2.4 x 10-2 124 3.23 x 10 8

0 9 8.4 x 10-2 80 1.75 x 10 -7

1:4(a) 1.8 x i0-1 63 4.76 x 1

(a) Three releases were measured at this boiling rate;

the greatest release fraction is assumed to apply.

the above mentioned experiments. The equation given above is used for boiling

rates greater than 0.6 mx/mmn. RB is calculated internally in the FIRIN code.

Wr is required as input.

2.4.3.3 Heating of Residue

Continued heating of residual material after the liquid has boiled off

will release additional radioactive particles to the air. Mishima, Schwendiman

and Rada~sch (1968b) measured the quantity airborne from this residue at various

temperatures and velocities. A general increase was found in airborne release

with temperature of the surface on which the residue rested, as well as a

slight increase with velocity of airflow. The data are shown in Table 2.11.

The following equation is the best fit of the data and is used in the model:

mass rate (g/s) = (7.37 x 10-12T + 7.51 x 10-11V) Wr (2-90)

where T is the air temperature, 'C, V is the air velocity, cm/s. and Wr is the

mass of radioactive materials, g.

A separate calculation is performed to estimate the radioactive release

from each stage of heating unpressurized liquids. The user must input the Wr

value, which is the original mass of radioactive material in the liquid.

Although the Wr will change slightly as the material boils, this loss is so

minor that it is ignored in following stages. Heat transfer equations within

FIRIN provide the input to decide which source term calculation should be

2.*53
TABLE 2.11. Releases from Heating Residue Following Boiling of

Radioactive Liquids

Release Fraction

(%/s)

1.67E-6

1.28E-6

9.44E-7

1 .67E-5

1 .04E-6

8.89E-7

9.86E-7

T

1000

700

400

1000

700

400

1000

V

(cm/s)

100

100

100

50

50

50

10

applied as well as providing TL for preboiling, the boil-off rate RB for the

boiling stage, and T and V for residue releases. Releases ar 'e assumed to

continue for 2 h after the material has boiled off completely.

2.4.4 Pressurized Releases

Radioactive materials are usually kept in closed vessels in nuclear fuel

cycle facilities. Vessels in the vicinity of a fire may become pressurized

because of the buildup of vapors under temperature increases. When the

difference between the internal pressure of the vessel and pressure of the room

exceeds the vessel integrity, the container will fail, releasing radioactive

materials to the room.

FIRIN requires failure pressure of the ves sel,, quantity of radioactive

material, and certain characteristics of the material to be specified as input.

for this mechanism. The time of failure will be determined by heat transfer

equations within.FIRIN determining the pressure buildup inside the vessel.

Models have been developed to estimate the release of radioactive materials from pressurized-releses (Ayer et al. 1988). A separate computer code

has been created -for determining the source term from pressurized releases

.involving radioactive powders. For simplicity, however, the following regression algorithm is used instead of integrating the PREL code with FIRIN to

obtain a pressurized powder release source term estimate.

F = 1 x 10 (V 0)1. (2-96)

2.*54
where F = fraction of radioactive powder airborne

V0 = initial velocity of powder jetting out of the vessel, mi/s

Velocity can be calculated by

V (2 P V t)1/2 (2-97)

where P =failure pressure, Pa

=t void space in the vessel (vessil volume minus mass of powder!

theoretical powder density), m

m =powder mass, kg

The user inputs failure pressure, vessel volume, powder mass, and theoretical powder density. FIRIN calculates time of failure'and quantity of

release., Airborne particles are assumed to have on AMMD of 11.2 p.m and 'a ag of,

6.

Models for estimating the source term from pressurized releases of radioactive liquids are also given in Ayer et al. (1988). The mole fraction of

pressu'rizing gas is the determining factor in these equations and can be calculated by the methods shownin~n Appendix B'of Ballinger, Sutter,'and Hodgson

(1987). These methods involve using temperature and pressure dependent properties of the pressurizing gas to compute the amount of gas dissolved. In th .e

experiments reported, the hi'ghest quantity released was 8.9% from a fl-ashing

spray of uranine solution. For simplicity, FIRIN 'assumes 10%,of radioactive

liquid.,is made airborne from pressurized release. The AMMD and ag of the

airborne material are assumed to be 7.3 p.m and 3.9, respectively. Failure

pres.sure and mass of radioactive material involved are the only inputs require~d

for this subroutine.

2.4.5 Burning Radioactive Pyrophoric Metal's

Although radioactive materials in nuclear fuel cycle facilities are

primarily in the form of oxides and nitrates, some pyrophoric metals may be

handled. These metals are usually kept in an inert atmosphere and handled with

2.*55
special engineered safety features; however, potential fires involving pyrophoric metals can be taken into consideration with the following model.

Burning plutonium metal rods in airflows of 50 cm/s and temperatures up

to 900%C gave releases of 2.8 x 10-6 to 5.3 x 10-5 wt% airborne (Schwendiman,

Mishima, and Radasch 1968).- Larger pieces of plutonium metal gave off 3.9 x

104to 0.049 wt% maximum when heated Up to 10000C at flow rates of 525'cm/s

(Mishima 1966). Release fractions among the two sets of experiments may be

caused by the difference in si ze of the burning metal pieces, the difference in

flow rates, a combination of these, or other experimental differences.

Table 2.12 lists the data from which the model is derived. The mass rate

is a function of the site of the metal piece squared as shown below.

,mass rate, (g/s) = (1.66 x 10-14 W2)W r (2-98)

where Wr is the total mass of radioactive material, g, and W is the size of the

radioactive metal pieces, g.

FIRIN requires Wr and W as input and assumes the metal burns 'in 1 h.

Although the burning of pyrophoric metals is a two-step process initially

controlled by temperature and, once ignited, controlled by diffusion of oxygen

from the fuel, for simplicity, the above equation assumes uniform release and

complete oxidation of the fuel.

TABLE 2.12. Releases from Burning Radioactive Pyrophoric Metals

Releases Metal

Fraction Size

(%/s) (g) . 5.28E-6 1770

1.25E-6 1000

8.06E-8 4.60

3. 0E- 10 9.9 to 11.3

6.97E-9 9.9 to 11.3

1.18E-8 9.9 to 11.3

4.67E-10 9.9 to 11.3

2.83E-9 9.9 to 11.3

4.42E-10 9.9 to 11.3

2.56
3.0 THE FIRIN COMPUTEtR PROGRAM

.A u~ser of FIRIN c~an estimate the radioactive mass genera~tion rate and size

distributi~on of radioactive particles becoming airborne in a fire.. Thisi-radioactive source term computation is the major project thrust.; however.,,other fire

source terms are also calculated.. These terms-incl~ude ~mass loss'a~nd energy

generation rates,.and compartment transient conditions.,.To perform these est-imations, the user has certai~n information requirements and options availrable.

This chapter provides background information to enable the u~ser to understand

and use the code.

Descriptions. include the following:

* program and data structure of the FIRIN code

e numerical algorithms used in the program

e subroutine functions

* input requirements to run FIRIN

e interpretation of output information

e code limitations.

3.1 PROGRAM STRUCTURE

FIRIN is structured into operational modules shown in Figure 3.1. these

major modules, or blocks, are computations of the following:,

" fire source terms

" heat and mass transfer

" radioactive source terms.

Fire source terms and heat and mass transfer are discussed in this

section; radioactive source terms are composed of seven routines, which are

explained in Section 3.4.

The block identified a's Increment TimeSte'p updates the time. Before this

block (See Figure 3.1), the-program checks if-the updated time exceeded a

specified end time selected by the user for terminating the run.

3.1
YES

2 HEAT & MASS TRANSFER

CONSIDERATION

(COMPARTMENT EFFECTS)Y

(A. 3)

FIGURE 3.1. FIRIN--Overview Flow Chart

Block 1, fire source term computations, is expanded 'in Figure 3.2. 'The

blocks in this figure illustrate determination of the maximum fire duration,

and computation of mass, heat, gas, and smoke generation rates. They provide

input for subsequent blocks. Block 1.1 computes the mass burning rate and

maximum fire duration. This enables computation of heat, gas, and smoke

generation rates in the fire compartment. These factors are summed at the top

of Figure 3.2 and lead to Block 2.

3.2
TO BLOCK-2

1.3 COMPUTE GAS

1.2 COMPUTE HEAT -

GENERATION RATE GENERATION RATES

-1.4 COMPUTE SMOKE

GENERATION RATES

.5

i

S

(A~

1. 1 COMPUTE MASS

BURNING RATE

AND MAXIMUM

FIRE DURATION - -.mTO BLOCK-3

FROM INPUT OR INCREMENT TIME STEP

FIGURE 3.2. BLOCK 1--Fire Source Terms Computation
Block 2, shown in expanded form in Figure 3.3, structures heat and mass

transfer considerations in the compartment. This summation, with input from

Block 1, permits computation of the fire-generated radioactive releases in

Block 3, Figure 3.4. The radioactive source term development is included in

Section 3.4 after the data structure and numerical algorithms are defined;ý

thus, FIRIN is structured in a sequential form to approximate the history of

the mass, both radioactive and nonradioactive, and energy of a fire confined in

a, compartment.

3.2 DATA STRUCTURE

Types of combustible (e.g., paper wipes, solvents) and noncombustible

materials (e.g., stainless steel, concrete) found in the fire compartment will

affect the fire behavior. Data on physical/chemical and pyrolysis/combustion

properties of fuels (combustibles) and physical properties of noncombustibles

are stored in data statements at the beginning of the main program. The materials data format is described in the following section; fire ventilation

conditions are included, since they determine the burning mode. Fuel properties are listed in Appendix B.

3p,2.1 Fuel Material Data

Fuel materials are combustible items normally found in nuclear fuel cycle

facilities. Although they are not the direct cause of the fire, they are

available to sustain the fire once it is initiated; therefore, properties of

these fuel materials must be used to compute the fire source terms. Fuel

materials commnonly found in nuclear fuel cycle facilities are listed in

Table 3.1. Ventilation options are also listed. They have been assigned array

element designations. The array element I is the identifier for 1 through 9,

which represent the combustible materials; element J i s the identifier for

1 through 3, which represent ventilation conditions. Two additional fuels can

be included if the user desires. Combustio n data (listed in Table 3.2) must be

read in for these additional. fuels.

3.4
2.3 COMPUTE H20 & CO2 RELEASES FROM

CONCRETE P-H

2.5 PERFORM MASS

BALANCE IN FIRE

COMPARTMENT

TOE~ T TO BLOCK-3

q a

2.2 COMPUTE HEAT

TRANSFER TO

CONCRETE BOUNDARY

2.4 COMPUTE

COMPARTMENT FLOWS

INIlOUT .I~lLZ

2.6 COMPUTE HEAT

TRANSFER TO

VESSELS AND

EQUIPMENT

S

(I,

I

2.1 PERFORM HEAT

BALANCE IN FIRE

COMPARTMENT

a a

FROM BLOCK-i

FIGURE 3.3. BLOCK 2--Heat and Mass Transfer Considerations

(Compartment Effects)
COMPUTE (RST) FROM

BURNING OF

CONTAMINATED_

COMBUSTIBLE LIQUIDS-

(CALL RST1I)

I

COMPUTE (RST) FROM

BURNING OF

CONTAMINATED

COMBUSTIBLE SOLIDS,

(CALL RST2)'

I

3.3 COMPUT iE (RST),

FROM HEATING OF.

CONTAMI NATED

SURFACES

(CALL RST3)

FROM BLOCK-i

FROM BLOCK-2

AT

RISK

NO

TO T

I

COMPUTE (RST)

FROM HEATING OF

U.NPRESSURIZED.

RADIOACTIVE LIQUIDS

(CALL RST4)

I

K®@

I

A3.5'COMPUTE (RST)

FROM PRESSURIZED

RELEASES OF SOLIDS

(CALL RSTS)

C J

H3.6 COMPUTE (RST)

,FROM PRESSURIZED

RELEASES OF LIQUIDS

(CALL RST6.) H

.7 COMPUTE- (RST)

FROM BURNING OF

Pu OR U METAL

(CALL RST7)

aH

FIGURE 3.4. BLOCK 3--Radioactive Source Terms (RST) Computation

3.6
TABLE 3.1. Fuel Material and Ventilation Conditions for the

Fire Compartments

Ventilation

Fuel Materials (I) Conditions (J)

1 Polymethyl methacrylate 1 Overventilated

2 Polystyrene C[0 2] > 15%)

3 Polyvinyl chloride 2 Semiventilated

4 Polychloroprene ()(11% < [02] < 15%)

5 Cellulose (oak)(a 3 Underventilated

6. Cellulosic material ([02) < 11%)

7 Kerosene

8 User's option

9 User's option

(a) Oak was sel-ected to represent wood products based on the

information available.

Physical/chemical and pyrolysis/combustion properties of the listed fuel

materials are stored in data statements at the beginning of the ma in program.

Most of the information was developed in smal-l- and large-scale combustion

apparatus at Factory Mutual Research Company (Tewarson et al:. 1980; Steciak

et al. 1983).

Variable array names assigned for the physical/chemical and pyrolysis/

combustion properties of fuel materials are listed in Table 3.2. The identification of corresponding properties are included. The actual values for these

variables used in the code are listed in Appendix B.

.Heat flux, for example, can be represented using the information in these

tables. QFC (I,J) with I = 2, J = 1 represents the convective heat flux from a

flame to fuel surface during polystyrene burning under an overventilated

fire. This particular combustion property (if specified) is called within

FIRIN by internal logic whenever the Fire Source Terms Module is in operation.

3.2.2 Construction Material Data

Construction materials in the fire compartment have an effect on the heat

transfer calculations. Construction materials are used for equipment, vessels,

walls, ceilings, and floors in nuc lear fuel cycle facilities. As shown in

3.7
TABLE 3.2. Data Base for Physical/Chemic'al 'and Pyroloysis/Combustion

Properties of Fuel Materials

Variable Array Name in FIR'IN

A. Physical/Chemical Propertie~s

QRR(I); 1 1 to 9

QCHEAT(I)

HEATV(I)

HEATC(I)

WFC(I)

WFH(I)

WFH(I)

WFCL (I)

B. Pyrolysis/Combustion

Properties

QFC(I,-J); 1 1 TO 9,

J .= 1to 3

QFRR(I,J)

XA(IJ)

xC(I,J)

XR(I,J)

YFCO2(I,,J)

YFCO1(I,J)

YFH2O(I,J)

YFHCL(I,J)

YSMOK(IJ).

SOFRA (I)

YFCH4(I,J).e

Property

ýFuel material surface reradiation, kW/m 2

Energy required to genera e combustible

'.vapor air mixture, kJ/mý

Heat required to generate a unit mass

I'of vapor, kJ/g.

Net heat of complete combustion, kJ/g

Weight fraction of carbon in fuel

Weight fraction of hydrogen in fuel

Weight fraction of oxygen in fuel

Weight fraction. of chlorine in fuel

Convect~ive heat 2flux from flame to fuel

surface, kW/m2

Radiative heat Vlux from flame to fu'el

surface, kW/mL

Combustion efficiency

Convective fraction of combustion'

efficiency

Radiative fraction of combustion

.efficiency

Fractional yield of carbon dioxide

.Fractional yield of carbon monoxide'

Fractional yield of water vapor

Fractional yield of hydrochloric acid

Fractional yield of smoke

Soot fraction'in smoke

Fractional yield of methane

Table 3.3, the array element MATER is the identifier from 1 to 15 and

represents a variety of noncombustible materials.

Array names for physical properties' such as material conductivity, emissivity, density, and heat capacity of noncombustible solids are ,listed in

Table 3.4. Material.,th~ermal conductivity of, c~oncrete,,for ,example, is represented by COND. (MATER=1).

'The user must specify MATER in the input data. The array elements 8 to 15

are the user'as option to be used to fill, in material properties for materials.

other than those listed above. If this option is implemented, physical

3.8
TABLE 3.3. Noncombustible Material Options for

the F~ire Compartment

Noncombustibl e

MATER Materials

1 Concrete

2 Fire brick

3ý Stainless steel

4 Steel

5 Aluminum

6 Copper

7 Brass

8 to 15 User's option

TABLE 3.4. Data Base for Physical Properties of Noncombustible

Solid Materials

Variable Array Name

COND (MATER), MATER

CONDM (MATER)

in FIRIN

= 1 TO 15

Physical Property

Material thermal conductivity, kJ/m-s-0K

Linear extrapolation factor(a) of thermal

conductivity

EMIS(MATER)

RHOO (MATER)

CPCA (MATER)

CPCAM( MATER)

Material emissivity

Material density, kg/in3

Material heat capacity, kJ/kg-*K

Linear extrapolation factor(a) of material

,heat capacity

(a) A slope factor 'nterpolated by assuming the physical properties are

linearly proportional to the change in temperature (AT) in compartment

heat balance (i.e., COND = COND ± CONDM x (AT) where CONDM is a linear

extrapolation factor of material thermal conductivity).

properties (listed in Table 3.4) of the material must be input. Appendix B

lists the physical property data used in the code.

3.2.3 Other Data

In addition to the data bases discussed above, there' are a total of 12

other unit files where input and output data for FIRIN are stored. These unit

files are located after the FIRIN data statements, before the input from the

user is read in. Discussion on these unit files is presented in Section 3.5.

3.9
Other data (e.g., the ideal gas constant, gravitatio~nal constant, StefanBoltzmann constant) are required for the calculations. They-are initialized at

the section labeled initialization and parameterization after the input data

has been read in.

3.3 NUMERICAL ALGORITHMS

Thi~s section addresses the three major algorithms used in FIRIN in the

heat-and mass balances. Specific details of the models and equations are found

in Chapter 2.0.

The first algorithm deals with five v ariables: compartment pressure, hotlayer moles and tem perature, and cold-layer moles and temperatures. These

variables are coupled and dependent on the flows i~nto and out of the compartment., Three other first-order differential equations for the hot-layer moles,

hot-layer temperature, and cold-layer moles are solved in simple finite difference form at each time step.. An exact equation for-compartment pressure is

then used, which is a form of the equation of state. This method works well

for suitably small time steps. Larger time steps can cause computational,

instabilities.. A time step of 0.01 to 1.0 s is suggested. The cold-layer

temperature is fixed at the initial value. Since this layer is usually shortlived in forced ventilated fires of the type likely to occur in n uclear fuel

cycle facilities (with cold air entering at the topr and exiting through air

vents at the bottom), the error in'the energy,'balance is small.

The s~econd type of algorithm is the unsteady-state heat transfer to the

walls, floor, and ceiling. The usual second-order conduction equation is

.solved using finite differences and a standard explicit method. The explicit

method was preferred over implicit methods for programmin~g simplicity. This

decision is consistent with the sufficiently small time step needed in the

first algorithm.

The third algor-ithm is the iterative method used to obtain the equilibrium

pressure in~side heated vessels containing solutions. This algorithm assumes a

new temperature inside the vessel with each time step. Then, it calculates

water evaporation and adju sts the heat input between phases or at equilibrium.

The assumption that equilibrium exists is not completely accurate. Some delay

3.10
in readily reaching equilibrium wil'l occur; therefore, the condition calculated

in the vessel does not reflect' this short time delay.

3.4 SUBROUTINE FUNCTIONS

The seven subroutines listed in Table 3.5 are used to calculate the

quantity and characteristics of radioactive particles given off during the

fire. They compose the Radioactive Source Terms (RST) Computation Module

within FIRIN. 'Each subrout~ine predicts the radioactive releases based on one

of these release mechanisms listed in the table. K is the numeric identifier

for subroutines RSTI through RST1 called in the main program..

Figure 3.4 is the breakdown block-diagram of the RST Computation Module,

showing its interdependency with the other two major modules described in

Section 3.1 (Program Structure). Blocks 3.1 to 3.7 in this module call on

subroutines RST1 to RST7 for the predicti-on of mass rate and particle

characteristics from the mechanism listed in each block.

3.5 INPUT AND OUTPUT DATA

Twelve unit files store the data input to and output from FIRIN.

Table 3.6 lists these file names and corresponding types of input and output.

INPUTFILE is a dummy variable for the input file name. The user must read

in the appropriate name immediately after invoking FIRIN. Once the program

reaches completion, the data in all the output unit files are ready to be

printed on the user's request. The user should refer to the 'output file names

shown in the table to call for a printout.

TABLE 3.5. Subroutines for Estimating Radioactive Releases

Subroutine Name (K) Release Mechanism

RSTI 1 Burning of contaminated combustible solids

RST2 2 Burning of contaminated combustible liquids

RST3 3 Heating of contaminated surfa -ce

RST4 4 Heating of unpressurized'radioactive liquids

RST5 5 Pressurized releases of radioactive powdersRST6 6 Pressurized releases of radioactive liquids

RST7 7 Burniing of radioactive pyrophonic metals'

3.11
TABLE 3.6. Unit Files (in FIRIN) for Input and Output Data

Unit File Names Types of Information Stored

Input data for

INPUTFILE(a) -fire source terms computation

-compartment effects computation

-radioactive source terms .computation

Output data from

RSTHL.DAT Change in mass of radioactive particles in hot

layer at each time step. Shows losses by

particle depletion mechanism'

RSTCL.DAT Same as RSTHL, but for cold layer

SMKHL.DAT Same as RSTHL, but for smoke particles

SMKCL.DAT Same as SMKHL but for c~old layer

RSZHL'6DAT Size distribution of radioactive particles in

hot layer at each time step

RSZCL.DAT Same as RSZHL, but for cold layer

SSZHL.DAT Same as RSZHL, but for smoke particles

SSZCL.OAT Same as SSZHL, but for cold layer

PRINT.DAT Fire source term and compartment effects by time

step

ARAD.DAT Buildup of radioactive particles on floor,

walls, ceiling, and vents at each time step

ASMK..DAT Same as ARAD.DAT, but for smoke particles

The following two sections describe the input format and output information to/from FIRIN. Chapter 4.0 gives examples of these by illustrating sample

problem input and output.

3.5.1 Input Format

Various input parameters are required depending on the initial compartment

conditions, amount and types of combustibles, and mechanisms releasing radioactive particles. The input information required to produce a compartment fire

history is listed in Table 3.7. Explanations of the data for each type are

included in the table.

3.12
TABLE 3.7. Input.Data

Card Variable

Type Name Description

1PLUTANS PLOT ANSWER--User specifies 'Y' for FIRIN to store

variables plotting packages. Two new units named

PLOTTING DATA 1.DAT and'PLOTTINGDATA_2.DAT are then

opened and written to during program execution.

1TSPEC COMPUTING TIME--User can specify the duration (in

seconds)*de~sired to observe the fire. The execution of

the program will be termi~nated'at time =TSPEC.

1DELT TIME STEP--User must spec~ify the size of time step (in

seconds) desired for the computation uses in FIRIN. For

stable numerical solution results, small time steps are

suggested (i.e., 1.0 > DELT > 0.01).'

1MIBO BURNING ORDER--One way to approximate fire growth in

FIRIN; users estimate the orders of fuel consumption

(burning order) in the fire if more than one combustible

material in the compartment is assumed to burn. The

maximum number of burning orders is MIBO, and it governs

the numbers of physical card requirement for Card

Types 2 and 3.

1IGNITE IGNITION ENERGY--Another less conservative way to

approximate fire growth in FIRIN is to use the ignition

energy concept. This approximation allows autoignition

of combustibles at risk if the heat-flux levels

generated by the initial burning combusti 'bles in the

compartment-are above a specifie~d level. 'The ignition

energy levels required for autoignition of the

combustibles depend on material properties, and are

stored in the program. To use this concept for

approximation, IGNITE = 1 must be inputted. Otherwise

IGNITE = 0 must be specified. When this concept is

applied, MIBO = 2 must be specified. The first burning

order (IBO = 1) refers to initial burning materials and

(IBO = 2) combustibles at risk because of possible

autoignition are specified.

1IPRINT PRINT--User specifies the number of time steps between

printout into the output unit files. For example, when

DELT = 0.1 is selected and the user wishes to obtain

computed data every 10 s *in 'real time of the fire,

IPRINT = 100 should be specified.

3.13
TABLE 3.7.. ((contd.)

Line

Type

1

Variable

Name

MJE( IE)

Descript ion

EQUIPMENT AT RISK--User can specify up to a total of

10 pieces of equipment and vessels of each of the

following four types: -1) simple heat sink, 2) closed

containers of powder, 3) closed containers of liquid,

and 4) open liquid containers MJE is the number of

each container type. If no equipment or vessel of each

type-is to be modeled:, use 0,0,0;0.

Input data to Fire Source Terms Computation Module

2 FUEL(I,IBO)

1=1,9

IBO=1 ,MIBO

3 AREC(I,IBO)

I=1.9

IBO = 1, MIBO

Mass of combustible material (g) involved in'the fire.

I denotes type of fuel as listed:

I = 1) PMMA

2) PS

3) PVC

4) PC

5) Cellulose -wood

6) Cellulosic materials -paper, cardboard

7) Kerosene

8) User's option

9) User's option

180 is the burn order and denotes the sequence in which

the fuels burn. The maximum burn order is 5. MIBO

physical lines are required, one for each burn order.

0.0 must be input for each combustible material type not

involved in the fire.

Burning surface area (in2) of each fuel involved in the

fire.

Similar to FUEL (I,IBO).

If the User's Option is implemented for FUEL(I,IBO) [FUEL(8 or 9, IBO) greater

than 0.0], combustion properties of the material-must be input as shown in line

types 3a - 3e4 One set of lines is required for each new fuel material.

3a QCHEAT(I)

3a

3a

3a

3a

QRR(I)

HEATV (I)

HEATC(I)

WFC(I)

Energy required to generate combustible vapor-air

mixture (k/m ).

Fuel material surfaces reradiation -(kW/i2)-.

Heat required to generate a unit mass of vapor (kJ/g).

Ne~t'heat of complete combustion (kJ/g).

Weight fraction of carbon in fuel.

3.*14
TABLE 3.7. (contd)

Card Variable

Type Name Description

3a WFH(I) Weight fraction of hydrogen in fuel.

3a WFQ(I) Weight fraction of oxygen in fuel.

3a WFCL(I) Weight fraction of chlorine in fuel.

3b QFC(I,J) Conve~tve heat flux from flame to fuel surfaces

3b QFRR(I,J) Radiative heat flux from flame to fuel surface (kW/m2)

J=1,3

3b XA(I,J) Combustion efficiency.

J=1,3

3c XC(IJ) Convective fraction of combustion efficiency.

J=1,,3

3c XR(I,J) Radiative fraction of combustion efficiency.

J=1,3

3c YFCO (I,J) Fractional yield of carbon dioxide.

J= 4,3

3d YFH O1(I3,J) F ractional yield of water vapor.

3d YFHCL(I,J) Fractional yield of hydrochloric acid.

J=1,3

3d YSMOK(I,J) Fractional yield of smoke.

J=1,3

3e YFCO (1,J) Fractional yield of carbon monoxide.

J "1,3

3e YFCH4(I,J) Fractional yield of methane.

J=1,3

Input data to Compartment Effects Module

4 LR Length of the fire compartment (in).

4 WR Width of the fire compartment (in).

4 ZR Height of the fire compartment (in).

3.15
TABLE 3.7. ,(contd)

Card

Type

4

Variable

Name

XCEIL

XWALL

XFLOOR

Descri ption

4

4

Thickness of the compartment ceiling (in)..

Thickness of the compartment wall (in).

Thickness of the compartment floor (in). If the

compartment -is on the floor level with no other

compartment below it, a large value of XFLOOR is

suggested for heat transfer consideration.

4 MATERC Ceiling construction material. Use the numeric

identifier (MATER =1,2,....15) for noncombustible solid

materials. MATERC =1 (see Table 3.3) denotes concrete

as ceiling material.

4 MATERW

MATERF

Wall construction material. Use the numeric identifier

as above. MATERW = 2 denotes fire break as wall

material.

Floor construction material. Use the numeric identified

as for MATERC and MATERW. MATERF = 1 denotes concrete

as floor material.

4

If a material of construction other than the seven for which FIRIN has data is

input by setting.MATERC, MATERW, and/or MATERF = 8 to 15, card type 4a must be

read in for each new material introduced. Material properties should not be

read in twice.; i.e., if MATERC and MATERF = 8 and MATERW = 9, two cards should

be read in, the first one for material type 8 and the second for material type

9.

4a COND(MATER)

4a CONDM( MATER)

4a EMIS(MATER)

4a EMISM( MATER)

4a. .HOO( MATER),

4a RHOOM( MATER)

4a CPCA(MATE)

Material thermal conductivity (kJ/m-s.0 K).

Liner extrapolation factor of thermal conductivity (see

Table 3.4).

Material emissivity.

Linear extrapolation factor of material emissivity (see

ýTabl e 3.4) .

Material Idensity (kg/in3).

Linear extrapolation factor of material density (see

Table 3.4)..

Material heat capacity (kJ/kg0K).

3.16
TA~BLE 3.7. (contd)

Line Variable

Type Name - Descri ption

4a CPCAM(MATER) Linear extrapolation factor of material heat capacity

(see Table 3.4).

51 NFP Number of additional flow paths to/from the fire

compartment. A glove box is an example of a compartment

that has glove ports as its additional flow paths where

-the gloves attached to it have burned off. As many as

20 paths can be designated in FIRIN. The value selected

for NFP governs the number of physical line requirements

for Line Types 28 through 31. If NFP = 0, no data input

is required for these line types.

5 P1 Initial pressure (atm) at the outside of the inlet

ventilation. Usually P1 =1.0.

5 P2 Initial pressure (atm) at the outside of the outlet

ventilation.

5 TINIT Initial temperature (*K) of the fire compartment.

5 PINIT Initial pressure (atm) inside the fire compartment.

5 ZIF Height of elevation of the-center plane of inlet

ventilator from the floor level in the compartment-.

5- ZOF Height of elevation of the center plane-of outlet

ventilator from the floor-level in the compartment.-..

5 ZFIRE Normalized height of the flame base above floor level

(in). For'example when a glove box is in a fire, ZFIRE

is the elevation of the glove box floor.

5 VIF Initial volumetric inlet flow rate to fire compartment

(m Is).

5 EQUIP Numeric identifier for equipment and for vessels at risk

in the fire compartment.

EQUIP = 1.0 (equipment and/or vessels)

EQUIP = 0.0 (no equipment or vessels)

If EQUIP = 0.0 is specified,, no input data are required

for Line Types 8 through 28.

5 EFFIC Initial efficiency of in let and outlet filters,

fraction.

3.17
TABLE 3.7.(ond (contd)

Line

Type

6

Variable

Name

TFO

6

6

6

6

7

TCO

TWO

N2X2IF

N2X2OF

NBO(I)

Descri ption

Initial floor temperature, *K.

Initial ceiling temperature, *K.

Initial wall temperature, *K.

Size of inlet filter in terms-of multiples of 2' x 2'.

Size of outlet filter in terms of multiples of 2' x 2'.

Numeric Identifier for the nine combustibles at risk.

This line type is required only when ignition energy

concept is applied (or IGNITE = 1).

Input NBO(I) = 0 for material that burns initially in

the fire.

NBO(I) = 1 for combustibles that are at risk and

that can contribute to the fire via

ignition energy concept

NBO(I) = 2 for any of the nine combustible types

that will not contribute to the fire at

all

NBO(IM 3 for material types that burn at the

start of the fire and are also at risk

because of ignition energy concept.

simple heat sink.

if there are no Type 1 vessels or equipment

Input to Equipment

Lines 8-13 are not

(MJE(1)=O).

Type 1:

requi red

8 WD(JE,1)

J E =1, MJ E(1)

9 HEQ(JE,1)

JE=1 ,MJE(1)

10 HTF(JE,l)

JE=1, (MJE,(1)

11 MATERE(JE,1)

JE=1,MJE(l)

Width of equipment and/or vessels (in). JE denotes

number of each vessel or area of equipment up to 10.

Length of equipment or vessels,(in). Height of

cylinders, length of boxes or square vessels. This

parameter used with WD to find area exposed to fire for

heat transfer.

Height of the base of equipment or vessels (in).

Material of construction of equipment or vessel. FIRIN

contains data for seven types as listed in Table 3.3.

If the User's Option is implemented by setting MATERE=8

to 15, physical properties of the material must be input

as shown by line type 4a.

3.18
TABLE 3.7. .(contd)

Line Variable

Type Name Description

One line type, 4a, is required here for each new material introduced by

MATERE(JE,1) > 7. Material properties should not be repeated. For example, if

MATERC=8, then properties for type 8 material has been read and should not be

input again.

12 WMASS(JE,1) Weight (kg).of equipment or vessel when empty.

JE=1 ,MJE(1),

13 TE1(JE) Initial surface temperatures (*K) of equipment or

JE=1, MJE(1) vessels.

Input to'Equipment Type 2: closed containers of powder.

Lines 14 -24 are not requ~ired if there are no type 2 vessels (MJE(2)=O).

14 WD(JE,2) Same as line 8.

J E =1,MJ E(2)

15 HEQ(JE,2); Same as line 9.

JE=1, MJE(2)

16 HTF(JE92) Same as line 10.

JE=1, MJE(2)

17 MATERE(JE,2) Same as line 11.

JE=1, MJE(2)

18 WMASS(JE,2) Same as line 12.

JE-1, MJE(2)

19 VGAS2(JE) Gas volume (m3) inside vessel.

JE=1, MJE(2)

20 VPWD(JE) Volume of powder (m3) inside vessel.

JE=1, MJE(2)

21 WH202(JE) Mass of water (g) inside vessel. This value can be

JE=1, MJE(2) obtained using the moisture content-of the powder.

22 TE2(JE) Initial surface temperature (*K) of vessel.

J E-1 ,MJ E(2)

23 T12(JE) Initial i~nside temperature (OK) of vessel.

J-E,=1, MJE(2)

24 PF2(JE) Failure or rupture pressure,(atm)'of vessel.

JE=1, MJE(2)

3'.19
TABLE 3.7. (contd)

Line Variable

Type Name Description

Input to Equipment Type 3: closed containers of liquid..

Lines 25 - 34 are not required if there are no type 3 vessels (MJE(3)=0).

25 WD(JE,3) Same as line 7.

JE=l, MJE(3)

26 HEQ(JE,3) Same as line 8.

JE=l, MJE(3)

27 HTF(JE,3) Same as line 9.

JE=1, MJE(3)

28 MATERE(JE,3) Same as line 10.

JE=1, MJE(3)

29 WMASS(JE,3) Same as line 11.

JE=1, MJE(3)

30 VGAS3(JE) Volume of gas (in3 ) inside vessel.

JE=1, MJE(3)

31 WH203(JE) Mass of liqui~d (g) inside vessel.

JE=1, MJE(3)

32 TE3(JE) Initial surface temperature (OK) of vessel.

'JE =1 ,MJ E(3)

33 T13(JE) Initial inside temperature (0K) of vessel.

JE=1, MJE(3)

34 PF3(JE) Failure or rupture pressure of vessel.

JE=1, MJE(3)

-Input to Equipment Type 4: open containers of liquid.

Lines 35 - 42 are not required if there are no type 4 vessels (MJE(4)=0)..

35 WD(JE,4) Same as line 7.

JE=1, MJE(4)

36 HEQ(OE,4) Same as line 8.

JE=1, MJE(4)

37 HTF(JE,4) Same as line 9.

JE=1, MJE(4)

3.*20
TABLE 3.7.(cnd (contd)

Line Variable

Type Name

38 MATERE(JE,4)

JE=1, MJE(4)

39 WMASS(JE,4).

JE=l, MJE(4)

40 VOL(JE)

JE=l, MJE(4)

41 TE4(JE)

JE=1, MJE(4)

42 TL(JE)

JE=l, MJE(4)

Description

Same as line 10.

Same as line 11.

Liquid volume (m3) inside vessel.

Initial surface temperature (0K) of vessel.

Initial liquid temperature (*K) of ves~sel.

Input for alternate flow paths. Lines 43 - 46 are not required if NFP = 0.

43

44

45

46

TFP(IFP)

IFP=1 ,NFP

HFP(IFP)

IFP=1 ,NFP

PFP(IFP)

IFP=1 ,NFP

DFP(IFP)

IFP=1 ,NFP

Failure times (in seconds) of the additional flow paths

to the fire compartment during the course of the fire.

The total of NFP = 20 additional flow paths are

currently allowed input to FIRIN.

Height of the additional flow paths (m)..

Pressure (atm) at the outlets of the additional flow

paths to the compartment.

Equivalent diameters (in) of the additional flow paths t o

the compartment.

Input data to RST Computation Module

47 NRAD(K) Number of radioactive source terms that will be

K=1,7 generated under the Kth type of release mechanism. K is

the numeric identifier for the total of seven types of

radioactive release mechanisms described in Section 3.4.

Provide a total of seven values including zeros if the

mechanism is not involved. Thus, NRAD(1) = 2 denotes

that there are 2 radioactive source terms resulting from

burning two types of contaminated combustible solids.

The values specified for NRAD(J) are the numbers of

physical lines required for Line Types 48 through 56.

3.21
TA~BLE 3.7.(cnd (contd)

Li ne

Type

48

48

48

48

Variable

Name

IFORM

I

J ACT

lB 0

QRAD1

IFORM

Descri pti on

Line Types 48 and 49 are use~d for radioactive releases

from the burning of contaminated combustible solids.

The number of physical lines required for input depends

on the NRAD(1) value specified in Line Type 47. If

NRAD(1) = 0, no input data is required of Line Type 48.

IFORM here denotes the physical form of radioactive

contaminant found on the combustible solid:

IFORM = 1 (powder)

-IFORM = 2 (air-dried

liquid)

IFORM = 3 (liquid)

I is the numeric identified for the types of combustible

materials the radioactive material is associated with,

where I = 1, 9. See Section 3.2 for the combustible

materials and their corresponding numeric identifier.

JACT can be any integer, ranging from 1 to 10, assigned

to a source term for identification among other possible

source terms in a single fire scenario. Up to 20 radioactive species can be tracked.

IBO is the burning order of the contaminated combustible

solids. See descriptions for Line Types 2 and 3.

QRAD1 is the estimated total mass of radioactive material. NOTE:. If NRAD(1) is greater than 1, Lines 48 and

49 must be repeated in alternating fashion NRAD(1) times.

Line Type 50 and 51 are used for radioactive releases

from burning of contaminated combustible liquids. The

number of physical lines required for input depends on

the NRAD(2) value specified in Line Type 47. If

NRAD(2)=0, no input data i~s required of Line Type 50.

IFORM here denotes the forms of radioactive contaminant

in combustible liquids:

IFORM 1 (uranium or plutonium powder)

IFORM =2 (uranium or plutonium liquid)

IFORM =3 [nonvolatile radioisotopes other than

uranium or plutonium (e-eg., zirconium,

cerium)]

IFORM =4 [semivolatil .e radioisotopes (e.g.,

cesium)]

IFORM =5 [volatile radioisotopes, e.g., iodine)].

Same description as I above in Line Type 48.

49

50

50

3.22
TABLE 3.7. (contd)

Variable

Name

JACT

I BO

QRAD2

JACT

QRAD3

IVES

JACT

QRAD4

I VES

JACT

QRAD5

VOLP

POEN

Descri ption

Same description as JACT above in Line Type 48.

Same description as IBO above in Line Type 48.

QRAD2 is the estimated total mass (g) of radioactive

material. If NRAD(2) is greater than 11, lines 50 and 57

must be repeated in alternating fashion NRAD(2) times.

Line Type 52 is used for radioactive releases from

heating of contaminated surfaces. The number of

physical lines required depends on the NRAD(3) value

specified in Line Type 47. If NRAD(3)=0, no input data

is required of Line'Type 52.

Mass ()of radioactive material on the surface heated

by the fire.

Line Type 53 is used for radioactive releases from

heating of unpressurized radioactive liquids. NRAD(4)

physical lines must be input. IVES is a number from 1

to 10 identifying up to 10 vessels of radioactive

liquid. IVES is the same as JE for equipment type 4

(see lines 35 - 42).

Same description as JACT above in Line Type 48.

Mass"(g) of radioactive material in the liquid. Similar

input requirement as for QRAD3.

Line Type 54 is used for, radioactive releas~es from

pressurized releases of solids'. NRAD(5) physical lines

must be input'. 'Same description as IVES above in Line

Type 53 but with'powder. IVES is the same as JE for

Equipment Type 2 (see Lines 14 -24).

Same description as JACT above in Line Type 48.

Mass (g) of rad ioactive powder in the vessel. Similar

input requirement as for QRAD3.

Volume of powder container, inm

Theoretic density of radioactive powder, g/m3

3.*23
TABLE 3.7. (contd)

Line

Type,

55

55

55

56

56

56

56

Variable

Name

IVES

JACT

QRAD.6

JACT

INB

QRAD7

SQ

Description

Line Type 55 is used for radioactive releases from

pressurized releases of liquids,. NRAD(6), physical lines

must be input. Same description as IVES above in Line

Type 53. IVES is the same as JE for Equipment Type 3

(see Lines 25 - 34).

Same description as JACT above in Line Type 48..

Mass (g) of radioactive liquid-in the vessel. Similar

input requirement as for QRAD3.

Line Type 56 is used for radioactive releases from burning pyrophoric metals. NRAD(7) physical lines must be

input. Same description as JACT above 'in Line Type 48-.

Same description as IBO above in Line Type 47.

Mass (g) of metal burned. Similar input requirement as

for QRAD3.

Size of radioactive metal (g) that are burned.

Line Type 1 - 3. These lines provide input data to the Fire Source Terms

Computation Module. A minimum of one physical line of each type is required to

run FIRIN. More than one of each can be used as input when appropriate.

Line Types 4 - 42. These lines provide input data to the Compartment

Effects Module. One physical line of Line Types 4, 5, and 6 is required. Line

Type 7 is required if an ignition energy concept is chosen to approximate fi~re

growth. Line Types 8 through 42 are required if equipment is modeled in the

fire compartment.

Line Types 43 -46. These lines are not required as an input unless there

are additional flow paths besides normal ventilation. One or more physical

'lines of each of-these types are used when required.

Line Types 47 --56. These lines input data to the RST Computation Model.

One physical line of Line Type 47 is required; additional lines can be used as

input when appropriate.

3.*24
Before using FIRIN, the user should review the input data requirements in

Table 3.7. For a simple fire (i.e., a compartment with a few combustibles and,

limited quantities of radioactive materials at risk), less than 20 physical

lines are required to run FIRIN. The s~implest c ase with radioactive material

requires only 8 lines. With the addition of equipment, vessels, and flow paths

to the fire compart ment, the analysis sophistication increases and more lines

are required.

3.5.2 Output Information

FIRIN can be used indepen'dently'as a source term code; however, it has

been designed to fill the input requirements of FIRAC. With the use of both

codes, a user can analyze the radioactive s~ource terms up to the facilityatmosphere interface.

Several unit files store the time history output from FIRIN., Output

information includes transient data on the 1) fire source term, 2) fire

compartment, 3) accumulation on filters, and 4) radioactive source term.

Frequency of data output printing is specified by the user in input for

IPRINT. For example, in a fire lasting 500 s (based on quantity of combustible

materials and fire compartment conditions) with IPRINT=1O and DELT =1, 50

outputs (1 every 10 s) would be printed.

Output is termi~nated at thleend of a specified time noted by the following

remark at the bottom of the output table:

TIME EXCEEDS USER SPECIFIED TIME AT . SEC

Other messages can be found in the output files. The following message

occurs when combustibles have auto ignited:

COMBUSTIBLE TYPE X HAS IGNITED AT TIME: ... SEC

3.*25
If the fire becomes oxygen depleted before all the combustibles have finished

burning, the following message will be printed:

ALL BURNING HAS STOPPED AT TIME: ... SEC WITH X% OF ALL

COMBUSTIBLES CONSUMED IN THIS FIRE

The message

ALL COM~BUSTIBLE MATERIALS WERE CONSUMED BY ... SEC

appears after the time step in the last combustible is burned up. The program

will keep running after this until it reaches the user specified time. In this

way the transport of particles to surfaces and the vents as well as depletion

of particles can be followed after the fire goes out.

Information given in the various output files are summarized in Table 3.8.

TABLE 3.8. Parameters in Output Files

File

RSTHL and SMKHL

Parameters

Time, s

Airborne at To, g

+ Generated by Fire, g

+ Entrashed w Plume, g -Total Losses, g -Airborne at T

'hot layer mass balance

Sover time step

Fraction of Losses Due to:

Settl ing

Browman Diffusion

Thermophoresi s

Di ffusi ophoresi 5

Out Vent

breaks down contribution

of losses from each particle

depletion mechanism

RSTCH and SMKCL Time, s

Airborne at To, g

+ Hot Layer Settling -Total Losses, g -Airborne at.T

cold layer mass balance

over time step

3.26
TABLE 3.8.(cnd (contd)

File Parameters

Fraction of Losses Due to:

Settling

Out Vent

Plume Gas

RSZHL, RSZCL,

SSZHL, SSZCL

Particle Diameter (microns) for Bins

>001

0.1-0.3

0:3-0.5

0.5-0.7

0.7-0.9

0.9-1.1

1.1-2

2-6

6-10

10-20

>20

Time, s

0.1

0.173

0.387

0.592

0.794

-0.995

1.480

3.460

7.750

14. 140

20.00

,bin size and geometric

average of sizes

PR INT

Compartment Pressure, atm

Oxygen Concentration, volume fraction

Hot Layer Thickness m

VolumtricInle, m3

Volumetric Intlet, m /

Hot Layer Temperature, OF

Mass Burn Rate, g/s

Heat Generated by Fire, kW

Heat Loss to Wa~lls,- kW

Heat to Fire Gas, kW

ARAD, ASMK Time, s

Accumulated Mass (g) on:

Floor

Wall1

Ceiling

Vents

Envi ronment

3.27
3.6 PROGRAM LIMITATIONS

FIRIN was not programmed to mechanistically calc ulate fire growth. An

approximation of fire growth can be made using the concept of burning order.

The user decides in what order combustibles burn or whether they burn

simultaneously and inputs the burn order in the FUEL and AREC arrays (see

Table 3.7).

Because the calculations for many of the compartment effects were approximations, instabilities may occur in the output if too large a time step is

chosen. For smaller fires, time steps of 1 or 2 s may be adequate. Larger

fires require time steps of less than 1 s to avoid instabilities.

To determine the optimum time step (largest time step that will not result

in instabilities), the user can run several small test cases varying the time

step and analyzing compartment pressure over short time intervals. First the

user should try to determine where maximum burning that occurs in the postulated fire, then assign the identified fuels a burn order of one. The first

100 s of the fire can be run with time steps ranging from 0.01 to 5. From

.PRINT.DAT a person can obtain data on compartment pressure and plot this

parameter against time. The optimum time step will be the largest one

resulting in minimal pressure fluctuations.

Radioactive source term equations are based on empirical correlations of

the current available data.. Little attempt has been made to produce equations

based on first principal theories because of the lack of data on radioactive

aerosols produced in a fire. However, the most recent experiments at PNL have

explored the mechanistic effects of various parameters on radioactive source

terms, and equations based on these latest experiments have been included.

3.6.1 Cautions

.The FIRIN code was developed without the benefit of complete structured

programming techniques. Other than providing subroutines for the radioactive

source term mechanisms of release and for particle depletion mechanisms, very

little compartmentalization was used. The user must be extremely careful in

3.*28
making code changes. Since temperature, pressure, and fluid flow parameters

are all interrelated, a change in one area of the code may affect many other

areas.

At the time of this publication, FIRIN has not undergone any formal verification. Informal comparisons have been made comparing FIRIN output against

other codes in simulating compartment fire experiments. The radioactive source

term part of FIRIN has not even been informally verified against experiments

independent of those from which it was developed.

3.29

4.0 SAMPLE PROBLEMS

Sample problems are presented in this chapter to illustrate the use of

FIRIN. Input files and selected output are shown for a basic problem

(problem one) and for variations of the basic scenario (problems two - five).

A listing of the FIRIN code is given in Appendix C. This version of the code

was used to run all the sample problems described in this chapter. Appendix D

is a listing of the parameters used in the main FIRIN code, their definition,

and units.

4.1 BASIC SCENARIO

A glove box made of PMMA containing PVC bagging material, paper wipes,

solvent, and rubber gloves is located in a concrete room. Room dimensions are

21 m x 9 m x 4 m; the ceiling and walls are 0.25 m thick; and the floor is

0.15 m thick. Each of the combustibles is assumed to be contaminated with

plutonium dioxide powder. The glove box is elevated 0.61 m above the floor.

Airflows through the room at the rate of 1.5 m3/s or seven air changes per hour

and in a downward direction from the ceiling to the floor. An inlet vent is

located at ceiling level and outlet vent at floor level. Each vent is a 2-in.

x 2-in, filter with efficiency of 99.95%. The change in pressure across inlet

and outlet filters is 0.005 atm. Initial temperatures of the air and surface

are 298 *K. Initial pressure in the room is 0.995 atm.

4.2 PROBLEM ONE

In the first sample problem, the PVC, paper, and solvent are assumed to

burn first. The fire spreads to include PMMA and rubber gloves. (PVC, paper,.

and solvent are given a burn order of one; PMMA and rubber gloves are given a

burn order of two). Table 4.1 lists the combustibles, the-quantity involved inthe fire, their burning surface area, and level of contamination.

In addition to the contaminated combustibles, the floor of the glove box

is contaminated with 15-g PuO2, thus involving another radioactive source

term: heating of contaminated surfaces. Table 4.2a shows the input parameters

4.1
Table 4.1. Combustibles for Sample Problems

Type Quantity (g) -Surface Area (mWj Con Itaminants (g PuO21

PMMA. 40,860 3.6 .27

PVC 454 0.09 1

PC 4,540 2.0 75

Paper 227 0.09 1

.Solvent 910 0.3 2

and values required to run this sample problem. 'JACT was used in this problem

to identify the source term' from each, burning material. .In other problems the

user may wish to ide'nti~fy contaminants with different decay-levels or physical

forms. In problem four JACT is used to identify the source term from radioactive po .wder as opposed to that from radioactive'liquid.

FIRIN echoes the input to aCRT screen if the user is running the problem

interactively-, or to the log file if the user is running the program in batch

mode. The echoi ng output aids the user to see if the input values were read in

correctly. Output files produced in running FIRIN are described in Table 3.6.

Appendix D contains all output files from this sample problem except the plotting data bases. Plotting data bases contain the same data as are in some of

the other files but in a form that i's m ore easily read by plotting programs.

The output, file PRINT.DAT con tains data on burn rates, energy generation

rates, and conditions in the first compartment. Table 4.2b shows PRINT.DAT for

the first sample problem. The increase in mass burn rate at 300 s pinpoints

the start of the second burn order. The large amount of combustion gases produced in-this time step overpressurize the compartment, and air is blown out

the inlet vent until the flow becomes positive again at 420 s. The hot layer

completely descends at 340 s. About the same time, oxygen concentration

decreases rapidly but stays slightly above 11%, which is considered the limit

below which a-fire is smothered.

4.2
TABLE 4.2a. 'Inputfor Proble-m One,-,

PLOTANS, -TSPEC, DELT, MIBO,'IGNITE, IPRINT, MJE(1), MJE(2), MJE(3), 4MJE(4)

'Y', 1000.0, 2.0, 2, 0,1 10, 0, 0, 0,) 0

FUEL(1,1), FUEL(2,1), FUEL(3,I), FUEL(4,1) ... 0.0, 0.0, 454.0, 0.0, 0.0, 227.0, 910.0, 0.0, 0.,0

FUEL(1,2), FUEL(2,2), FUEL(3,2), FUEL(4,2) ... 40860.0,) 0.0, 0.0, 4.540.0, 0.0, 0.0., 0.0, 0.0, 0.0.

AREC(1,l), AREC(2,1), AREC(3,I), AREC(4,1) ... 0. ,00,..'; 0.0, - 0.0, 0.09, 0.0, 0.0, 0.09, .0 00 . AREC(1,2), AREC(2,2), AREC(3,2), AREC(4,2)...

3.6, 0.0, 0.0, 2.0, 0.0, 0.0, 0.0, '0.0, 0.0

LR, WR, ZR, XCEIL, XNALL, XFLOOR, MATERC, MATERW, MATERF

21.0, 9.0, 4.0, 0.25,, 0.25, 0. 15, 1, 11

NFP, PI, P2, TINIT, PINIT, ZIF, ZOF, HFIRE, VIF, EQUIP, EFFIC

0, 1'.0, -0.990 298.0, 0.995 4.0,'0.:0, 0ý.61,' 1._5; `0.0, ý:0.9995.

IFO,, TCO, . TWO, ,;N2X2IFN2XOF-..

298.0, 298.0, 298.0,

NRAD(l),'NRAD(2), NRAD(3),

.4, 1, .1,

IFORM, I, JACT, IBO

1, 3, 3, 1

I i

NRAD(4)', NRAD(5),

0,' 0.,

NRAD(6).,

0,

NRAD(7)

0

Q RADI

1.0

IFORM, I, JACT,

1, 6, 6,

QRAD1_

1.0

IFORM, I, JACT,

1',1, 1

Q RAD 1

27.0

.IFORM, I, JACT,

1, 4, 4,

QRAD1.

75.0

IFbRM, I, JACT,

1, 7, 7,

QRAD2

2.10

JACT, QRAD3.

8), 15.0O

I BO

I B

2

I BO

2

I BO

4.3
TABLE 4.2b. PRINT.DAT from Problem One

OUTPUT FOR COMPARTMENT EFFECTS

COMPARTMENT OXYGEN HOT LAYER VOLUMETRIC FLOW RATE HOT LAYER MASS BURN HEAT GEN. HEAT LOSS NEAT TO TIME PRESSURE CONC. THICKNESS INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS (SEC) (ATM) (VOL FRACT) (U (U..3/S) (Mi.31) (F) (G/S KW) (KW) K1W

*.s 95~ 1.10 6.800 :1ee -so"6 76.4060 0..6 so66" 0.66.6066 2.0"s .9"95, .2 1606 6.46:32 2.3815 -1.6186 115. 3006 1 ,6.429 359.7645 -344.5267 15.2378 40.00 0.9953 0.2100 0.7 28 1.3986 -1.6634 112.2788 10.S414 359.7131 -334.4408 25.2722 60.06 0.9953 6.2100 2.1342 1.4002 -1.5998 111.9967 106.462 359.8726 -326.0634 33.6382 86.66 0.9953 0.2100 1.4399 1.4063 -1.6997 112.5872 16.5392 359.6376 -319.43742 40.2060 106.00 0.9954 6.2100 1.7348 1.3921 -1.6079 113.5621 10.5382 359.6662 -313.7714 45.8348 1226.06 0.9956 6.2106 2.6668 2.3317 -1.6683 112.1149 2.4368 21.3988 -36.0367 -14-.6481 146.06 0.9949 0.2100 2.1883 1.5156 -1.4844 108.0633 2.4313 21.3928 -35.8402 -14.4474 160.06 0.9949 8.2100 2.3644 1.5158 -1.4842 164.7199 2.4314 21.3944 -34.5921 -1E'1978 186.66 6.9949 0.2100 2.5359 1.5156 -1.48560 161.9597 2.4315 21.3953 -33.1885 -11.7932 266.66 0.9956 0.2100 2.7363 1.5139 -1.4861 99.6523 2.4316 21.3959 -31.8256 -16.4291 226.60 0.9956 0.2100 2.86690 1.5120 -1.4886 97.7054 2.4317 .21.3984 -3065638 -9.1674 240.00 0.9"SO 6.2106 3.0347 1.5104 -1.4089 96.0493 2.4317 21.8908 -29.4319 .- 8;0361 .260.06 0.9949 6.2100 3.1996 1.5249 -1.4751 94.4550 1.5367 6.7864 -23.3766 -14.5896- .286.06 0.9949 0.2100 3.3578 1.5187 -1.4613 92.8679 1.5367 6.7865 -21.9379 -23.1514 306.60 1.6689 .0.2646 3.5204 -2.6842 -5.6842 106.1561 162.9438 3611.3425 -1803.8683 2207.4742 326.60 1.0012 0.1983 8.8534 -6.33560 -3.3513 166.8976 193.5692 3023.8186 -21867.4659 1136.4127 346.66 1.0084 6.1917 4.6666 -1.9335 -3.5355 244.6716 156.0263 2873.3374 -894.4583 1978.8792 366.00 1.0162 0.1843 4.66660 -1.5296 -2.2880 333.2971 162.2772 2993.6435 -1702.0634 12296.6681 386.66 1.6616 0.1767 4.6666 -6.1186 -6.8657 376.4951 162.0798 2418.6659 -2131.2954 266.7765 400.60 1.6661 6.1693 4.e066 -6.6864 -6.6899 391.8969 162.8818 2432.3267 -2222.4307 269.8990 .426.66 6. 99a 6.1616 4.6666 6.0469 -6.5935 468.35660 63.0673 2441.9312 -2279.1914 162.7397 440.00 6.999 6.1544 4.6666 6.0.613 -6.5324 412.2046 103.'3489 2448.1277 -2312.1697 135.9586 466.66 6.9984 0.1476 4.6666 6.1823 -6.4379 417.3647 166.1799 2304.3577 -2318.2805 '-13.9229 486.00 0.9948 0.1426 4.6666 .6.976 -6.2393 462.8662 91. 1003 1943.5426 -2165.7485 -162.2659 566.660 0.9945 0.1377 4.6666 0.6326 -6.2166 383.6743 83.9528 1690.6646 -1853.5145 -262.91065 526.06 0.9948 0.1344 4.6666 10.6669 -6.2215 368.3522 78.69660 1496.5461 -1642.6213 -246.0672 546.06 6.9951 6.1317 4.6666 6.56637 -4.2272 351.2458 73.2433 1341.2565 -1470.7566 -129.5001 566.66 6.9954 0.1293 4.666 065293 -4.2305 338.0436 66.6902 1213.8297 -1329.1627 -115.2726 5660.66 0.9957 0.1272 4.666 6.4982 -6.2313 326.4149 86.1799 1167.2998 -1216.6145 -;163.3147 666.66 6.9959 6.1253 4.666 6.4703 -6.2362 316.6646: 61.9039 1616.8616 -2116.1426 -93.2800 626.06 0.9962 0.1238 4.6666 0.44560 -6.2274 366.8351 58.9619 939.6893 -2623.9113 -84.8220 646.66 0.9964 6.1221 4.6666 6.4226 -6.2235 298.4929 56.3526 871.4666 -949.1132 -77.6532 666.66 19.9965 6.1207 4.6666 6.4611 -6.2187 296.9198 53.9684 612.69829 -883.6264 -71.5375 686.66 0.9967 0.1194 4.6666 6.3818 -6.2133 284.6635 51.7922 759.5112 -825.7933 -86.2821 706.66 6.9969 6.1182 4.06666 6.3641 -6.2067 277.6532 49.7946 712.6261 -774.3571 -61.7376 726.66 6.9976 0.1171 4.6666 6.3477 -6.2015 271.7943 47.9497 6706.226 -728.3066 -57.7785 746.06 0.9971 6.1161 4.6666 0.3328 -6.1955 266.3646- 46.2397 632.5688 -686.8126 -54.3632 766.06 0.9972 6.1151 4.6666 0.3185 -6.1894 261.3131 44.8478 .596.6668 -649.2415 -51.2346 786.06 6.9974 6.1142 4.6666 6.3654 -6.1634 256.5963 43.1663 566.5473 -615.6513 -48.5606 800.00 0.9975 6.1134 4.06666 6.2932 -0.1775 252.1777 41.7659 537.7449 -583.6648 .- 46.65"9 826.66 0.9976 6.1126 4.6666 0.2818 -6.1718 248.6261 40.45560 511.2757 -555.1332 -43.8575 846.06 0.9977 6.1119 4.6666 6.2711 -0.1262 244.2151 39.2194 466.8686 -528.7316 -41.8636 866.66 6.9977 6.1111 4.6666 0.2611 -6.1669 246.4213 38.0519 464.2953 -564.3385 -46.6432 88066.6 0.9978 0.1105 4.6660 6.2517 -6.1557 236.9252 36.9484 443.356" -481.7365 Zc3 8 .

3 7 89

ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 896.666 SEC

966.66 0.9969 6.2114 4.666 1.6516 -0.6177 222.6959 6.66660 0.666 -392.3763 -392.3763 926.60 0.9924 6.1146 4.06666 6.8778 -6.6462 261.6863 6.6666 9.666 -258.5367 -258.5367 946.66 6.9943 6.1169 '4.00w6 6.6606 -6.6807 188.1795 6.6666 0.6666 -183.4765 -283.4765 966.06 6.9954 6.1186 4.666 0.5269 -6.6999 178.5825 6.6666 6.666 -237.2334 -137.2334 986.66 6.9962 6.1199 4.6666 6.4391 -6.1107 171.3725 0.6666 6.666 -106.6377 -106.6377 1666.60 0.9967 6.1211 4.6666 6.3776 -0.1168 165.7341 6.6666 0.6060 -85.3472 -85.3472
4.3 PROBLEM TWO - ONE BURN ORDER

.The second, sample problem is similar to the first except that all combustible materi Ials, the PVC, paper, sol Vent", PMMA, !and rubber glb'ves, areassumed to start burning at the same time. Each combustible is given a burn

order of one. Table 4.3a shows'the'i-nput 'pa~rameters',And val'ues required for

this sample problem. The -time, step -was, reduced to 1 st to avoid instability

problems in airflow.

TABLE, 4-.3a. Input for .P roble im: Two

PLOTANS, ISPEC, DELT, MIBO, IGNITE, IPRINT,, MJE(1), .MJE(2),, MJE(3),, MJE(4)

'Y,1000.-0, '1.0, 1, 0 , 2 0,' 0, 0, 0, 0

FUEL(l, 1) , FUEL (2,:1.):-',FUEL (3 1),. FUEL:(4, ).

40860.0, 0.0, 454.0, 4540.0, 0.0, 221.0, 910.0, 0.0, 0.0

AREC(1,1), AREC(2,1)., AREC(3,1), AREC(4,1).

3.6; . 0.0, .0.,09' ;2. 0.00.09, 0.30,1 0.0, 0.0

IR, WR,, ZR, XCEIL, XWALL, XFLOOR, MATER.C, MATEN,: MATERF_',

21.-0, 9.0, 4.0, 0.25, 0.25, 0. 15, , , NFP, PI, P2, TINIT, PINIT, ZIF, ZOF, ZFIRE,, VIF, EQUIP,,EFFIC

0,1.0, 0.990 .298.0, 0.995. 4.0, 0O.0,: 0.61, 1.5, -0.'0, 0..9995

IFO, TCO,. TWO, N2X2IF, N2X2OF

298.0, 298.0, 298.0, 1, 1

NRAD(1), NRAD(2), NRAD(3), NRAD(4), NRAD(5), NRAD(6), NRAD(7)

4, L,1 0,' 0,- 0,. 0

IFORM, I, JACT, IBO

1, 3, 3, 1

QRAD1

1.0;

IFORM, I, JACT, IBOý

1, 6, 6, '11

QRAD1

1.0

IFORM, I,'JACT, INO

QRAD 1

27.0

IFORM, I, JACT, IBO

1,4 ~4, 1

QRAD1

75.0

IFORM, I, JACT, IBO

1, 7, 7, .1

QRAD2

2.0

JACT, QRAD3

8, 15.0

4.5
Results from this sample problem are shown in Table 4.3b. This PRINT.DAT

file can be compared to the PRINT.DAT file from the first problem (Table 4.2b).

With all material burning at once, the fire starts out at its ma ximum burn

rate. The hot layer descends sooner (at 260 s compared to 340 s) than in

problem one, and all combustibles are burned up in slightly over 10 min.

Reverse flow through the inlet filter i's experienced at t~he start of the fire

for problem two.

4.4 PROBLEM THREE -AUTOIGNITION ENERGY OPTION,

Use of the autoignition energy option is. illustrated in the third sample

probl~em. The PMMA and rubber gloves are assumed to burn first. Paper, s'olvent, and PVC are present in the fire compartm ent but do not start burning

unless heat flux from the fire reaches a sufficient, material dependent level

to cause flashover .of these materials. PMMA and rubber gloves are given a burn

order of two, but are identified with the NBO parameter as being at risk via

ignition energy option. The parameters and values required for input are shown

in Table,4.4a. The PRINT.DAT file is shown in Table 4.4b.

As shown by the PRINT.DAT output file, heat flux in the room reaches

sufficient levels to start the solvent burning but not the paper or PVC. The

solvent starts burning at 26 s raising the mass burn rate at this time to its

maximum value during the fire. The oxygen concentration drops below 11% at a

little over 10 min Into the fire, extinguishing any remaining flames. Most of

the combustibles (98.7%) that started burning (PMMA, rubber gloves, and

solvent) have been consumed by this time.

4.5 PROBLEM FOUR -EQUIPMENT AT RISK

In this sample problem, pieces of equipment are added to the scenario in

problem o ne. Four containers of radioactive material on the floor of the glove

box and an adjacent steel glove box located next to the burning glove box are

modeled. Two of the four containers of radioactive material hold plutonium

4.'6
TABLE 4.3b. PRINT.DAT from Problem Two

OUTPUT FOR COMPARTMENT EFFECTS

COMPARTMENT OXYGEN NOT LAYER

TIME PRESSURE CONC. THICKNESS (SEC )--' ATM ) (VOL FRACT) ( M )

VOLUMETRIC FLOW RATE HOT LAYER MASS BURN HEAT GEN. HEAT LOSS HEAT TO

INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS

(M**3/S) (M.3/S) ( F) ( G/S) ( KW ) ( KW ) ( KW )

0.00 .so5 0210 .00 1.5so0 -1.5000 78.4600 20I 1.08 0.10 1.1881 -1.4060 -5.3953 694.8214 40.00 1.05 .210 2.3219 -0.6703 -4.4888 629.3458 60." 2.0"0633 0.1732 3.4058 -0.3970 -4.0020 575.3207 80.00 0.9915 0.1830 3.4440 1.0113 -0.4353 519.7217 100.00 0.9927 0.1550 3.4929 0.8651 -0.8060. 486.7848 126.00 .9938 0.14B5 3.5538 0.7298 -1.1497 463.5696 140.00 0.9934 0.1433 3.2824 0.7823 -1.0159 443.2081 180.00 0.9933 0.2394 3.8842 0.7894 -0.9979 423.2783 180."0 0.9934 0.1363 3.7494 0.7810 -1.0293 405.4338 2"0.00 0.9936 0.1339 3.8172 0.7729 -1.0397 389.8403 220.00 0.9935 0.1319 3.8877 0.7849 -1.0601 376.2856 240.00 0.9936 0.1303 3.9608 0.7825 -1.0861 364.3439 260.00 0.9920 0.1291 4.0000 0.9451 -0.5170 346.5760 280.00 0.9934 0.1279 4.0000 0.7775 -0.6123 332.3489 300.00 0.9944 0.1265 4.0000 0.6597 -0.5763 322.9827 320.00 0.9950 0.1251 4.0000 0.5883 -0.5105 315.3943 340.00 0.9955 0.1237 4.9000 0.5302 -0.4554 308.5584 380.60 0.9959 0.1224 4.0000 0.4890 -0.4079 302.1992 380.00 0.9962 0.1211 4.0000 0.4685 -0.3688 296.1595 400.00 0.9904 0.1199 4.0000 0.4292 -0.33865 290.3957 420.00 0.9988 0.1187 4.0000 0.4051 -0.3095 284.8964 440.00 0.9968 0.1177 4.0000 0.3837 -0.2867 279.8641 480.00 0.9969 0.1167 4.0000 9.3843 -0.2871 274.8849 480.00 0.9972 0.1257 4.60000 0.3487 -0.25600 269.956" 5001.00 -0.9972 0.1148 4.8000 6.330 -0.2350 2865.4491 5620.00 0.9973 0.1139 4.0000 0.3157 -0.2216 261.1874 540.00 0.9974 0.1231 4.0000 0.3020 -0.2097 257.6924 580. 00 0.9976 0.1124 4.6000 0.2894 -0.2999 253.2111 580.00" 97 0.1116 4.0000 0.2776 -0.1892 249.5112 860.00 0.9977 0.2109 4. 0000 0. 2867 -0.1803 245.9816 620.00 0.9978 0.1103 4.6000 0.2565 -0.1722 242.6098 All COMBUSTIBLE MATERIALS WERE CONSUME BY: 621.0000 SEC

178.:4'13 8 34917.3787 -36802.584 -16.188

178.0537 3489.7983 -3934.7281 -444.9277 177.7712 3483.8472 -39568.8259 -472.9788 110.8035 2751.2288 -3000.4888 -249.2400

99.9377 2326.6021 -2468.1008 -162.4988

98.0361 2248.5427 -2300.6143 -52.0715

89.8443 29065.2052 -1989.3739 -84.1687

82.3957 1668.0485 -1750.6318 ý-82.5834

77.2722 1495.1865 -1561.8726 -68.7081

73.2063 1384.1875 -1418.4805 -54.3130

89.9150 1282.1958 -1304.9890 -42.7932

88.5186 2274.2180 -1207.6857 -33.5697 71.4058 2234.8180 -1377.0184 -142.1984

88.6264 1262.7498 -1217.8215 -58.0728

85.8257 1089.7850 -1121.8087 -31.8217

62.2948 1018.1987 -1047,.8049 -31.6082. 69.7487 951.4331 -983.9459 -32.5128. 57.4202 891.4023 -928.7134 -35.3111 55.2276 836.3748 -874.1184 -37.7438 53.16899 788.1348 -825.4814 -39.3488

61.2375 740.2823 -780.4684 -40.1861 49.4245 898.3725 -738.8329 -40.4804 47.7205 859.9049 -700.3180 -40.3311 46.1104 824.7430 -804.86655 -39.9225 44.0042 592.3109 -631.8358 -39.3258 43.1769 582.3925 -600.9960 -38.6035 41.8249' 534.7305 -572.5334 -37.8030 40.6451 509.0999 -548.0520 -36.9522 39.3310 485.3026 -521.3764 -38.0738 38.1775 463.1830 -498.3442 -35.8122 37.0802 442.5274 -478.8174 -34.2960

840.00

860.600

680. 00

700. 00

720.00

740.00

780.00

780.00

800. 00

820.00

840.00s

880.00s

880.00s

900.00

920.00O

940 .00

960.00

980.00O

1000.00

0.9923 0.1131

0.9935 0.2159

0.9949 0.1180, 0.9958 '0.1195

0.9965 0.2200

0.9969 0.1219

0.9973 0.1228

0.9975 0.1236 0.9977 . 0.1244

0.9979 0.1250

0.9980 0.1268

0.9982 0.1262

0.9983 0.2287

0.9983 012272 0.9984 0:1277-

0.9985 0.1282 0.9988 0.1286 0.9988 0.1290

0.9987 0.1294

4.60000

4.6000

4.08001

4.0000

4.06000

4.08000

4.0000

A.6000

4. 000

4.2000

4.*0000

4.6000

4.60000

4.60000

4.0000

4. 000

4. 0000

4.0000

4.0000

1.0284 -0.0281 218.44899 0.7674 -0.0745 201.2742 0.5987 -0.1018 189.5225 0.4913 -0.1180 180.9238 0.4178 -0.1243 174.3214 0.3648 -0.1281 -189.06888 0.3250 -0.1295 184.7688 0.2940 -0.1294 161.1838

0.2e93 -0.1283 158.0908 0.2492 -0.1268 155.4272

0.2325 -0.1248 153.0879 0.2184 -0.2227 151.0095

0.2083 -0.1205 149.1446 0.1958 -0.1183 147.4588

0.1888 -0.1180 145.9181

0.1785 -0.1138 144.5057

0.1713 -0.1117 143.2018

0.1848 -0.1098 141.9919

0.1589 -0.1075 140.8841

6.0so"

0.000

0. 0000

6.90041

0. 0000

0.0000

6.6000

0. 0000

0.0000

0.0000

0.0000

0. .0000

6.0Ro0m

6. 060 0.00man

.0.0000

a.0"SO

0.0000

0.90"0

0.0000 -318.86815 -318.8615 0.0000 -217.8827 -217.8627

0.0000 -159.8888 -159.8688

8.0000 -121.2584 -121.2584

0.000 -95.7889 -95.7889 0.0000 -77.7596 -77.7596

0.0000 -84.5469 -84.5469 0.60000 -54.5851 -64.5851

0.0000 -46.8971 -46.8971 0.0000 -40.8433 -40.8433 0.0000g -35.9927 -35.9928 0.0000 -32.0449 -32.0449

0.0000 -28.7884 -28.7884 0.00100 -28.0879 -26.0879

0.0000 -23.7717 -23.7717 0.0000 -21.8128 -21.8128 0.0000 -20.1258 -20.1258 0.0000 -18.8615 -18.8615

0.0000 -17.3810 -17.3810
TABLE 4.4a. Input Problem Three

PLOTA1S, TSPEC, DELT, MIBO, IGNITE, IPRINT, MJE(1), MJE(2), MJE(3), MJE(4)

'', 1000.0, 2. 20, - 2, I .1, ý 10,' 0, . , ,s

FUEL(1,2), FUEL(2,2), FUEL(3,2), FUEL(4,2) ... 40860.0, 0.0, 0. 0, .4540.0, 0.0,0 0.0,, 0.0, 0.0,O 0.0

FUEL(1,,1), FUEL(2,1), ,FUEL(3,1ý), FU.EL(4,1)...

0.0, 0.0, 4 54..0, -0,.0, 0.0'O, 227.:0, 910.0,:0.0, 0.0

AREC(1,2), -AREC(2,2), AREC(3,2), AREC(4,2)...* 3.6, 0.0,9 0.0, 2.0, 0.0O.., 0.0, 0.0 0.0 0.

AREC(1,'1), AREC(2,1,,), AREC (3,J), AREC (4, 1).;

0. 0, '0.0-, 0. 09, 0ý.0, .0.0-, 0.09, .0.30:, 0.0, 0.0

LR, WR, ZR, XCEIL, XWALL, XFLOOR, MATERC, 'MATERW, MATERF-,

21.0, 9.0, 4.0, 0.25, 0.25, 0.15, 1, 1, 1

NFP, PI, P2,' T.INITi PINIT, ZIF, ZOF, 'ZFIRE,i .VI.F, EQUIP,* EFFIC

0,1 1.0,1 0.990 198.0, 0.-395 4.0," 0.0, .1 1.'5,' 0.0, 0.9995

TFO, TCO, :TW0,..N2X2IF, N2X2OF

298.0, 298.0, 298.0t, 1, 1

NBO(1), NBO(2), ,NBO(3:),,NBO(.4),, NBO(5)j, NBO(6)-, NBO.(7)., NBO(B), NBO(9).

0, 2, 1 0, .2, 11 2, 2

NRAD(1), NRAD(,2).,..NRAD(3), *NRAD(4), ý,NRAD(5),, NRAD(6,), NRAD(7) 4, 1 . . 1, 0, 0,0 0

IFORM, I, JACT, IBN

.1, 3j 3, .2

QRAD1

1.0

IFORM, I, JACT, IBN

1, 6, 6 , 2

Q RAD 1

1.0

IFORM, I, JACT, IBN

QRAD1

27.0

IFORM, I, JACT, IBO

QRAD1

75.0

IFORM, I, JACT, IBN

1, 7, 7, 2

QRAD2

2.0.

JACT, QRAD3

8, 15.0

4.'8
TABLE 4.4b. PRINT.DAT from Problem Three

OUTPUT FOR COMPARTMENT EFFECTS

COUPARTMET MOYEN MDT LAYER VOLUMETRIC FLOW RATE NOT LAYER MASS BURNi HEAT GEN. HEAT LOSS NEAT TO TIME PRESSU1RE CONC. THICKNESS INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS (SEC) ATM) (VOL FRACT) (U (Mse3/S) (M*3/S (F) (0/5 KW` (KW) (1W

2.U 0998 02100 -.1.00 s.on 6 4'11.12887 150.1266 2756.6'376 -17900.8984 9515.7396 4.98 1.0069 6.2100 0.1218 -2.0796 -5.0796 495.4149 182.9638 3011.7388 -2738.8726 272.8643 6.00 2.0M28 0.2100 0.2281 -0.7042 -3.7865 541.05.49 163.9454 3031.3247 -2730.0889 301.2358 80 1.68 .2100 0.3367 -1.8238 -5.0494 570.1249 183.9579 3931.5737 -2758.6608 273.0129 2800 1.0: 0.~2100 109M113 -4.8062 615.8334 283.7008 3026.4446 -3033.0967 -6.86522

COMBUSTIBLE TYPE 7 HAS IGNITED AT TIME: 26.0000 SEC

48.010 2.0050 0.2100 2.2375 -4.7282 -.4.4851 540. 2886 176.0944 3463.3540 -3714.3226 .- 258.9675 60.00 1.0036 0.2106 3.2246 -4.4415 -.4.0491 652.6978 174.7944 3468.9646 -3804.192M -347.2348 88.010 0.9915 0.16849 3.4765 1.035? -. 4.568 504.6337 207.8879 2724.4441 -2966.9832 -242.5391 100.00 0.9948 0.1587 3.5294 0.7348 -1.1968 476.7023 107.8421 2723.2637 -274B.7693 -23.4417 128 00 0.9958 8.1567 3.6123 986168 -1.4854 4865.6288 107.76e4 2721.3811 -2661.4841 69.8970 140. 00 0.9934 0.1451 3. 6938 6.8076 -1.0183 444.6642 09.8106 2009.2694 -2109.6714 -100.4020 166.00 0.9934 0.1410 3.7474 0.8095 -1.0121 423.9318 83.60056 1764.1699 -1840.2595 -86.0896 106.00 0.9934 0.1378 3.8132 0.0014 -1.0320 405.6875 77.7416 1668.06516 -1848.3732 -72.3216 280.00 8.9936 0.1363 3.8819 0.7917 -1.0566 389.86894 73.5687 1427.1570 -1486.6582 -58.58122 220.00 0.9938 0.1332 3.9536 0.7820 -1.01778 378.2143 76.2880 1317.6464 -1359.6187 -41.9723 24@.00 0.9902 0.1316 4.0000 0.9740 -0.6429 357.1132 74.7061 1384.4845 -1505.9421i -242.4776 266.00 0.9934 0.1380 4.9080 0.8044 -. 8.418 942.2620 171.2052 1269. 1883 -1328.4757 -57.2894 280.00 0.9944 0.1224 4.0000 6.8899 .6.6012 332.1121 68.12090 1181.6399 -12168.8386 -35.2909 300.00 0.9958 0.1268 4.6800 0.8127 -. 5.371 323.8179 86.1931 1099.6997 -2132.6336 -32.9332 3206.W 0.9954 0.1262 4.0000 0.6584 -4.4778 316.3362 82.4485 1024.2664 -106g9.9221 -35.6587 84000 .0.9958 M.1238 4.6000 0.6169 -6.4282 369.3243 69.8813 955.8013 --994.4923 -38.6920 308 00 0.9968 0.1224 4.0000 8.4827 .4.3877 362.6878 67.4879 893.8534 -934.7046 -40.8511 308 00 0.9963 0.1211 4.9600 0.4634 -. 3.842 296.8958 65.2579 837.8126 -879.8895 -42.0879. 460.00M .9966 0.1199 4.8600 0.4274 -4.3282 296.4372 68.2780 787.0168 -829.5939 -42.5771 428.00 ff.9967 0.118? 4.96W0 8.4642 -4.3823 284.7979 51.2348 740.8508 -783.4124 -42.6616 440.00 0.9969 0.1177 4.9980 0.3632 -8.2816 279.4617 49.4252 698.7885 -740.9636 -42.2971 4"66.0 8.9970 8.211" 4.8800 0.8842 -4.2636 274.4100 47.7081 8668.2870 -781.8883 -412.8023 488.00 8.9972 0.1167 4.8000 0.3487 -8.2475 269.6259 46.1032 862.0013 -666.8539 -40.8252 600 .00 8.9978 0.1148 4.8080 0.3367 -4.2333 266.0897 44.6914 692.65668 -832.6627 -40.0067 620.00 0.9974 0.1139 4.8900 0.3180 -8. 2260 260.7646. 4 3.2e46 5682.6437 -801.7462 -39.2014 640.00 0.9975 0.1131 4.88900 0.3624 -0.2091 2568.6943 .41.8157 534.9999 -573.1622 -38.1623 668.00 .9976 0.1124 4.9800 0.2898 -0.1987 -252.8036 40.6382 589.3944 1.548.6004 -37.20600 580.00 0.9977 8.1116 4.8800 0.2781 -0.1892 249.0986 $9.3268 485.6252 -521.8715 .-36.2462 660.00 0.9978 0.1109 4.880 0.2672 -0.1886 245.5668 38.1758 483.5143 -498.8896 -36.2953 ALL BURNtING HAS STOPPED AT TIME: 688.000 SEC WITH 98.7 PERCENT OF AU. COMBUSTIBLES CONSUMED IN THIS FIRE

620.00 0.9997 0.1124 4. 0000 1.1386 -0.8161 227.6817. 9810000 0.000., -387.0560 -387.0560 640. 00 0.9928 0.1157 4.09800 8.8758 -0.0624 207.0284 0.0088 8.908M -254.1741 -254.1741 868.0 so 9.9948 8.2179 4. 0008 0.8838 -0.0979 193.4686 9.0080 9.0000 -188.4563 -1608.4563 680.00 0.9956 0.1196 4. 0800 0.6349 -8.1167 183.7905 6.98.008 0.0080 -135.1602 -135.2602 760.00 0.9963 0.1210 4.8008 0.4493 1-0. 1268 176.561088 0.0000 6.00Wo -106.2580 -205.2688 720.00 8.9968 0.1222 4.880M 0.3888 -0.1316 170.7720 8.0800 0.0Sam8 >64.4860 -84.4850 740.88 0.9972 0.1231 4.8808 0.8440 -0.1335 166.1324 0.0000 0.0as" -69.4829 -69.4829 768.00. 0.9976 0.1240 4.0SO0 0.3096 -0.1337 162.2704. 0.. .008" -58.3076 -58.3076 788.88 0.9977 0.1248 4.0888 0.2824 -0.1329 259.0137 - 0.0000 -,0.0808 -49.7674 -49.7673 808.00 0.9979 0.1255 4.0800. S. 2606 -0.1313 266.20M6 0.8800 ý0.6000 '-43.0994 '-43,.0994 820.00 8.9980 0.1261 4.0000 0.2424 -0.1294 163.7419 O.000 0. 0800 -37.7949 -37.7949 840.00 8.9981 8.1267 4. 008 0.2272 -0.1272' 152.6867 0.0000 0.8888 -33.5660, -33.5060 860.00 0.9982 8.1273 4. 0088 0.2142 -8.1249 2 49.6221 0.080" 0.0008 -29:9881 -29.9881 880.00 0.93 0.1278 4.0900 0.2830 -0.1226' 147.8678 16.Name 0.8000. -.-27.0862 -27.0651
TABLE 4.4b. (contd)

900.00 l. 9984 0.1283 4.0000 0.1933 -0.1202 146.2728 0.8000 0.0000 '-24.6082 -24.6082 920.00l ::.998 0.,1287 4.0000 0.2847 -0.1279 144.8120 0.0000 O.'0000ý. -22.6209 -22.6209 940.00 

980.00 .996 2.292 4.0000 0.1770 -0.1157 143.4884 2 0.0000 .00001- -20.7314 -20.7314 0.9988 0.1296 4.0000 -0.1702 -0.1136 142.2203 0 .0000 0.0000, 19.1833 -19.2832 980.0e 0.9987 0.1300 4.0000 '0.1840 -0.1113, 141.0805 0.0000 0.0000' -17.8328 -17.8328 1000.00 -0.9987 0.1303 4'.000 .1 -0.1093 139.9787 0.0000 .0.0000. -18 8470 -18.8470

TIME EXCEEDS USER SPECIFIEDMMEI AT: 18006.09M SEC
dioxide. The other two contain plutonium nitrate solution.,-All four containers are stainless steel with a diameter of 0.15 m and a height of 0.23 m.

The weight of each'of the containers alone is estimated. at 0.45,kg.

Of the two powder containers, one is full of powder. The other is

partially full containing about half powder and half air. Applicable po wder,

properties are moisture content 1%, bulk density 1.5 g/cm3, theoretic density

10 g/cm3. All four are sealed and may overpressurize-an d rupture during the

fire. The failure pressures of the containers are.3.4.atm and 1.3 atm for the

full and partially full cans, respectively.

One of the liquid containers is assumed to be full containing about 90%

liquid and 10% air by volume. The other liquid container is half full of

liquid. The nitrate solution has a density of 1.5 g/cm3 , Failure .pressures of

the cans are similar to those for the powder containers..

The steel glove box acts as a heat sink during the fire. -Dimensions are

0.61 m x 0.91 m. The glove box sits at floor level and weighsabout 9 kg. All

initial temperatures are 298 OK.

For this sample problem, JACT was set to 1 for All plutonium dioxide

powder source terms, and 2 for the nitrate contaminant. The required parameters and input file for this problem are shown in table 4.5a. The PRINT.DAT

file is shown in Table 4.5b.

The results in PRINT.DAT from this problem. are very similar to those in.

problem one. The heat absorbed by the steel glove box is part of the heat loss

to walls so cannot be seen separately. The radioactive source term, however,

is much greater for this problem than for problem one-because the two partially

full containers of radioactive material became overpressurized during the fire

and contribute to the radioactive release. -Over 28 g of contaminant remain

airborne in the compartment at 1000 s in this problem compared to a l~ittle over

1 g in problem one.

4.6 PROBLEM FIVE -ALTERNATE-FLOW PATH

Another variation of problem one is shown here. An alternate~flow path is

assumed to open up in the room 400 s after the fire starts. The flow path, due

4.11
TABLE 4.5a. Input for Problem Four

PLOTANS, TSPEC, DELT, MIBO, IGNITE, IPRINT, MJE(1), MJE.(2), MJE(3),ý MJE(4)

IV', 1000.0, 2.0, 2, 0, 10, 1, 2, 2., 0

FUEL(1,1), FUEL(2,1), FUEL(3,1), FUEL(4,1)...

0.0, 0.0, 454.0, 0.0, 0.0, 227.0, 910.0, 0.0, 0.0

FUEL(1,2), FUEL(2,2), FUEL(3,2), FUEL(4,2)...

40860.0, 0.0, 0.0, 4540.0, 0.0, 0.0,, 0.0, 0.0, 0.0

AREC(1,1), AREC(2,1), AREC(3,1), AREC(4,1)...

0.0, 0.0, 0.09, 0.0, 0.0, 0.09, 0.30, 0.0, 0.0.

AREC(1,2), AREC(2,2), AREC(3,2), AREC(4,2)...

3.6, 0.0, 0.0, 2.0, 0.0, 0.0, 0.0, ,o.',-0.0,

LR, WR, ZR, XCEIL, XWALL, XFLOOR, MATERC, MATERW, MATERF

21.0, 9.0, 4.0, 0.25, 0.25, 0.15, 1, 1, 1

NFP, P1, P2, TINIT, PINIT, ZIF, ZOF, ZHIRE, VIF, EQUIP, EFFIC

0, 1.0, 0.990 298.0, 0.995 4.0, 0.0, 0.61, 1.5, 0.0, 0.9995

IFO, ICO,. TWO, N2X2IF, N2X2OF

298.0, 298.0, 298.0, 1, 1

WD (1,1)

0.61

HEQ (1,1)

0.91

HTF(1,1)

0.0

MATERE(1,1)

4

WMASS(1,1)

9.0

TEI1()

298.0

WD(1,2), WD(2,2)

0.15., 0.15

HEQ(1,2), HEQ(2,2)

0.23, 0.23

HTF(1,2), HTF(2,2)

0.61, 0.61

MATERE(1,2), MATERE(2,2)

3, 3

WMASS(1,2), WMASS(2,2)

0.45, 0.45

VGAS2(1), VGAS2(2)

3.E-4, 2.OE-3

VPWD(1), VPWD(2)

4.1E-3, 2:OE-3

WH202(1), WH202(2)

60.10, 30.0

1E2(1}, TE2(2)

298.0, 298.0

T12(1), T12(2)

298.0, 298.-0

PF2(1), PF2(2)

3.4, 1..3 -

4.12
TABLE 4.5a.(cnd (contd)

WD(1,3), WD(2,3)

0.15, 0.15

HEQ(1,3), HEQ(2,3)

0.23, 0.23.

HTF(1,3), HTF(2,3)

0.61, 0.61-

MATERE(1,3), MATERE(2,3)

3, 3

WMASS(1,3), WMASS(?,3)

0.45, 0.45

VGAS(1),VGAS3.(2)

4.OE-4, 2.OE-3

WH203(1), WH203(2)

5800.0. 3200.0

TE3(1), 1E3(2)

298.0, 298.0

T13(1),

298.0,

PF3(1),

3.4,

NRAD(l),

4,

T13(2)

298.0

PF3 (2)

1.3

NRAD(2), N'RAD(3),

1, 1, :,JACT, IBO

1, 1

NRAD(4), NRAD(5), NRAD(6), NRAD(7)

0, 2, 2, 0

I FORM,

1,

QRADI

1.0

I FORM,

1,

QRAD1

1.0

I FORM,

1,

QRAD1

27.0

1 FORM,

1,

QRAD1

75.0

1 FORM,

QRAD2

2.0

JACT,

1 ,

IVES,

1 ,

IVES,

2,

IVES,

1 , IVES,

2)

]

I ,

6,

4$

JACT,

1 ,

JACT,

1,

JACT,

1,2

I BO

1

I BO

2

I BO

2

1, JACT, IBO

7, 1, 1

QRAD3

15.0

JACT,

1,

JACT,

1,

JACT,

2,

JACT,

2.

QRAD5,

'6000.0,

QRAD5,

3000.0,

QRAD6

5800.0

QRAD6

3,200.0

VOLP,2

0.0041,

VOLP2

0.0041,

PDEN

1. OE+7

PDEN

1. OE+7

4.13
TABLE 4.5b. PRINT.DAT from Problem Four

OUTPUT FOR COMPARTMENT EFFECTS

TIME 

COMPARTMENT OXYGEN HOT LAYER VOLUMETRIC FLOW RATE HOT LAYER MASS BURN HEAT GEN. HEAT LOSS HEAT TO PRESSURE CONC. THICKNESS INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS (SEC) (ATM ) (VOL FRACT) (U) ( M..3/S) (M*3/S) ( F) ( G/S) ( KW) ( KW ) ( .KW )

0.00 e09950s 0.2100 0.90000 1.5000 -1.5000 78.4000 0.0000 0.0000 0. 0800 0.0000 20.00 0.995,4 0.2100 0.4031 1.3825 -1.6175 115.0380 10.5423 359.7440 -344.3492 15.3949 40.00 4.9963 0.2100 0.7916 1.3974 -1.6028 211.9976 10.5407 359.6905 -3344.1955 25.4950 60.00 0.9953 0.2100 1.1339 1.4010 -1.5990 111.7143 10.5395 359.6475 -325.8058 33.8416 80.00 0.9953 0.2100 1.4398 1.4010 -1.5990 212.2988 10.5383 359.8097 -319.1855 40.4242 100.00 0.9954 0.2100 1.7344 1.3922 -1.6078 123.2972 10.5373 359.5670 -313.0818 46.4931 120.80 0.9956 0.2100 2.0064 1.3319 -1.6882 221.9209 2.4308 21.3888 -35.2429 -13.8543 140.00 0.9949 0.2200 2.1881 1.5150 -2.4860 207.9225 2.4313 21.3927 -35.3839 -13.9912 180.00 0.9949 0.2100 2.38.42 1.5156 -1.4844 104.6202 2.4314 21.3943 -34.4102 -13.0160 180.00 0.9949 0.2100 2.5358 1.5152 -1.4848 202.8679 2.4315 21.3952 -33.3026 -11.9074 200.00 0.9950 0.2100 2.7033 1.5147 -1.4853 99.5404 2..4316 21.3958 -32.4964 -11.1007 -220.00 0.09950 0.2100 2.8687 1.5128 -1.4872 97.5629 2.4316 21.3962 -31.0763 -9.8790 240.00 .0.9950 0.2100 3.0344 1.5109 -1.4891 95.8902 2.4317 21.39865 -29.7781 -8.3818 260.00 0.9949 0.2100 3.1982 1.5253 -1.4747 94.2878 1.5307 8.7863 -23.6651 -14.87988 280.00 0.9949 0.2100 3.3573 1.5190 -1.4810 92.6908 1.5307 8.7884 -22.1217 -13.3935 300.00 1.0091 0.2046 3.5202 -2.7220 -5.7220 108.2448 162.5802 3004.0889 -1756.2403 1247.9486 320.00 1.0018 0.1983 3.8619 -0.5014 -3.5442 184.6337 162.3574 2999.6438 -1727.9767 1271.6681 340.00 1.0086 0.2926 4.0000 -1.7905 -3.3621 258.7447 157.1004 2894.7654 -1034.4063 1860.3591 360.00 1.0102 0.2840 4.0000 -1.4085 -2.0022 342.7002 163.1130 3014.7183 -1810.6853 1204.1329 380.00 1.0005 .16 4.0000 -0.0636 -0.7884 381.8283 102.4477 2426.7822 -229E.F,436 231.7388 400.00 0.9997 0.1689 4.0000 0.0322 -0.6407 894.6332 102.8702 2436.7892 -2253.8533 182.9358 420.00 0.9995 0.1625 4.0000 0.0528 -0.5888 404.6769 103.1739 2443.9839 -2292.9607 151.0332 440.00 0.9994 0.1540 4.0000 0.0018 -0.5145 412.9556 103.3946 2449.2107 -2318.9290 130.2817

4b480.00 

4810.00 0.9981 0.2467 4.0000 0.2069 -0.4099 417.2576 99.6872 2282.7485 -2315.9187 -33.1702 0."9946 '0.2423 4.0000 0.5945 -0.2205 401.9709 90. 6694 1927.2357 -2094.1279 -188.8922 500.00 0.9943 0.2374 4.0000 0.6240 -0.2008 382.7915 .83.-6645 2676.9672 -2842.-9349 -184.9878 520.00 0.9946 0.1342 4.0000 0.5919 -0.2072 385.5075 77.7295 1484.5676 -1832.1653 -147.5977 540.00 0.9949 0:1315 4.0000 0.5552 -0.2141 360.4468 .72.8023 1330.4548 -1481.2849 -130.8033 580.00 0.9962 0.2291 4.0000 0.5214 -0.2184 337.2825 68.'6639 1203.9478 -1320.4720 -116.5250 580.00 '0.9955 0.1270 4.0900 0.4912 . -0.220 325.6776 84. 8669 1098.1782 -1202.7114 -104.5332 8010.00 '0.9958 .0.1251 4.0000' 0.4639 -0.2200 315.3630 61."601 1008.4008 -1102.8079 -94.4071 620.00 0.19960 0.123:4 4.0000 0.4392 -0.2181 388.1252 568.6390 931.2053' -1017.0567 -86.8514 840.00 0.9982 0.12219 4.0000 0.4187 -0.2150 297.7924 56.0691 864.0933 -942.6744 -79;5811 680.00 0.9904 0.2205 4.0000 0.3962 -0.2210 290.2272 53.8941 865.1051 -977.5499 -72.3648,. 680.00 0;9966 0.1192 4.0000 0.3774 -0.2003 263.3107 51.5267 753.0409 -020.'0687 -67.0178 700.00 .0.9987 0.'1282 4.0000 0.3600. -0.2022 276.9761 49.5370 700.5425 --768.9203 -62.3899 720.00 0.9969 0.2170 4.0000 0.3440 -0.2958 271.12251 47.7011 664.0070 --723.1631 -58.3461 740.00 0.9970 0.1159 4.000 0.3291 -0.1902 2865.7040 45.9993 627.1306 -68829297 -54.7991 760.00 0.9971 0.2150 4.'0000 0.3153 -0.1846 260.8614 44.4152 5.92.9405* -644.6049 -51.8644 780.00 -0. "72 0.1141 4.00 0.3024 -0.1790 255.9539 42.9355 581.7719 -810.8483 -48.0764 800.00 0.9974 0.2233 4.0000 0.2904 -0.21735 251.5450 41.5487 533.2394 -579.6187 -46.3792 820.00 0.995 01252 4.0000 0.2792 -0.1681 247.4034 40.2450 507.0211 -551.1529 -44.1318 B40.00 0.9975 0.1117 4.0000 0.2687 -0.1629 243.5026 39.01e4 482.0490 -524.9450 -42.0960 860.00 :0.9976 0.2110 4.0000 0.2589 -0.1578 239.8195 37.8557 4"0.4939 -500.7359 -40.2420

ALL 880.00 0.9977 0.1103 4.0000 0.2496 -0.2629 238.3339 36.7569 439.7636 -478.3003 -38.5427 COMBUSTIBLE MATERIALS WERE CONSUMED BY: 892.0000 SEC

900.00 '0.9914 0.1208 4.0000 0.9457 -0.0262 223.9146 0.0000 0.0000 -408.2432 -408.1432 920.00 

940.00 

0.9918 0.1141 4.0000 0.8952 -0.0348 202.8881 0.0000 0.0000 -;266.1252 -266.1525 0.9939 0.1164 4.0000 0.8699 -0.0728 189.0065 0.000 0.0000 -187.7884 -187.7884 980.80 0.9951 0.1281 4.8000 0.5320 -0.0942 179.2957 0.0000 0.000 -139.9482 -139.9482 980.00 0.9960 0.1195 4.000 0.4420 -0.1064 171.8522 0.0000 0.0000 -108.4947 -108.4947 1000.00 0.9965 0.1208 4. 0000 0.3792 -0.1133 166.1230 0. 0000 0.0000 -86.7011 -86.7011
to a filter failure or other opening in the room, is 0.7 m in diameter and

4.3.m above the flloor. (The size of the opening approximates the size of a

filter and is a largeopening, which may adversely affect fluid flow calculations.) The time step was lowered to 0.5 s to avoid instabilities in flow

calculations.. Also note that NFP was changed to 1 so that alternate flow path

parameters could be read in., Table 4.6a shows the change in parameters

required for this problem. The PRINT.DAT file from this problem is shown in

Table 4.6b.

Th rsut sowth pening of the alternate flow path at 400 s. Prior

to this, the fire is similar to problem one, with reverse flow occurring at the

maximum burn rate. After the flow path opens, however, outlet flow is quickly

diverted to this opening, stabilizing flow in the compartment. Radioactive

material is allowed to escape unfiltered through this path. Figure 4.1 shows

the accumulated mass of radioactive particles that escape the fire compartment

for problems one and five after 400 s. Prior to 400 s, results from the two

problems are approximately equal. After 400 s, however, radioactive particles

are ventilated out the'unfiltered alternate flow path in problem five resulting

in a higher radioactive release to the environs.

4.15
TABLE 4.6a. Input for Problem Five

PLOTANS, TSPEC,-DEL~i'MIBO, -IGNITE, 1PRINT,'MJE(1), MJE(2), MJE(3), MJE(4)

IV', 1000.0,_0.5, -2, ý 0, , 10, 0, 0, 0, 0

FUEL(1,I), FUEL(2,1), FUEL(3,1), FUEL(4,1)...-

0.0, 0.0,' 454.0, 0.0, 0.0, 227.0, 910.0, 0.0, 0.0

FUEL(1,2), ýFUEL(2,2), FUEL(3,2),-.FUEL(4,,2) ...

40860.0,' 0.0, .0.0, ,.4540.0, 0.0, 0.0, 0.0, 0.0, 0.0

AREC(1,1), AREC(2,1),-AREC(3,1), AREC(4,).

0.0, 0.0 , 0.09, 01.0, 0.0, 0.09, 0.30, 0.0, 0.0

AREC(1,2), AREC(2,.2), .AIREC(3,2), AREC (4,1)~...

1 3.6' , 0.,0, 2.0, 0.0, 0.0, 0.0, 0.0, 0.0

LR, WR, ZR, XCEIL,. XWALL, XFLOOR, MATERC, MATERW, MATERF

21.0, 9.0, 4.0, 0.25, 0.25, 0.15, 1, 1, 1

NFP, P1-, P2, TINIT, PINIT, ZIF,. ZOF, HFIRE, VIF, EQUIP, EFFIC

1, 1.0,10.990 298.0, 0.9954.0 C 0"O.0, 0.61,- 1.5, 0.0, 0.9995

IFO, TCO, TWO, N2XIF,ý N2X2OF:

298.0, 298.0, 298.0, 1 , 1

TFP(1)

400.0.

HFP(I)

4.3

PFP(1)

0.99

DFP(1)

0.7

NRAD(1), NRAD(2), NRAD(3), NRAD(4), NRAD(5), NRAD(6), NRAD(7)

4, 1 1, 01, 0, 0, 0

IFORM, I, JACT,.IBO

1, 3, 3, 1

QRAD1

1.0

IFORM, I, JACI, 'Igo

1, 6, 6 , 1

Q RAD 1

1.0

IFORM,: I, JACT, IBO

1,1,1 1, 2

Q RAD 1

27.0

IFORM, I, _ATIBO

1, 4, 41 ,1 2

QRAD1.

75.0

IFORM:, I, JACT, 180

1, 7,. 7, 1

QRAD2

2.0

JACT, QRAD3

8, 15.0

.4.16
TABLE 4.6b. PRINT.DAT from Problem Five

OUTPUT FOR COMPARTMENT EFFECTS

COMPARTMENT OXYGEN HOT LAYER VOLUMETRIC FLOW RATE HOT LAYER MASS BURN HEAT GEN. HEAT LOSS HEAT TO

TIME PRESSURE CONC. THICKNESS INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS

(SEC)- ( ATM ) (VOL FRACT) (UM) ( M*3/S) (Mw3/S) ( F) ( G/S) ( (W ) ( KW ) ( KW )

40.86 :9.995a 6.21600 0.4260 1.504 20.60 0.9963 0.26 0.26 1.4363 4.6 0.9953 0.216M 6.11 1.484 6a.00 6.93 2100 1.1497 1.4031

86.60 0.9953 0.2200 1.4631 1.40002 100.06 0.9954 0.2100 1.7480 1.3915 1260.66 .9950 0.2200 2.6075 1.5123 146.06 6.9956 .22100 2.1691 1.5135 1806.0 6.95 .2200 2.3653 1.5133 186.60 0.9950 0.2106 2.5369 1.5126 200.00 6.99560 0.2206 2.7064 1.5118 220.60 6.9950 0.2200 2.8703 1.5106 240.M0 0.99560 0.2166 3.0362 . 1.5065 2860.06 6.9949 0.2100 3.1993 .1.5191 286.00 0.9949 0.2100 3.350? 1.5171 306.66 1.6668 0.2644 3.5437 ~'-6.2249 326.06 1.0012 0.1982 3.8622 -0.3420 340.06 1.6087 0.2918 4.6066 -1.9523 386.66o 1.0160 0.1984 4.6066 -1.5387 386.06 1.0017 0.2772 4.6666 -6.1944

406.06 1.0665 0.1698 4.6666 -0.6557

426.60 0.9967 6.1843 4.6666 1.6632 446.60 .9-967 0.1589 4.6666 1.0594

466.66 0.9907 0.2536 4.0606 1.0577

486.06 0.9m6 0.1489 4.0000 1.0675

660.66 0.9984 0.1448 4.0666 1.6971 526.60 0.9963 0.1416 4.6666 1.1649 540.66 0.9903 0.2390 4.609W 1. 1082

56.66 a.9963 0.1370 4.06000 1.1054

506.60 0.9963 0.2353 4.0600 1.1038

666.60 0.9963 0.2340 4.0666 1.1022

620.60 0.9963 0.2329 4.0660 1.1060

846.66 0.9963 0.2320 4.0666 1.0991 666.66 0.9904 0.2322 4.6066 1.0978 686.06 0.9904 0.2806 4.606W 1. 0966

706.66 0.9964 0.1800 4.6006 1.0956

726.66 0.9964 6.2296 4.6066 1.0948

746.66 0.9904 0.1292 4.6066 1.0940

786.06 6.9964 0.1269 4.606W 1.0933

ALL COMBUSTIBLE MATERIALS WERE CONSLUME BY: 772.666 SEC

-1.5965 106.1687 16.5S425 359.7523 -34'2.2163 1759 -1.5954 2065.7407 106.411 359.7041 -331.3324 28.3717

-1.5989 160 .8855 106.400 359.6849 -322.7829 38.9621

-2.5998 160.4123 10.5390 359.6369 -315.9845 43.8648

-1.8668 110.6921 10.5381 359.86602 -316.3917 49.2084

-1 .4877 169.5328 2.4310 21.3966 -34.0268 -12.6362 -1.4885 165.6558 2.4313 21.3934 -33.6984 -12.3031 -1.4867 102.8275 2.4315 21.3947 -32.6269 -11.2222 -2.4874 200.3155 2.4316 21.3955 -32.4110 -16.0154 -2.48e4 98.21260 2.4316 121.3982 -36.23065 -8.8344 -1.4966 95.4345 2.4317 '21.3966 -29.1353 -7.7387 -1.4925 94.9203 2.4317 21.3989 -28.1444 -8.7475 -1.4809 93.4244 1.8607 8.7884, -22.1408 -13.3544 -1.4829 91.9423 1.5368 0.7885 -20.8263 -12.0398 -3.2251 104.2166 183.87-12 3029.8442 -1669.2764 1166.5739 -3.356" 259.1662 163.4975 3022.3875 -2188.80655 1136.6819

-3.4722 241.7253 158.7619 2888.0122 -924.2516 1963.7612 -2.1673 3306.834 162.8854 300S68.58 -1713.6301 1294.95604

-6.9115 372.0691 101-.8714 2413.1364 -2083.0913 330.0391' -6.7125 389.5966 102.5860 2430.0334 -2197.6245 232.4089 -6.6441 392.18656 162.4514 2426.8697 -2256.1956 279.6731 -0.6460 389.1879 102.4222 2426.17"6 -2239.2488 286.9272 -0.6467 406.7271 102.4629 2426.9648 -2184.2439 292.8669 -0.0407 464.8737 101.1330 2367.37"6 -2129.6938 237.6824

-4.6235 899.1889 94.6789 2160.6829 -2826.6581 80.6248

-0.0196 887.8179 89.1719 1892.6975 -18568.1411 84.5584

-0.0182 375.7424 84.8448 2731.9997 -1761.7128 30.2776

-6.0186 884.6524 80.9624 1667.1530 -15668.3963 40.7633 -

-0.0194 355.0638 77.9674 2509.1958 -1453.6863 55.6328 9.26W3 846.8641 75.5226 1431.4832 -2866.9666 70.57866 -6.6211 339.9146 73.6167 1369.1982 -1264.7498 84.4485 -6.0216 884.816 71.0615 1316.8228 '-1222.0964 96.7263 -0.6225 329.37865 70.4912 2277.7587 -1176.3555 1907.4012 -0.0236 825.4162 69.3526 1244.06591 -1127.4384 116.6267 -6.6284 322.1354 88.4666 1226.2501 -1691.6914 124.5587 -0.0238 319.4450 67.6046 1193.1902 -1081.7919 131.8983 -0.6240 817.2498 66.9386 1178.9988 -1038.6943 137.2943 -6.0243 815.4725 66.3749 1157.9468 -1965.5518 142.3955

7890.6

806.66

826.06

840.00

866.66

896.06

966.06

926.00

940.06

966.06

980.66

1060 .0

0. 9887

6. 9892

6.9895

0. 9896

0.9897

0. 9898

6. 9898

0.9898

0. 9898

6. 9899 6.9899

6.9899

6.21320

0.21396

0.21442

0.21484

60.5262

0.2552

0.21581

0. 1667

0.21631

0.2658

0.21674

0.1894

4.9066

4.9066

4.98W6

4.06M6

4.6666

4.0666

4.06686

4.60600

4.00W0

4.606W

4.0666

4.066W

1.2878

1. 2299

1.1963

1.1789

1. 1892

1. 1834

1. 1597

1. 1574

1. 1558

1. 1547

1.1540

1.1534

6.0819 285.1660 0.A0666

0.6494 237.8274 0.0606 0.0312 2106.921 0.6006 0.02216 292.8768 0.00 0.0163 180.3921 0.6666 0.0132 271.6848 6.0606 0.0112 263.8486 0.6000 6.6699 158.0639 0.0606 0.0090 263.2430 0.0000 6.6684 149.20659 6.660 6."068 246.7444 0.0600 6.0677 242.7326 0.0000

0.60060 -766.2646 -766.2646

0.60600 -461.3662 -401.3062 0.60600 -238.8968 -236.8968 0.6066 -148.3610 -148.3610 0.60660 -95.6102 -95.6102 0.6660 -61.9292 -61.9292 0.066600 -39.3096 -39.3098

0.60660 -23.5196 -23.5198 0.000 -12.1551 -12.1551 6.App06 -3.7702 -3.7702 6.660pp 2.5431 2.5432 6.0ay06 7.3779 7.3779
cc

0

w5

Cu

0.2 1 1 1 1

400 500 600 700 800 900 1000

Time, s

FIGURE 4.1. Accumulated- Mass of Radioactive

from Problems 1 and 5

Material to Environs

4 *18
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5.1
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Powers, D. A.

Concrete."

1977. "Empirical Models for the Thermall Decomposition of

Trans. Am. Nucl. Soc. 26:400.

Schwendiman, L. C., J. Mishima, and C.-A. Radasch. 1968. Airborne Release of

Particles in Overheating Incidents Involving Plutonium Metals and Cmons

BNWL-SA-f1735, Pa-cific Northwest Laboratory, Richland, Washington.

Steciak, J., A. Tewarson, and 4. S. Newman. 1983. Technical Report - Fire,

Properties of Combustible Materials Commonly Found in Nuclear Fuel CycleFacilities. FMRC J.1. 0G3R8.RC, FactoryMutual Research, Norwood,

Sutter, S. L., J. W. Johnston, and J. Mishima. 1981. Aer osols Generated by

Free Fall Spills of Powders and Solutions Static Air. NUREG/CR-2139, U.-S.

Nuclear Regulatory Commission, Washington, D.C.

Sutter, S. L., J. Mishima, and L. C. Schwendiman. 1974. Fractional Airborne

Release of Strontium During the Combustion of 30 Percent Normal Tributyl

Phosphate in a Kerosene-Tyee Diluent. BNWL-B-358, Pacific Northwest

Laboratory, Richland, Washington.

Tewarson, A. 1980a.

4(4) :184-191.

"Heat Release Rate in Fire." Fire and Materials.

Tewarson, A. 1980b. Physico-Chemical and Combustion/Pjrolysis Proeerties of

Polymeric Materials--Technical Report. PMRC J. I. 0EON 6.RC, National Bu-reau

of Standards, Washington, D.C.

*Tewarson, A. 1982. Quantification of Fire.Properties of Fuels and Interaction

with Fire Environment. Factor Mutual Research Corporation, Norwood,

Massachusetts.

Tewarson, A.,

Intensity."

Tewarson, A.,

Parameters.

and R. F. Pion. 1976. "Flammability-of Plastics-I. Burning

Combustion and Flame. 26:85-103.

et al. 1980. The Influence of Oxygen Concentration on Fuel

Factory Mutual Research, Corporation, Norwood, Massachusetts.

Waldmann, 1., and K. H. Schmitt. 1966.

of Aerosols." In Aerosol Science, pp.

".Thermophoresi s and Di ffusiophoresi 5

137-162. Academic Press, London.

5.3
Wal ker, E. 1978. A Summary of Parameters Affecting the Release and Transport

of Radioactive Material from an'Unplanned Incident. Bechtel, Inc., San

Francisco, California.

Zinn, B. T., et al. 1978. Investigation of the Properties of the Combustion

Products Generated by Building Fires--Final Report of National Burea-u o-f

Standards. School of Aerospace Engineering, Georgia Institute of Technology,

Atlanta, Georgia.

Zinn,. B. T., et al. 1980. The Smoke Hazards Resulting from the Burning of

Shipboard Materials Used by the U7.S. Navy. NRL 8414, Georgia Institute of

Technology, Atlanta, Georgia.

Zukoski, E. E., T. Kubota, and B. Cetegen. 198 0. Entrainment in Fire

Plumes. Daniel and Florence Guggenheim Jet Propulsion Center, California

Institute of Technology, Pasadena, California.

5.4
APPENDIX A

EXPERIMENTAL DATA FOR BURNING CONTAMINATED

COMBUSTIBLE SOLIDS

APPENDIX A

EXPERIMENTAL DATA FOR BURNING CONTAMINATED

COMBUSTIBLE SOLIDS

TABLE A.1. Burning Cellulose Contaminated with DUO Powder

Run

Number

4

Time, min

0

3.00

7050

11.00

14.00

Cumulative Fractiop al

Release of U x 10

0

1.38

8.38

16.13

18.78

Cumulative

Mass Loss, g

0

2.57

19.97

29.95

31.00

12

15

23

0

7.42

8.50

12.17

17.00

0

21.33

22.32

29.25

33.50

0

3.20

3.97

7.68

10.97

0

3.*28

5.00

7.28

10.42

0

4.*10

5.*88

7.73

12.72

0

3.28

8.*62

15.40

23.90

0

12.67

14.40

27.82

30.27

0

12.30

32.80

47.50

47.80

0

25.*40

43.00

51.50

54.60

0

20.40

38.10

4 3.10

47.80

0

14.68

21.87

31.10

31.12

0

5.43

9.20

26.77

27.84

0

5.66

11.32

24.43

23.86

0

5.33

15.88

21.56

22.49

0

10.88

20.*38

22.96

21.77

Notes (a)

HF = 23 kW/m2

A = 8 t/m

UC = 0.10 g/g

Smoldering

HF = 23 kW/m2

A =8 i/m

UC = 0.03 g/9

HF = 13 kW/m 2

A =8 x/m

UC = 0.09 g/g

HF = 23 kWlm2

A =8 x/m

UC = 0.09 g/g

HF = 23 kW/m2

A =8 tVm

UC = 0.08 g/g

HF = 23 kW/m2

A =8 t/m

UC = 0.09 g/g

26

27

A.1
TABLE A.1-. (ctd (contd)

Run

Number

Cumulative Fractiop al

Time, min Release of U x 10~

Cumul ative

Mass Loss, g

28 0

3.68

6.05

6.80

11.38

0

56.60

76.10

86.00

90.30

0

4.53

20.65

22.33

23.15

Notes (a)

HF = 23 kW/m2

A = 17.5 O~m

UC = 0.095 g/g

(a) HF'= external heat flux

A = airflow

UC = uranium concentration (gu/g combustible)

Run

Number

20

TABLE A.2.

Time. min

0

1.*12

2.57

4.48

9.*78

Burning Cellulose Contaminated with Air-Dried UNH

Cumulative Fractiopal

Release of U x 10~

.0

10.5

18.9

20.5

28.*9

Cumulative

Mass Loss., g

0

5.*27

11.65

13.16

14.53

Notes (a )

HF = 23 kW/m 2

22 0

1.00

2.25

8.25

0

7.91

8.58

9.62

0

8.22

12.00

14.57

HF = 13 kW/m2

(a) HF = external heat flux

A.2
TABLE A.3. TABLEA.3.Burning CelluloseýContaminated with Liquid UNH

Run

Number

3

Time, min

0

7.*00

12.00

17.*00

20.50

Cumulative Fractia pal

Release of U x 10

0

2.63

9.*10

13.18

14.47

Cumul ative

Mass Loss, g

0

25.81

62.47

93.75

101.69

Not es (a)

HF =23 kW/m2

5

18

0

20.00

32.00

39.00

44.50

0

4.87

5.*95

8.30

15.30

0

0.28

0.*50

4.33

7.52

0

1.51

2.*33

4.17

7.*04

0

29.91

64.07

84.91

108.79

0

5.97

13.17

24.34

38.04

HF= 7 kW/m2

HF = 23 kW/m2

(a) HF = external heat flux

A.3
TABLE A.4. TABLEA.4. Burning Contaminated Polychioroprene

Run

Number

DUO PowdE

7

9

11

Time, min

Cumulative Fractiogqal

Release of U x 10~

Cumulative

Fractional

Smoke Release Notes

Contaminant:

0

1.00

1.50

2.83

7.50

0

1.16

.2.33

4.00

10.00

0

8.25

13.58

15.*08

15.67

0

4.79

9.72

10.05

10.26

0

6.44

7.61

7.*76

8.*00

0

2.39

3.12

3.*54

3.71

0

0 .0435

0.*1149

0. 1294

0. 1393

0

0 .0862

0. 1312

0. 1418

O0.1484

0

0 .0154

0 .0498

0 .0670

0 .0703

Air-Dried UNH Contaminant:

24 0

1.00

2.*00

4.40

7.*50

0

1.19

3.86

4.16

4.*22

0..

0.*115

0 .0685

0 .0955

0.*1002

Liquid UNH Contaminant

8 0

0.66

1.25

2.*25

9.00

0

1.1

22.*7

32.3

34.7

0

0 .0152

0 .0576

0.0748

0. 1028

A.4
TABLE A.5. TABLEA.5.Burning Contaminant Polymethyl .Methacrylate

Run

Number

DUO powdi

6

13

Cumulative Fractional

Time, min Release of U x 100 Notes

contami nant:

0

14.50

18.00

24.50

31.50

0

9.*00

19.00

27.27

34.57

0

2.*92

3.15

3.16

3.18

0

2.*26

2.*84

2.92

2.98

Liquid UNH contaminant:

10 0

13.78

15.41

20.25

26.00

0

1.86

1.87

1.87

1.88

0

1.08

1.62

1.78

2.01

21 0

4.12

7.50

13.33

16.65

Air-dried UNH contaminant:

14 0

7.*25

10.53

13.33

16.60

0

0.26 1

0.606

0.634

0.645

A.5
TABLE A.6. TABLEA.6. Burning Polystyrene Contaminated with Liquid UNH

Run

Number

17

25

Time, min

0

9.00

10.00

13.50

18.53

0

6.65

7.75

9.25

12.75

Cumulative Fractio gal

Release of U x 10

.0

1.48

1.52

1.55

1.57

Notes

0

1.74

1.78

1.80

1.82

A.6
APPENDIX B

FUEL AND CONSTRUCTION MATERIAL PROPERTIES

IN FIRIN DATA BASE

TABLE B.1. TABLEB.1. Fuel Material Properties in FIRIN Data Base

Property

QCHEAT, kPI2

QRR, kW/m

HEATV, kJ/g

HEATC, kJ/g

WFC, fraction

WFH, fraction

WFO, fraction

WFCL, fraction

QFC, kW/m2

0v

5v

uv

QFRR, kW/m2

0v

sv

uv

XA, fraction

0v

sv

uv

XC, fraction

0'1

sv

uv

XR, fraction

0v

sv

UV

Polymethyl

methacryl ate

2600.00

11.00

1.63

25.20

0.60

0.08

0.*32

0.00

Polystyrene

1950.00

14.00

1.70

39.20

0.92

0.08

0.000

0.00

Pol1yv inyl

chloride

2300.00

21.00

2.47

16.40

0.38

0.05

0.000

0.57

Polychl oroprene

2440.00

8.00

2.35

25.00

0.54

0.06

0.00

0.40

Cell1ul ose

(wood)

420.00

16.00

3.60

17.70

0.48

0006

0.*46

0.000

Cellulosic

Materials (paper)

2000.00

12.00

3.20

14.00

0045

0.06

0049

0.00

Kerosene

100.00

8.000

1.50

46.00

0.87

0.13

0.00

0.00

12.00

6.00

0.00

40.00

20.00

0.00

0094

0.47

.0.00

0.64

0.32

0.00

0.30

0.15

0.00

13.00

6.50

0.000

66.00

33.00

0.00

0.68

0.34

0.00

0.40

0020

0.00

0028

0.14

0.000

26.00

13.00

0.000

37.00

18.50

0.00

0.35

0.17

0.00

0.19

0.09

0.00

0016

0.08

0.000

38.00

19.00

0.000

34.00

17.00

0.00

0.41

0.21

0.00

0.24

0.07

0.00

0.16

0.05

0.00

18.00

9.00

0.00

40.00

20.00

0.00

0.70

0.35

0.00

0.44

0.22

0.00

0.26

0013

0.00

7 .00

3050

0.00

6.00

3.00

0.00

1.00

0050

0.00

0.80

0.40

0.00

0020

0010

0.000

10.80

5.40

0.000

13.70

6.85

0.00

0.91

0.45

0.00

0.57

0.28

0.00

0.33

0.17

0.00
TABLE B.1.(cnd (contd)

Property

YFCO2, fraction

0v

sv

Uv

YFH 0, fraction

sv

uv

YFHCL, fraction

0v

sv

uv

YSMOK, fraction

0v

sv

uv

YFCO1, fraction

0v

sv

uv

YFCH4, fraction

0v

sv

uv

.Polymethyl

methacryl ate Polystyrene

Polyvi nyl

chloride

Cell1ul ose

Polychloroprene (wood)

Cellulosic

Materials (paper) Kerosene

w

2.10

1.47

0.00

0.69

0.49

0.00

0.00

0.00'

0 *000

0.210

0.254

0.000

0.011

0.005

0.000

0.001

0.005

0.000

2.*20

1.*54

0.00

0.45

0.*32

0.00

0.00

0.00

0.00

0.15

0.85

0.*00

0.021

0.035

0.000

0.02

.0.*10

0.*00

0.46

0.38

0.00

0.09

0.*08

0.00

0.19

0.*16

0.00

0.086

0.*277

0.000

0.039

0.019

0.000

0.02

0.*10

0.00

0.*50

0.25

0.00

0.*10

0.*05

0.*00

0.*19

0.*16

0.*00

0.*38

0.43

0.00

0.035

0.003

0.000

0.02

0.*10

0.*00

1.*30

1.04

0.00

0.43

0.*34

0.00

0.00

0.*00

0.*00

0.015

0.075

0.000

0.004

0.002

0.000

0.001

0.005

0.000

1.60

1.12

0.00

0.54

0.*38

0.00

0.00

0.00

0.00

0.001

0.002

0.000

0.003

0.001

0.000

0.002

0.010

0.000

2.80

1.96

0.00

1.04

0.73

0.00

0.00

0.00

0.00

0.087

0.200

0.000

0.030

0.015

0.000

0.005

0.002

0.000
TABLE B.1. (ctd (contd)

Parameter

QCHEAT

QRR

HEAT V

HEATC

WFC

WFH

WFO

WFCL

QFC

ovSvUv

QFRR

XAXC

XR

YFCO

YFH

YFHKC

YSMOK

YFCO 1

Y.FCH 4

Def in iti on

Energy required to generate combustible vapor air mixture

Fuel material surface reradiation

Heat required to generate a unit mass of vapor

Net heat of complete combustion

Weight fraction of carbon in fuel

Weight fraction of hydrogen in fuel

Weight fraction of oxygen in fuelWeight fraction of chlorine in fuel

Convective heat flux from flame to fuel

Over-ventilated (0? > 15%)

Semi-ventilated (15% >02 > 11%)

Under-ventilated (02 < 1f%)

Radioactive heat flux from flame to fuel

Combustion efficiency

Convective fraction of combustion efficiency

Radiative fraction of combustion efficiency

Fractional yield of carbon dioxide

Fractional yield of water

Fractional yield of hydrochloric acid

Fractional yield of smoke

Fractional yield of carbon monoxide

Fractional yield of methane
TABLE B.2.. Construction Material Properties in

Thermal Conductivity, ()Dens i

kJ/m.s.*K Emissivity~b k2/rn

COND C0NDM(a) EMIS RH0O

1.878E-3 1.0575E-6 0.94 2240.0

1.075E-3 0.0 0.75 2000.0

FIRIN Data Base

Heat Capacity,(c)

kJ/kg *K

CPCA CPCAM(a)

0.879 0.0

0.837 0.0

Concrete

Fi rebrick

Stainless

steel

Steel

Aluminum

Copper

Brass

13.84E-3

45.83E-3

202 .36E-3

387 .43E-3

1060.37E-3

-1 .52E-5

1 .56E-5

-1 .35E-4

5 .88E-5

-1.035E-4

0.24

0.16

0.06

0.*07

0.*09

7820.0

7850.0

2707.0

8940.0

8520.0

0.465

0.465

0.879

0.379

0.377

4.075E-4

4.075E-4

4.10E-4

1.2E-4

2.5E-4

(a) Extrapolation factor with change

(b) Siegal and Howell 1981

(c) Raznjevic 1976.

in temperature

REFERENCES

Raznjevic, K. 1976. Handbook of Thermodynamic Tables and Charts. McGrawHill, Inc., New York.

Siegal, R., and J. R. Howell. 1981. Thermal Radiation Heat Transfer.

2nd ed. McGraw-Hill, Inc., New York.

B .4
APPENDIX C

FIRIN CODE LISTING

C

C C

C FIRIN COMPUTER CODE C

C C

C FIRIN is developed to estimate both the radioactive and non- C

C radioactive source terms for fire accident scenarios in nuclear fuel C

C cycle facilities. The major FIRIN calculations include: C

C 1. Generation rate of: C

C smoke and soot mass C

C net energy deposition in gases C

C 2. Mass lost rate of combustion from fire C

C 3. Mass generation rate of radioactive particles C

C 4. Source particle characteristics C

C smoke C

C radioactive C

C FIRIN can be used independently to estimate fire generated releases, C

C the releases at the atmospheric boundary can be estimated in conjunct- C

C ion with the computer code FIRAC, which is developed at Los Alamos C

C National laboratory. C

C C

C C

C Dimension Block C

C C

PARAMETER NUM = 51

PARAMETER IIBO= 6

C

CHARACTER INPUTFILE*30

CHARACTERs 1 PLOTANS

REAL MASS C9,3) ,LR,N2X2IF,N2X2OF

C

C N2X2IF = NO. OF 2FT X 2FT FILTERS ON INLET FILTER BANK

C N2X2OF = NO. OF 2FT X 2FT FILTERS ON OUTLET FILTER BANK

C

COMMON/PARA1/RHOO CIS) ,CPCA (15) ,CPCAM (15)

COMMON/PARA2/COND (15),CONDM (15)

COMMON/PARA3/EMIS (15),TINIT,UUIN,WRADF

COMMON/PARA6/IFORM, I, TSTEP, QMR (11,10) ,JACT, J

COMMON/PARA6/FMH2O, FMHO2, FMHN2 ,FMCO1 ,FMCO2,LR,WR, ZR,

GZM.,TAVWH,TAVWCJ,TCAV,TFAV,PCOMP,FHL,FCLDPART(11),

OHLR,FRAC(B,12),DX,GRPART(2,12),A(2,12),B(2,12),

OAO(2,12) ,BO(2,12) ,ALOSS(2,12) ,BLOSS(2,12) ,FRACF(11),

@FRACW(11) ,FRACC(11) ,FLAG

COMMON/PARA7/FE, DELT, THL, TCL

C

DIMENSION OUTVEN(2) ,VEMASS (2) ,FMASS (2) ,WAMASS (2) ,CMASS (2)

C

DIMENSION TC (NUM, 2) ,YEC (HUM) ,YHC (NUM) ,YCC (lFM),

ITDIFC (HURM) ,TW(NUM,N1JM,2) ,QWA (NUM) ,TDIFW(NUMw,NUM),

2YEW(NUM,NUM) ,YHW(NUM,NUM) ,YCW(NUM,NUM) ,SMSZ(11),

3ZCL(10,4) ,TBCL(10,4) ,EQ(4) ,AFLOSS(8,2,12)

5, TF (HUM, 2) ,YEF (NUM) ,YHF (HUM) ,YCF (HUM)

6,TDIFF(NUM),ARER(10,4),WD(10,4),HEQ(10,4),ARHT(10,4)

7,WMASS(10,4) ,MATERE(10,4) ,HTF(10,4)

8,MJE(4) ,TE1 (10) ,QE1 (10) ,TE2 (10) ,QE2 (10) ,FAIL2(10) ,T12 (10)

9..VGAS2(10) ,VPWD(10) ,WH202(10) ,Q12(10) ,PF2(10) ,VOL(10)

C

DIMENSION OKFP (20) ,TFP (20) , KF4L (20) ,HFP (20) ,OKPFO (20) ,PFP (20),

C.1
1OKPFI (20) ,FPI4L (20) ,FPICL(20) ,FPOHLC20).,FPOCL (20) ,DFP (20)

2,ARBL(20) ,TE4(10) ,QE4(l0),,TL(l0) ,TE3:(10)4 , T13 (10) , FAIL3 (10),

8VQAS3(10) ,Wtt203(10) ,PF3(10) ,P121(1O) ,P-12(10) ,QE3(10) ,Q13(l0),

4P13 (10)

C

DIMENSION QFC(9,3) ,QFRR(9,3) ,QRR(9) ,HEATV (9) ,HEATC (9) ,QCHEAT(9),

1XA(9,3) ,XC(9,3) ,XR(9,3) ,YFC02(9,3) ,YFH2O(9,3) ,YSMOK(9,3)

2,YFCOI(9,3) ,YFCH4(9,3) ,WFC(9) ,WFH(9) ,WFO(9) ,WFCL (9),YFI4CL,(9,3)

C

DIMENSION TBURN(9,IIB0) ,BRATE(9,3) ,FLEL (9, 1180) JAREC (9,I180),,

INBO (9) ,QACT (9,3) ,QCON (9, 3),QRAD (9, 3),

20C02(9,3),GCOI(9,3),GH2O(9,3),SMOK(9,3),GHCL(9,3),GCH4(9,3)'

DIMENSION QRAD1 (29,10,1180) ,QRAD2 (6,10,1180) ,NRAD (7) ,QRAD3 (10),

1SQ(10,IIBO) ,QRAD4(10,l0) ,QRAD7 (10,1180) ,DFUEL(9,1IBO),.

ITEND (9,1180) ,TSTART(9,I180) ,XAX3 (29,10) ,VOLP (10) ,PDEN(10, 10),

2RBOIL (10) ,QRAD6(10,l0) ,QRADB(10,10) ,XMAX1(29,,10) ,XMAX2(29,10)

C

C :C

C Data, BlIockL iC

C C

C This block contains data on physical/chemical and pyrolysis/ -C

C combustion properties of fuels and physical properties of non-C

C combustibles. C

C C

C Th, mean values ofACHEAT are used here for Ignition concept C

C

DATA QCHEAT/2800.,1950.,2300.,2440.,'420.,2000.,100.,0.,0./

DATA QRR/11,124.,21.,8.,18. ,12.0,8. 0. ,0./

DATA, HEATV/1.63.,1.7,2.4,7,,2.36,3.8,3.2, 1.15,1,4_.1/

DATA HEATC/26.2,39.2,16.4,25.,17.7,14.0,46.0,0.,0./

DATA QFC/12.,13.,.,.,.7.0.,.0,

DATA QFRR/40.,66.,37,.,34.,40.,6.,13.7,0.,0,O.,

+20. ,33. ,28.6,27.,20.,3.,6.86,11 -0.0/

DATAXA94.,.504,,1,.1.0,

+.47, .34, .27,0.12, .36 6.,0.46,11.0.0/

DATA XC/.84,.40,.19,0.24,.'44,.80,0. 57,0.,0., ..32, .20, .09,0.07, .22, .4,0.28,11.0.0/

DATA XR/.3,.28,.16,0.18,.28,.2,0.33,0.,0.,

DATA YFC02/2.1,2.2, .48,0.5,1.3,1.6,2.8,0. ,0.,

+1.47,1.54, .38,0.25,1.04,1.12,1.96,11.0.0/

DATA YFH2O/.69,.45,.09,0O.1,.43$.54,1.04,0.,0., .. 49, .32, .08,0.06, .34, .38,0.73,,11.0.0/

DATA YFHCL/2.0.,.19,.19,7*0.,.16,.16,14.0,./

DATA YSMOK/.021,.26,.086,0.38,.015,.001,0.0871,0.,0.,

.254 .85,0. 277 ,0 .43, .075, .002,0. 2,11.0. 0/

DATA YFCO1/.011,.071$.039,0.036,.004,.0o3,0.03,0.,0.,

4.005, .035, .019,0.003, .002, .001,0.015,11.0.0/

DATA YFCHA/.001,.02,.02,.02,.001,.002,.005,0.:,0.,

.DATA WFC/.6,.92,.38,.54,.48,.45,.87,0.,0./

DATA WH.8.8.5.6.6.6.30,.

DATA WO.20,.0,4,90,.,.

DATA WFCL/2.0.,.67,.40,6.0./

DATA COND/2. -78E-3,1.075E-3,13.84E-3,45.83E-ý3,2.02.36E-3,

*387 .43E-3,106.37E-3,8.0./

DATA CONM/ý1.0675E-6,0.0,-1.52E-5,l.66E.-S, .-1.3SE-A,.5.88E- 6,

G-1.35E-4,6u0./

C.2
DATA EMIS/.94,.75,.24,.18,.06,.07,.09,S.0./

DATA RHOO/2240.,2000.,7820.,7850.,2707.,8940.,8520.,8.6./

DATA CPCA/.879,.837,.465,.465,.879,.379,.379,8*0.f

DATA CPCAM/2*0. ,2*4 .075E-4,4.2E-4,2.2E-4,2.5E-4,8*0.0/

DATA DPART/0.1,0.173,0.387,0.592,0.794,0.995,1 .48,3.48,7.75,

014.14,20./

DATA SMSZ/0. ,0.045,0.115,0.24,0.24,0.11,0.28,0.17,3*0./

C

C READ-IN NAME OF INPUTFILE

C

TYPE *,'. ENTER NAME OF INPUT FILE:

READ(s, 'CA)') INPLJTFILE

C

C C

C Open unit files for output data C

C C,

OPEN CUNrT=2, NAME:INPUTFILE, TYPE='OLD' ,READONLY)

DPEN(UNIT=3,NAME= 'RSTHL .DAT' ,TYPE='NEW' ,FORM='IFORMATTED')

OPEN(Ut4IT=4 ,NAME='RSTCL .DAT' ,TYPE='NEW' ,FORM='FORMATTED')

OPEN(UINIT=5,NAME='SMKHL .DAT' ,TYPE='NEW' ,FORM='FORMATTED')

OPEN(UNIT=7,NAME= 'SMKCL .DAT' ,TYPE='NEW' ,FORM='FORMATTED')

OPEN (UNrT=8, NAME= 'RSZHL .DAT' ,TYPE= 'NEW', FORM=' FORMATTED')

OPENCUONIT=9,NAME='RSZCL .DAT' ,TYPE='NEW' ,FORM='IFORMATTED')

OPENCUNIT=11 ,NAME='SSZHL .DAT' ,TYPE='NEW' ,FORM=-'FORMATTED')

OPEN(UINIT=13,NAME='SSZCL .DAT' ,TYPE='NEW' ,FORM='FORMATTED')

OPEN(UNIT=2.S,NAME='PRINT .DAT' ,TYPE='NEW' ,FORM=-'FORMATTED')

OPEN(UNIT=12,NAME='ARAD.DAT',TYPE='NEW' ,FORM=-'FORMATTED')

OPEN(U)NIT=14 ,NAME='ASMK .DAT' ,TYPE='NEW' ,FORM='FORMATTED')

C

C

C Read and write input data f or program execution C

C C

READ(2,*) PLOTANS,TSPEC,DELT, MIBO,IGNITE,IPRINT, CMJECI) ,1=1,4)

PRINT * , 'TSPEC=',TSPEC,' DELT=',DELT,' MIBO=',MIBO,' IGNITE=',

i-IGNITE,' rPRINT=',IPRINT,' (MJE(I),I=1,4)',(MJE(I),1=l,4),

+' PLOTANS = ',PLOTANS

C

C....OPEN PLOTTING FILES IF USER DESIRES

C

rF(CPLOTANS .EQ. 'Y') .OR. (PLOTANS .EQ. 'y')) THEN

OPENCUNIT=15 ,NAME= 'PLOTTINGDATA_1 .DAT' ,TYPE='NEW',

FORM='IFORMATTED' ,RECL=160)

OPENCUNIT=16,NAME= 'PLOTTINGDATA_2.DAT' ,TYPE='NEW',

FORM= 'FORMATTED' ,RECL= 180)

END IF

C Input IGNITE=0 for using Burning Order concept

C Input IGNITE=1 for using Ignition Energy concept

READ(2,*) ((FUEL(I,IBO),1=1,9),1BO=1,MIBO)

PRINT * '((FUEL(I,IBO),1=1,9),IBO=1,MIBO)'

PRINT * ((FUEL (1,180) ,1=,9) ,IBO=1,MIBO)

READ(2,*) ((AREC(I,IBO),I=1,9),1BO=1,MIBO)'

PRINT * ,'((AREC(I,IBO) ,i=1,9),iBo=i,Mrso),

PRINT * ((AREC (1,180),I=1,9) ,IBO=1,MIBO)

C.3
DO 990 IBO=1,MIBO

C Input fuel characteristics for fuels other than those in data base

DO 990 J=8,9

.IF (FUEL(J,IBO) .GT.0.)TNEN

IF (QCHEAT(J).GT.O.)GO TO 990

READ(2,s)QCHEAT(J) ,QRR(J) ,HEATV(J) ,HEATC(J) ,WFC.(J),

4WFH (J) , WFO (J) , WFCL (J)

READ(2,e)(QFCCJ,K),K=1,3),CQFRR(J,K),Ij1,3),CXACJ,K),K=1,3)

READ(2,e) (XC(J,K) ,K=1,3) ,(XR(J,K) ,K=I ,3),,(YFC02(J,K) ,K=1,3).

READ(2,e)(YFH2O(J,K),K=1,3),(YFHCL(J,K),l<=1,3),(YSMOK.(J,K),

4K=2,3)

READ(2,*) (YFCO1(J,K),K=1,3), (YFCI44(J,K),K=1,3)

PRINT * , 'QCHEAT(J)=' ,QCHEAT(J),' QRR(J)=',QRR(J)'

PRINT * , HEATV(J)=',HEATV(J),' HEATC(J)=',HEATC(J).

PRINT * , ' WFC(J)=',WFC(J)

PRINT ik , ' WFH(J)=',WFH(J),' WFO(J)=',WFO(J)

PRINT * , IWFCL(J)=',WFCL(J)

PRINT * , '(QFC(J,K),K=1,3)',(QFC(J,K)-,K=1,3)

PRINT * , (lQFRR(J,K),K=1,3)',(QFRR(J,K),K=1,3)

PRINT * , '-.CXACJ,K),K=1,3)',CXACJ,K),K=1,3)

PRINT * , '(XC(J,K),K=1,3)',(XC(J,K),K=1,3)

PRINT * , '(XRCJ,K),K=1,3)',(XR(J,K),K=1,3)

PRINT * , 'CV'FCO2CJ,K),K=1,3)',(YFCO2CJ,K),K=1,3)

PRINT * , '(YFH2O(J,K),K=1,3)',(YFH2O(J,K),K=1,3)

PRINT * , '(YFHCL(J,K),K=1,3)',(YFHCL(J,K).,K=1,3)

PRINT * , '(YSMOK(J,K),K=1,3)',(YSMOK(J,K),K=1,3)

PRINT * , '(N'FCOI(J,K),K=1,3)',(YFCOI(J,K),K=1,3)

PRINT * , '(YFCH4(J,K),K=1,3)',(YFCH4CJ,K),K=1,3)

END IF

990 CONTINUE

READ C2,*) LR, WR, ZR,XCEIL,XWALL,XFLOOR,MATERC, MATERW,MATERF

PRINT * , 'LR=',LR,' WR=',WR,' ZR=',ZR

PRINT * , 'XCEIL=',XCEIL,,' XWALL=',XWALL,' XFLOOR=',XFLOOR

PRINT * , 'MATERC= , MATERC,' MATERW-' ,MATERW,' MATERF=' ,MATERF

IF(MATERC.LT.B)GO TO 900

C Input building material characteristics if other than those in data base

M=-MATERC

READ (2,a) COND( M) ,CONOM CM) ,EMIS CM) ,RHOO CM) ,CPCA CM) ,CPCAM CM)

PRINT * , 'COND CMATERC)=' ,COND CM),' CONDM(MATERC) =',CONDM(M)

PRINT * , 'EMISCMATERC)=' ,EMIS(M),' RHOOCMATERC)=,'RHOOCM)

PRINT * , 'CPCA(MATERC)=' ,CPCA CM),' CPCAM(MATERC)=',CPCAM(M)

900 IF(MATERW.LT.8)GO TO 901

IF(COND(MATERW).NE.O.)GO TO 901

M=-MATERW

READ (2,*) CONDCM) ,CONOM CM) ,EMIS (M) ,RHOO CM) ,CPCA CM) ,CPCAM CM)

PRINT * , 'COND(MATERW)=' ,COND(M),' CONDM(MATERW)=',CONOM(M)

PRINT * , 'EhIIS (MATERW) =',EILIS M),' RHOO (MATERW)=' ,RIOO (M)

PRINT * , 'CPCA(MATERW)=' ,CPCA CM),' CPCAM(MATERW)=' ,CPCAM(M)

901 IF(MATERF.LT.S)GO TO 902

IF(COND(MATERF).NE.0.)GO TO 902

M=MATERF

READ(2,*)COND(M) ,CONDM(M) ,EMIS(M) ,RHOOCM) ,CPCA(M) ,CPC 'AMCM)

PRINT * , 'COND(MATERF)=' ,COND (M),' CONDM(MATERF) =' ,CONDM(M)

PRINT * , 'EMIS CUATERF) =' ,EMIS CM),' RHOO (MATERF)=' ,RHO00 M) '

PRINT * , 'CPCA(MATERF) =',CPCA (M),' CPCAM(MATERF)=', CPCAM CM)

902 CONTINUE

CA4
C Input initial T, P, and flow of compartment

READ(2,'*) NFP,P1,P2,TINIT,PINIT,ZIF,ZOF,ZFIRE,VIF,EQUIP,EFFIC

PRINT * ,'NFP=',NFP,' P1=',PI,, P2=',P2,' TINIT=',TINIT

PRINT * ,'PINIT=',PINIT,' ZIF=',ZIF,' ZOF=',ZOF

PRINT * ,'ZFIRE=',ZFIRE,' vIF=',vIF,' EQUIP=',EQUIP,' EFFIC=',

DEFFIC

READ (2, .)TFO,TCO,TWO,N2X2IF,N2X2DF

PRINT *,'INITIAL T OF FLOOR=',TF0,' CEILING=',TCO,' WALL=',

OTWO

PRINT * , 'NO.ý OF 2FT X 2FT INLET F-ILTERS =',N2X2IF

PRINT * , 'NO. OF 2FT X 2FT OUTLET FILTERS =',N2X2OF

IF(IGNITE.EQ.0) GO TO 1-000

READ(2,*) (NBO(I) ,I=1,9)

PRINT * (NBO(I),I=2,9)=',(NBO(I),I=1,9)

C Input NBO(I)=O for material burns at the start of the fire

C Input NBO(I)=l for combustibles that are at risk and they can

C contribute to the f ir* via Ignition Energy concept

C Input NBO(I)=2 for any of the nine combustible types that will not

C contribute to the fire at all

C Input NBO(I)=3 for material types that burn at the start of the fire

C and also at risk due Ignition Energy concept

1000 IF(EQUIP.EQ.0.0) GO TO 1005

DO 1004 IE=2,4

IF(MJE(IE).Eq.o.)GO TO 1004

K=MJE CIE)

READ(2,*) (VD(JE,IE) ,JE=1,K)

PRINT * , '(WD(JE,IE),JE=1,K)',(WD(JE,IE),JE=1,K)

READ (2,*) (HEQ(JE,IE) ,JE=1,K)

PRINT * , '(HEQ(JE,IE),JE=1,K)', (HEQ(JE,IE) ,JE=1,K)

READ(2,*) (HTF(JE,IE),JE=1,K)

PRINT * , 'QITF(JE,IE),JE=1,K)',(HTF(JE,IE),JE=1,K)

READ (2,*) (MATERE(JE,IE) ,JE=1,K)

PRINT * (hIATERE(JE,IE) ,JE=11K) ',CMATERECJE,IE) ,JE,=1,K)

DO 999 JE=1,K

IF(MATERE(JE,IE).LT.7)GO TO 999

C Input construction material characteristics if other than those in data base

M=-MATERE(JE, IE)

IF(COND (M).NE.0.)GO TO 999

READ(.2,*)COND(M) ,CONDM(M) ,EIIS(M) ,RHOO(M) ,CPCA(M) ,CPCAM(M)

PRINT * , 'COND(MATER)=',CON'U(M),' CONDM(MATER)=',CONDM(M)

PRINT * , 'EMIS(MATER)=' ',EMIS(M),' RHDOOMATER)=',RHOO(M)

PRINT * , 'CPCA(IAATER)=' ,CPCA(M),' CPCAM(MATER)=' ,CPCAU(M)

999 CONTINUE

READ(2,*) (WMASS(JE,IE),JE=1,K)

PRINT * , '(WMASS(JE,IE),JE=1.,K)-',(WhIASS(JE,IE) ,JE=1,K)

IF(IE.GT.1)GO TO 1001

READ (2,.) (TEl (JE) ,JE=1,K)

PRINT * , 'CTE1(JE),JE=1,K)', (TEl (JE) ,JE=1,K)

GO TO 1004

1001 If CIE.GT.2)GO TO 1002

READ (2,.) (VGAS2(JE) ,JE=1,K)

PRINT * , '(VGAS2 (JE) ' JE=1 ,K).', (VGA.S2 (JE) ,JE=l ,K)

READ(2,*) CVPWD(JE),JE=1,K)

PRINT *,'(VPWtD(JE) ,JE=l,K) ',(VPWD(JE) ,JE=l,K)

READ(2,*) (W11202(JE) ,JE=1,K)

PRINT * , '(WH202(JE) ,JE=1,K) ',(WH202(JE) ,JE=1,K)

C.5
READ (2,) (TE2 (JE) , JE= 1,K)

PRINT * ,'(TE2(JE),JE=1,K) ', (TE2(JE) ,JE=1,K)

READ (2,) (T12 (JE) , JE=-1,K)

PRINT * , (TI2(JE),JE=1,K) ',(TI2(JE) ,JE=1,K)

READ(2,*) (PF2(JE) ,JE=1,K)

PRINT * , '(PF2(JE) ,JE=1,K)', (PF2(JE) ,JE=1,K)

GO TO 1004

1002 IF(IE.EQ.4)GO TO 1003

READ (2,.) (VGAS3(JE),JE=1,K)

PRINT * , '(VGAS3(JE) ,JE=1,K) ',(VGAS3(JE) ,JE=1,K)

READ (2,..)(WH203(JE) ,JE=1,K)

.PRINT a (WH203(JE) ,JE=1,K)', (WHi203(JE) ,JE=1,K)

READ (2,. (TE3 (JE) , JE-1, k)

PRINT * (TE3(JE),JE=1,K)',(TE3(JE),JE=1,K)

:READ (2,.) (TI3(JE),JE=1,K)

PRINT a (TI3(JE),JE=1,K) , (TI3(JE) ,JE=1,K)

READ (2,.) (PF3(JE) ,JE=1,,K) -PRINT * , '(PF3(JE) ,JE=1,.K) ',(PF3(JE) ,JE=1,K)

GO TO 1004

1003 READ(2,*)(VOL(JE),JE=1,K)

PRINT * . '(VOL(JE).,JE=1,K) ', (VOL(JE) ,JE=1,K)

READ (2,. (TE4 (JE) , JE=1, K)

PRINT * , (TE4(JE),.JE=1,K) ',(TE4(JE),.JE=1,K).

READ(2,*) (TL(JE) ,JE=1,K)

PRINT * , '(TL(JE),JE=1,.K)', (TL(JE) ,JE=1,K)

1004 CONTINUE

1005 -XF(NFP.EQ.0) GO TO 1010

C Input alternate flow path parameters

READ(2,*) (TFP(IFP) ,IFP=1,NFP)

PRINT * , '(TFP(IFP) ,IFP=1,NFP) ', (TFP(IFP) ,IFP=1,NFP)

READ(.2,.) (IWP(IFP) ,IFP=1,NFP)

PRINT * , '(HFP(IFP) ,IFP=1,NFP)', (HFP(IFP) ,IFP=1,NFP)

READ (2,.) (PFP (IFP) ,IFP= , NFP)

PRINT . , '(PFP(IFP) ,IFP=1,NFP) ',(PFP(IFP) ,IFP=1,NFP)

READ(2,*) (DFP(IFP) ,IFP=1,NFP)

PRINT * , '(DFP(IFP) ,IFP=1,NPP)',(DFP(IFP) ,IFP=1,NFP)

C.Input radioactive source term parameters

1010 READ(2,*) (NRAD(J),J=1,7).

PRINT. '(NRAD(J),J=1,7)',(NRAD(J),J=1,7)

C

C INITIALIZE QRAD ARRAYS

C

DO 1023 J1=1,II BO

DO 1013 J2=1,10

DO 1021 J3=1,29

1011 QRAD1(J3,J2,J1)=0.0

DO 1012 J3=106.

1012 QRAD2(JS,J2,J1)=0.0

,1013 QRAD7(J2,JI)=0.0

DO 1016 JI=1,10

DO 1014 J2=1010

QRAD4 (J2,JI)=0.0

QRADS(J2,J2)=O.0

1014 CONTINUE

1016 QRAD3(J1)=S.O

C

DO 1020 J=1,7

CA6
IF(NRAD(J).EQ.0)GO TO 1020

DO 1020 K=1,NRAD(J)

rF(J.GT.2)GO TO 1015

IF(J.GT.1)GO TO 1017

READ(2,*) IFORM,I,JACT,IBO

PRINT * , rIFORM--',IFORM,' I=',I,' JACT=',JACT,' IBO=',IBO

NJ=(( IFORM. 10) -10)41

READ(2, .)QRAD1 (NJ,JACT,IBO)

PRINT s , 'QRADI=-',QRAD1(NJ,JACT,IBO)

GO TO 1020

1017 READ (2,*)IFORM,I,JACT,IBO

PRINT *, 'IFORM=',IFORM,' I=',I,'JACT='-,JACT,' IB80=',1B0

NJ= (1-6) (IFORU-1) .3

READ (2, .)QRAD2(NJ,JACT,IBO)

PRINT * , 'QRAD2=',QRAD2(NJ,JACT,IBO)

GO TO 1020

1015 IF(J.EQ.3)READ(2,.)JACT,QRAD3(JACT)

IF(J.EQ.3)PRINT * , 'JACT=',JACT,' QRADS=',QRAD3(JACT)

IF(J.EQ.4)READ(2,*)IVES,JACT,QRAD4(IVES,JACT)

IFCJ.EQ.4)PRINT * , 'IVES=',IVES,' JACT=',JACT,

+' QRAD4=' ,QRAD4 (IVES,JACT)

rF(J.EQ.5)READ(2,'.)IVES,JACT,QRADS(IYES,JACT) ,VOLP(IVES),

*PDEN(IVES,JACT)

IF(J.EQ.5)PRINT a,'IVES=',IVES,' JACT=',JACT,

+' QRAD6=' JQRAD5 (IVES,JACT),' VOLUME= ',VOLP (JE), +' POWDER DENSITY = ',PDEN(IVES,JACT)

IF(J.EQ.8)READ(2,.)IVES,JACT,QRADB(IVES,JACT)

IF(J.EQ.8)PRINT * , 'IVES=',IVES,' JACT=',JACT,

+' QRADS =',QRAD8(IVESJACT)

rF(J.EQ.7)READ(2,.s)JACT,IBO,QRAD7(JACT,IBO) ,SQ(JACT,IBO)

IF(J.EQ.7)PRINT s , 'JACT=',JACT,' IBO=',IBO,

e'QRAD7=' ,QRAD7(JACT,IBO),' SQ=',SQ(JACT,IBO)

1020 CONTINUE

CLOSE (UNIT=2)

C

C C

C Format Block C

C

200 FORMAT(1H1,49X,'OUTPUT FOR RADIOACTIVE SOURCE TERM',/)

205 FORMAT(IH ,3X,'TIME ACCUMULATED MASS (G) ON:',/,4X,'(S)',

+5X,'FLOOR',5X,'WALL',5X,'CEILING',4X,'VENTS ENVIRON')

210 FORMAT(131('_') ,/)

245 FORMAT(1H ,F8.2,12(1X,E9.3))

250 FORMAT(1HI,49X,'OUTPUT FOR COMPARTMENT EFFECTS'/)

255 FORMAT(1H ,11X,'COMPARTMENT OXYGEN HOT LAYER VOLUMETRIC'

+,' FLOW RATE',4X,'HOT LAYER',4X,'MASS BURN HEAT GEN. HEAT 1,

*'LOSS HEAT TO',/,SX,'TIME',4X,'PRESSURE',8X,'CONC.',5X,

*'THICKNESS' ,5X, 'INLET' ,7X, 'OUTLET' ,4X, 'TEMPERATURE' ,SX, 'RATE',I +7X,'BY FIRE',SX,'TO WALLS FIRE GAS',/,4X,'( SEC ) ( ATM ),

i-3X,'(VOL FRACT)',4X,'( M )',5X,'( M**3/S )CMs*3/S )',4X,'( F )1

aSX,'( G/S )',5X,'( KW )',2(6X,'( KW ))

270 FORMAT(1X,F9.2,10(1X,F11.4))

275 FORMAT(lHl,49X,'OUTPUT FOR FIRE SOURCE TERMS',//)

305 FORMAT(' COMBUSTIBLE TYPE ',12,' HAS IGNITED AT TIME: '

1 F10.4,1 SEC',/)

312 FDRMAT(1X,F9.2,8(2X,E9.3))

315 FORMAT(' ALL BURNING HAS STOPPED AT TIME: ',F10.4,' SEC WITH '

1F5.1,' PERCENT OF ALL COMBUSTIBLES CONSUMED IN THIS FIRE '/

320 FORMAT(' ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY:',

1 F10.4,' SEC',/)

C.7
325 FOIRMAT(1HO,'TIME EXCEEDS USER SPECIFIED TIME AT:',Fl0.4,' SEC')

370 FORMAT C1H ,67X, 'PARTICLE DIAMETER (MICRONS) ,/,4X, 'T.IME',

011 (2X,F9.3) ,4X, 'TOTAL')

390 FORMAT(1H2,49X,'OUTPUT FOR SMOKE SOURCE TERM',/)

395 FORMAT(IH ,'MASS IN HOT LAYER, G')

400 FORMAT(1H ,'MASS IN COLD LAYER, G')

405 FORMAT(IH ,13X, 'AIRBORNE' ,3X, 'GENERATED ENTRAINED' ,SX,

O'TOTAL',5X,'AIRBOR11E FRACTION OF LOSSES DUE TO:',/,4X,'TIME,S',

OEX,'AT TO ()BY FIRE (+) W PLUME (-)"LOSSE .S (=) AT T',7X,

G'SETTLING B.DIFFUS THERMOPH. DIFFUSID.-OUT VENT'>y

410 FORMAT(1H ,F9..2,53,92,(XF.

415 FORMAT(IH ,12X,"'AIRBORNE HOT LAYER TOTAL',SX,'AIRBORNE',

§3X,'FRACTION'OF LOSSES DUE TO"',/4X 'TIME,S1,BX,'AT TO0. +)'

0' SETTLING(-) LOSSES'(= AT T',4X,'SETTLING OUT VENT',2X,

G'PL 'UME GAS')

420 FORMAT(IH ,F9.2,4(3X,E9.2),3(1X,F9.4))

C.

C C

C Initializati~on and Parameterization Block C

C C

NFLAGC=1

NFLAGW=-0

NFLAGF=O

FLAG=0.

QE=0 .0

QFA=0.0

EIGN=0.0

UMIN = 5.OE-03 IWinimum convective heat transfer coefficient,kW/K

A1=1000. /99.

R=8.208E-5 'Gas constant,atm*M3/gmo Ie*K

CPL=4.184E-03 !Specific heat of water,kJ/cm a K

CPAIR=2.88E-02 !Specific heat of air,kj/gmole*K

ELV=2.26

CP=33 .SE-3

GR=9.8 !Acceleration due to gravity,M/s2

SIG=5.669E-11 'Stefan-BolItzmnann constant,kW/M2*K4

TSTEP=DELT

JACTO=0

TSTEPO=0 .0

ITSTEP=1

QLOSSR=0.0

TQNETR=0 .0

TQACTR=0.0

TMASSN_0 .0

TMASSR=0 .0

TGRAD=0 .0

GTMASS=0.

P1=3.1415927

DO 1035 ISIZE=1,11

1035 DPART(ISIZE)=DPART(ISIZE)*1.E-4 !CONVERT OPART TO CM

DO 10386 JT=_1,2

DO 1038 ISZ=lil2

AO(JTISZ)=_0.

Be (JT, ISZ) =0.

1036 CONTINUE

VOLRM=-LR*WR*ZR

AMCL= (PINIT*VOLRM)/I(R*TINIT)

AMI4L=0.

FM02=.21

THL=TINIT

C.8
TCL=TINIT

PCOMP=PINIT

TA=TINIT

CH02=0.

CHN2=0.

CHCOI=0.

CHCO2=0.

CHCH4=0.

CHH2O=0.

CHHCL=0.

CCN2=0 .79*AMCL

CCO2=0 .21*AMCL

WSMIF=*0.

WSMOF=0.

WRADIF=0.

WRADOF:0.

A WI=LR *ZR

AW2=WR*ZR

AFLOOR=LR*WR

DX=ZR*100./(NUM-1) !DX IN CM

DXC=XCEIL/ (HUM-i)

DXW=-XWALL/ (HUM-i)

.DXF=XFLOOR/ (NUM-i) VC=AFLOOR*XCEIL*Al

VF=AFLOOR*XFLOOR*A1

CKDC=COND (MATERC) /DXC

CKDW=COND (MATERW) /DXW

CKDF=COND (MATERF) /DXF

DO 2040 JC=1,NUM

TC (JC,1) =TCO

TFC(JC,1) =TFO

YEC (JC)=0 .0

YHC (JC)=0.0

YCC (JC)=0.0

YEF(JC)=0.0

YHF(JC)=0 .0

YCF(JC)=0.0

DO 1040 IW=1l,NUM

TW(IW,JCI)=TWO

YEW(IW,JC)=0.0

YHW(IW,JC)=0.0

YCW(Iw, JC) '0 .0

1040 CONTINUE

TECL=0.

DO 104i IE=1,4

DO 1045 JE=1,10

TBCL(JE,IE)=O.

1045 CONTINUE

DO 1050 JE=1,10

FAIL2 (JE)=0 .0

FAIL3 (JE) =0.0

1050 CONTINUE

DO 1055 J71=1,2

FUASS (JT) =0.

WAMASS (JT) =0.

CUASS (JT) =0.

OUTVEN (JT) =0.

VEMASS (JT) =0.

1055 CONTINUE

VOF=-VIF

RES.ISTI= (F'-PINIT) /VIF

CAg
RESISTO = -(PINIT-P2)/VOF

THLUC=l. 8*TINIT-460 .0

C

C C

C Write output for time=0

C

WRITE (3, 200)

WRITE(3, 395)

wRITE(3,406)

wRITE(3,410)TSTEPO,AO(1,12) ,GRPART(1,12)*DELT,,AFLOSS(8.,1,12),

OALOSS(1,12) ,A(1,12), (AFLOSS(M,2,12) ,M=1,5)

WRITE (4,200)

WRITE (4.,400).

WRITE(4,415)

WRITEC4,420)TSTEPO,BO(1,12) ,AFLOSS.(1,1,12),BLOSS.(1,12),B(1,l2),

O (AFLOSS (U,1, 12) ,M=6 ,8)

WRITE (5,390)

WRITE (5, 395)

WRITE(6,405)

WRITE(5,410)TSTEPO,AO(2,12) ,ORPART(2,12)*DELT,AFLOSS(8,2,12),

OALOSS(2,12) ,A(2,12), (AFLOSS(M,2,22) ,M-l,5)

WRITE(7, 390)

wRITE(7,400)

wRITE(7,415)

WRITEC7,420)TSTEPO,BO(2,12) ,AFLOSS(1,2,12) ,BLOSS(2,12) ,B(2,12),

O(AFLOSS(M,2,12) ,U=6,8)

WRITE(B, 200)

WRITE (8, 396)

WRITE(8,370), (DPART(I)*1.E4,I=1,11)

WRITE(8,245)TSTEPS, (A0(I,M) ,M=-1,12)

WRITE (9, 200)

WRITE(9,400)

WRITE(9,370), (DPART(I)*1.E4,I=1,11)

WRITE(9,245)TSTEPO, (B0(1,M) ,M=1,12)

WRITE(11, 390)

WRITE(11,395)

WRITE(11,370), (DPART(I).1.E4,1=l,21)

wRITE(11,245)TSTEPO, (AO(2,M),MU-l,12)

WRITE (13,390)

WRITE (13,400)

WRITE(13,370) ,(DPART (I) u..E4,1=1,11)

wRrTE(13,246)TSTEPO, (B0(2,M),M=1,12)

WRITE (10,260)

WRITE(10,266)

WRITE (10,210)

wRITE(10, 270) TSTEPO ,PINIT,FMO2,ZHL,VIF, VOF,THLUC,TMASSR,TQACTR,

+QLOSSR, TQNETR

WRITE(12,200)

WRITE(12,205)

WRITE(I.2,245)TSTEPO,FMAkSS(l) ,WAMASS(1) ,CMA.SS(l) ,VEM&SS(1),

GOUTVEN (1)

wRrTE(14 ,390)

WRITE(14 ,206)

wRITE(14,245)TSTEPOFMASS(2) ,WAMASS(2) ,CUASS(2) ,VEMASS(2),.

@OLITVEN (2)

C

C C

C Parameters for heat transfer to equipment C

C C

C.*10
IF(EQUIP.EQ.0.0) GO TO 1085

ARAD=0.0

DO 1080 IE=1,4

DO 1080 JE=1,10

ARER(JE, IE)=WD(JE,IE)*HEQ(JE,IE)

ARAD=ARAD+ARER (JE, IE)

ARHT CJE, IE) =PI*WD (JE, IE) *HEQ(JE, IE) +PI*(WO (JE, IE) **2/2 .0)

C

C ARHT(JE,IE)=HEAT TRANSFER AREA (OUTSIDE SURFACE AREA)

C

ZCL (JE, IE) =HTF (JE, IE) 4-0.S*HEQ(JE, IE)

1080 CONTINUE

C

C C

C Fire source termwcalculation C

C C

1085 CONTINUE

J= 1

TFUEL=0 .0

DO 1070 IBO=1,MIBO

DO 1070 I=1,9

TFUEL=TFUEL*FUEL(I,I8O) !Calculat~e t~ot~al risking fuel

1070 CONTINUE

DO 1080 IBO=1,MIBO

DO 1080 I=1,9

OFUEL (I, 80) =FUEL (I, IBO)

BRATE(I,J)=(QE*QFC(I,J)4*QFRR(I,J)-QRR(I))*AREC(I,IBO)

1/HEATY (I)

IF(BRATE(I,J).GT.0.0)GO TO 1076

TBURN(I, 80) =0.

GO TO 1080

1075 TBURN(I,180) =FUEL (I, 80) /BRATE(I, J)

1080. CONTINUE

C

C *a*DO LOOP FOR BURNING ORDERS ..

C

IF (IGNITE. EQ.1) MIBO=I

1085 DO 151S IBO=I,MIBO

DO 1090 K=1,9

TSTART (K,180) =TSTEP

1090 CONTINUE

1100 BTMAX=0.

DO 1105 I=1,9

IF (TBURN(I,IBO).LT.BTMAX) GO TO 1105

BTMAX=TBURN (1,180)

1105 CONTINUE

C

C Calculate thermal diffusivitie's for heat transfer equations.

C

DO 1095 JW=1I,NUM-1

CALL THERMD(TC(JW,1) ,TDIFC(JW) ,MATERC)

CALL THERUD (TF (JW,1) ,TDIFF(JW) ,hATERF)

DO 1092 IW=1,NUM-2

CALL THERMD (TW(IW, JW,1) ,TDIFW(IW, JW) ,MATERW)

1092 CONTINUE

1095 CONTINUE

C

C.11
EIG=-QFA*DELT

EIGN=EIGN+EIG !Calculate total ignition energy available

TAREC=0 .0

DO 1120 I=1,9

C Identify ignition of combustibles at risk due to room fluxes

IF (NBO(I).EQ.1 .AND. EIGN.GE.QCHEAT(1)

1 .OR. NBO(I).EQ.3 .AND. EIGN.GE.QCHEAT(I) )THEN

FUEL (1,1) =FUEL(I, 2) .iFUEL(I , )

OFUEL (I,1)=FUEL (I,1)

AREC (I,1) =AREC (1,2) .AREC (1,1)

FUEL(I,2)=0.

NBO (I) =0

wRITE(3,305) I,TSTEP

wRITE(4 ,305) I,TSTEP

wRITE(5, 305) I,TSTEP*

WRITE(7, 305) I,TSTEP

WRITE(8,306) I,TSTEP

WRITE(9,305) I,TSTEP

WRITE(11,305) I,TSTEP

WRITE(13,305) I,TSTEP

WRITE (10, 305) I, TSTEP

C Identify contaminated combustibles for radioactive release calculation

IF (NRAD(1).EQ.0 .AND. NRAD(2).EQ.0)GO TO 1115

DO 1110 JACTh1,10

DO 1111 IFORM=1,3

NJ= ((IFORMalO) -10) +I

QRAD1(NJ,JACT,1)=QRADI(NJ,JACT,2).QRADI(NJ,JACT,l)

1111 CONTINUE

DO 1110 JFORM=1,2

NJ=C(I-8) .. (JFORM-1) *3

QRAD2 (NJ, JACT, 1) =QRAD2 (NJ, JACT,2) +QRAD2 (NJ, JACT, 1)

2110 CONTINUE

211 ENDIF

TAREC=TAREC+AREC (I, IBO)

1120 CONTINUE

IF (TAREC .GE. AFLOOR) TAREC=AFLOOR

IF (BTMAX.EQ.0.)GO TO 1515

IF (TSTEP.GT.TSPEC)GO TO 1530

J=1

QE=-QFA !QE HAS UNIT OF KW/M2

DO 1135 I=1,9

IF( FMO2 .GE. 0.15 ) GOTO 1125 !Interpalation of values

SCALE = 25.0 * ( 0.15 FMO2 )

QFC(I,3) = QFC(I,1) - (QFC(I,1) - QFC(I,2) )*SCALE

QFRR(I,3) = QFRR(I,1) ( QFRR(I,1) - QFRR(I,2) ) * SCALE

XA(I,3) = XA(I,1) - CXA(I,1) - XA(I,2) ) * SCALE

XC(I,3) = XC(I,1) - CXC(I,1) - XC (1,2) ) * SCALE

XR(I,3) = XR(I,1) - CXR(I,1) - XR(I,2) ) * SCALE

YFC02(I,3) = YFC02(I,1) - ( YFC02(I,1) - YFCO2(I,2) ) * SCALE

YFC01(I,3) = YFCO1(I,1) - ( YFCO1(I,1) - YFCO1(I,2) ) * SCALE

YFHCL(I,3) = YFHCL(.I,1) - ( YFHCL(I,1) - YFHCL(I,2) ) * SCALE

YSMOK(I,3) = YSMOK(I,1) - ( YSMOK(I,1) - YSMOK(I,2) ) * SCALE

YFH20(I,3) = YFH20(I,1) - ( YFH2O(I,1) - YFH2D(I,2) ) * SCALE

YFCI44(I,3) = YFCH4(I,l) - ( YFCH4(I,1) - YFCII4(I,2) ) * SCALE

J=3

IF( FMO2 .GT. 0.11 ) GO TO 1125

IF( FLAG MNE. 1.) GO TO 1S18

C. 12
1126 CONTINUE

IQFRMAX=0.0

DO 1130 K=1,9

IF(ARECQ(,IBO).EIQ.0.0 .OR. QFRR(K,J).LE.QFRMAX) GOTO 1130

QFRMAX=QFRR (K,J)

1130 CONTINUE

BRATE (I, J)=(QE+QFC (I, J) .QFRMAX-QRR (I)) *AREC (1,180)

1/HEATV (I)

MASS (I,J)=BRATE(I,J)*DELT

QACT(I,J)=XA(I,J)*HEATC(I)*MASS(I,J)

QCON(I,J)=XC (I,J) *HEATC (I) *MASS (I, J)

QRAD(I,J)=XR(I,J)*HEATC(1)*MASS(I,J)

GCO2 (I,J) =YFCO2 (I, J) *MASS (I, J)

GCO1 (I,J)=YFCOI (I,J) *MASS (I, J)

GCH4 (I,J) =YFCH4 (I, J) .MASS (I, J)

GH2O (I,J) =YFH2O (I, J) *UASS (I, J)

GHCL(I,J)=YFHCL(I,J)*MASS(I, J)

SMOK(1,J)=YSMOK(I,J)*MASS(I, J)

1135 CONTINUE

GRPART (1 ,12) =0.

WRART (2, 12) =0.

TQACT=0.

TQCDN=0.

TQRAD=0.

TGCO2=0.

TGCOI=0.

TGH2O=0.

TGCH4=0.

TGHCL=0.

TSMOK=0.

TMASS=0.

TMO=0.

TMC=0.

TNMt=0.

TMCL=0.

DO 1140 I=1,9

TQACT=TQACT+iQACT (I, J)

TQCON=TQCON+QCON(I, J)

TQRAD=TQRAD+.QRAD (I, J)

TGCO2=TGCO2+GCO2 (I, J)

TGCOI=TGCOI+GCO1 (I, J)

,TGH2O=TGI-20.GH2O (I, J)

TGCH4=TGCH4+GCH4 (I, J)

TGHCL=TGHCL+GHCL (I, J)

TSMOK=TSMOK*SMOK (I, J)

TMASS=TMASS+MASS (I, J)

TMO=TMO+WFO (I) *MASS (I, J)

TMC=TMC*WFC (I) *MASS (I, J)

TMH=TMH4tWFH (I) *MASS (I,J)

TMCL=TMCL.4WFCL (I) *MASSCI, J)

1140 CONTINUE

DO 1139 ISZ=1,11

GRPART(1,ISZ)=O.

GRPART (2, ISZ)=SMSZ (ISZ) *TSMOK/DELT

GRPART (2,12) =GRPART (2,12) +GRPART (2, ISZ)

1139 CONTINUE

TQACTR=TQACT/DELT

TQACTN =TQACTR* .0034 12

GTMASS=GTMASS+TMASS

DO 1145 1=1,9

FUEL (1,180) =FUEL (I, IBO) -MASS (I, J)

0. 13
IFCFUELCI,IBO).LE.0..AND.ARECCI,IBO).GT.S.) TENO(I,IBO)=TSTEP

IF CFUELCI,IBO).LE.0.) AREC(I,IBO)=O.

1145 CONTINUE

DO 1165 I=1,9

IF(BRATE(I,J).GT.0.O)GO TO 1150

TBURN(I, IBO)=0.o

GO TO 1155

1150 TBURN(I, IBO) =FUEL (1,10) /BRATE(I, J)

1155 CONTINUE

C

C C

C Addition[I flow paths to/from compartment C

C C

P1COM=-PCOMP

PCOMP= (RI YOLRM) *(AMCL*TCL.AMHL*THL)

ZM= (AMCL*R*TCL) /(AFLOOR*PCOMP)

FPIIILT=0 .0

FPICLT=0.0

FPOCLT=0.0

FPOHLT=0 .0

IF(NFP.EQ.0) GO TO 1170

DO 1165 IFP=1,NFP

OKFP CIFP) =0.0

IF (TSTEP .GE. TFP (IFP) ) OIFP (IFP) =1.

OKFHL (IFP) =0.0

IF (HFP (IFP) .GE. ZM) OKFHL (IFP) =1.

OKPFO (IFP) =0.0

IF (PCOMP .GE. PFP (IFP) )OKPFO (IFP) =1.

OKPFI(IFP)=0.0

IF(PCOMP.LT.PFP(IFP))OKPFI(IFP)=1.

DELP=ABS(PCOMP-PFP(IFP))*1.01325 11.01325 is conversion from atm to bar

PLP=1.01326*PCOUP

C

C FPIHL(IFP) = FLOW INTO HL, M**3/S

C FPICL(rFP) = FLOW INTO CL, M**3/S

C FPOHL(IFP) = FLOW OUT H4L, Mua*3/S

.C FPOCL(rFP) = FLOW 011T CL, M**3/S

IF(OKFP(IFP).EQ.0.)GO TO 1160

FPIHL(IFP)=OKFP (IFP) .OKFHL(IFP) *OKPFI (IFP) *(DFP (IFP) **2)

1*3217.8* (DELP*PLP/TINIT) ** .5

FPICL(IFP)=OKFP(IFP)*(1.-OKFHL(IFP))*DKPFI(IFP).(DFP(IFP)0*2)

1*3217.8* (DELP*PLP/TINIT) ** .5

FPOHL(IFP)=OKFP (IFP) *OKFHL (IFP) *OKPFO(rFP) *(DFP (IFP) **2)

1*3217.8* (DELP*PLP/THL)** .5

FPOCL(IFP)=OKFP(IFP)*(1 .- OKFHLCIFP))*OKPFOCIFP)*CDFP(IFP)a*2)

1*3217.8* (DELP*PLP/TCL) ** .5

1180 CONTINUE

FPIHLT=FPIHLT+FPIHL (IFP) *PCOMP/ (R*TINIT)

FPOHLT=FPOHLT.FPOHL (IFP) *PCOMP/ (R*THL)

FPICLT=FPICLT+FPICL (IFP) *PCOMP/ (R*TINIT)

FPOCLT=FPOCLT4FPOCL (IFP) *PCOMP/ (R*TCL)

1265 CONTINUE

FPDKLV=FPODlLT*(R*TKL) /PCOMP

FPOCLV=FPOCLT. (R*TCL) /PCOMP

C

C C

C HEAT TRANSFER TO CEILING,WALLS,AND FLOOR C

C ADDITIONAL MASS RELEASES FROM CONCRETE C

C. 14
c C

C

C .** 1.CEILING

C

1170 CONTINUE

TCH2O=0.

TCCO2=0.

DO i186 JC=2,N4UI-1

CALL TEMP(MATERC,DELT,TC(JC,1),TC(JC,2),YEC(JC),.YHC(JC) ,YCC(JC),

.TDIFC(JC),TC(JC-1,1) ,TC(JC+1,1) ,DXC,TCH20,TCCO2,VC,NFLAGC)

2185 CONTINUE

CALL ENDPT(TCC1,1),TC(1,2),TC(2,1),TC(2,2),TC(NUM,1),

.TC(NUM-1, 1) ,TC(NUM, 2) ,TC (NUM-1 ,2) ,MATERC,DXC,QCA,CKDC,THL,

.eNFLAGC)

QC=AFLOOR* QCA

DO 1195 J2=1,NUM

TC(J2,1)=TC(J2,2)

1195 CONTINUE

C

C *AVAILABLE RADIANT HEAT TO WALL,EQUIPMENT AND HOTLAYER*

C

ZHL=ZR-ZM

WRAD=TQRAD* ZM/ZR

HLRAD=TQRAD-WRAD

DR=SQRT( . *AFLOORfPI)

IF(ZM.LE.0.)GO TO 1205

ERAD=WRAD*ARAD/ (PI*DR*ZM)

IF (ERAD .GT. WRAD) ERAD=WRAD

WRAD=WRAD-ERAD

GO TO 1210

1205 WRAD=O.

ERAD=O..

C

C .**2.WALL

C

1210 TWH2O=0.

TWC02=0.

AE=ZM'i4 . SQRT (AFLOOR)

IF( AE .LE. 0.0 ) THEN

WRADF = 0.0

ELSE

WRADF=WRAD/ (AE.DELT)

END IF

ZW--ZR/ (NUM-1)

NW=-INT (ZHL/'ZW)

IF(NW.LT.1) NW=1l

IF (NW.GT .NUM-2)NW=NUM-2

AHL=2 .0*ZHL* (LR+WR)

VW=-AHL*XWALL*A1

DO 1235 IW=1l,NUU-2

IF (IW.GT.NW)NFLAGW=1l

DO 1230 JW=-2,NUM-1

CALL TEMPCMATERW,DELT,TW(IW,JW,1) ,TW(IW,JW,2) ,YEW(IW,JW),

+DXW, TWV12O ,TWC02 ,VW, NFLAGW)

1230 CONTINUE

THLC=THL

IF (IW.GT.NW) THLC=TCL

CALL ENDPTCTW(IW,1,1),TWCIW,1,2),TWCIW,2,1I),TW(IW,2,2),

.eTW(IW,NUM,1) ,TW(IW,NUM-1,1) ,TW(IW,NUM,2) ,TW(IW, HUM-i ,2),MATERW,

C. 15
+DXW, QWA (IW) ,CKDW, THLC, NFLAGW)

NFLAGW=80

1235 CONTINUE

TAVWI4=O.

TAVWC=0.

DO 1240 IW=1I,NW

1240 TAVWH=TAVWH4TW(IW,1,1)

TAVWH=TAVWI4/NW

DO 1245 IW--NW NUM-2

1246 TAVWC=TAVWC~ii(IW,1,1)

IF(NW.EQ.NUM-2)GO TO 1250

TAVWC=TAVWC/ (NUM-2-NW)

1250 CONTINUE

QWB=0.

DO 1255 NT=1,NW

QWBI=QWB4QWA (NT)

1255 CONTINUE

PNW=-FLOAT (NW)

QWH= (QWB/PNW) *(AW1*2 .AW2*2.) *ZHLIZR

QWD=0.

IF(NW.GE.NUM-2) GO TO 1270

NC=NW*1

DO 1285 NTwNC,NUM-2

QWD=QWD.QWA (NT)

1285 CONTINUE

PNC=FLOAT ( (NUM-2) - NW)

1270 QWC= (QWD/PNC) *(AW1*2 .tAW2*2.) *ZM/ZR

DO 1275 JW=12,NUM

DO 1275 IW=1,NUM

TW(IW, JW, 1)=TW(IW,JW,2)

1275 CONTINUE

QW=-QWC*QWH

C

C * COMPUTE TIMES OF HOT LAYER PAST CERTAIN POINTS*

C

DO-1285 IE=1,4

DO 1285 JE=1,10

IF (ZM.L1 .ZCL(JE,IE) .AND.TBCL(JE,IE) .Eq.0.)TBCL(JE,IE)=TSTEP

1285 CONTINUE

ZTESTS=ZM-ZFIRE

ZTEST6=ZM-ZOF

IF(ZTESTS.LT.0. .AND.ZTESTS.LT.0. .AND.TECL.EQ.0.)TECL=TSTEP

C

C ** 3.FLOOR

C

TFH20=0.

TFC02=0.

IF (ZHL.LT.ZR) NFLAGF=1

DO 1300 JF=2,NUM-1

CALL TEMP(MATERF,DELT,TF(JF,1),TF(JF,2) ,YEF(JF) ,YHF(JF),

.YCF(JF) ,TDIFF(JF),TF(JF-1,1),TF(JF+1,1),DXFTFH20,TFC02,VF,

*NFLAGF)

1300 CONTINUE

THLC=TCL

IF (TECL.GT.O.)THLC=THL

CALL ENDPT(TF(1,1) ,TF(1,2) ,TF(2,1) ,TF(2,2) ,TF(NUM,1),

.TF(NUh4-1 ,1),TF(NUM,2) ,TF(NUM-1,2) ,MATERF,DXF,QFA,CKDF,THLC,

+eNFLAGF)

NFLAGOFz0

QF=AFLOgR*QFA

C. 16
DO 1305 JF=1,NUM

TFCJF,1)=TFCJF,2)

1305 CONTINUE

C

C C

C Mass balance in fire compartment C

C C

WTOT1=WSMIF+WRADIF

WTOT1=WTOT1 /N2X2IF

DENOMI=RESISTI* C1.0*g.79E-3*(WTOTI).+13.95E-8*C(WrOTl*.2.0))

WTOT2=WSMOF+WRADOF

WTOT2=WTOT2/N2X2OF

DENOM2=RESISTD (1 .0*9. 79E-3* (WTOT2) *13. 95E-6* CWTOT2**2 .0))

VIF= CPl-PCOMP) /DENOM1

VOF= CP2-PCOMP) /DENOM2

ZTESTI=Pl-PCOMP

ZTEST2=ZIF-ZM

ZTESTS=ZM-ZOF

.OKHL=0.0

OKHL1=0 .0

OKHL2=0 .0

OKCL=0.0

OKCL1=0 .0

OKCL2=0.0

IF(ZTEST1.GT.O.O.AND.ZTEST2.GE.0.0)OKHL=l.

IF(ZTEST1 .GT.O.0 .AHD .ZTEST2 .GE.0.0)TA=TINIT

IF(ZTEST1 .LT.O.O.AND .ZTEST2 .GE.0.0)OKHL1=1.

IF(ZTEST1.LT.O.O.AND.ZTEST2.GE.O.O)TA=THL

IF(ZTEST3 .GT.0.0) OKCL2=1 .0

IF(ZTEST1.LT.O.0.AND.ZTEST2.LT.0.0)OKCL=1.0

IF(ZTEST1 .LT.0 .0.AND .ZTEST2 .LT .0.0)TA=TCL

IF(ZTEST1.GT.0.O.AND.ZTEST2.LT.0.0)OKCLI=1.0

IF(ZTEST3.LE.0.0)OKHL2=1 .0

ZTEST4=ZFIRE-ZM

TIF=THL

IFCZTEST4 .LT.0..0)TIF=TCL

IF( TQCON .LE. 0.0 ) TQCON = .OE-10

ZFLAME=0 .23* (TQ&CON/DELT) a0 .4

IF( TMASS .LE. 0.0 ) ZFLAME = .OE-8

ZZ = ZR - ( ZFIRE * ZFLAME )

IF( ZZ .LE. 0.0 ) ZFLAME = ZR -ZFIRE

QZ= (TQCON/DELT) /(C PCOMP*CP/R) *(GR**0 .5) *(ZFLAME**2 .5))

VEL= (FIAIF* (TCL/PCOMP) *8.2E-6) /TAREC

FIAOF= .21* (PCOMP/ (R*TCL) ) *(GR** .5) *(ZFLAME**2 .5)

1* (QZ** .333)

TOF=TCL*TCL*CQZ** .887)/.21

FUN=FMOF- (TGCH4/16 . TGCOI/28 .*TGCO2/44 .*TGH2O/18.

1*TGHCL/3 .5) /DELT

FM02B= (TGCO1/566. TGC02/44 .*TGH2O/38 . )/DELT

FL4IF=FUN*FM02B

ZPL=ZR-ZFIRE

IF( ZZ .LE. 0.0 ) ZPL = ZFLAME

IF (TSTEP. GT .DELT) ZPL=ZM-ZFIRE

IF( ZPL .LT. ZFLAME ) ZPL = ZFLAME

QZ =QZ* (ZFLAME/ZPL) **2 .5

FM=-FMDF*(C(ZPL/Z FLAME) *s2.5) *((QZM/QZ) ** .333)

TM=-TCL.TCL* (QZM*. .667) /.22

FE=FM*R*TMfPCOMP

OKCLF=0 .0

C. 17
OKI4LF=6.

IFCZTEST4.LT.0.0)OKCLF=1 .0

rF(ZTEST4 .GE.0.)OKHLF=1.

FrF=VIF*PCOMP/ (R*TA)

FOF=VOF*PCOUP/ (R*TIF)

AMHL=AMHLe (OKHL*FIF.OKHLI*FIF.OKHL2*FOF+FIA*OKCLF+tFPIHLT-FPOHLT+

1 (FMOF-FMIF) *OKHLP) *DELT. (TCC02+eTWC02+eTFCO2) /44 . CTCH2O*TWH20+

2TFH26) /18.

AMCL=AMCL. (OKCL*FIF+OKCLI*FIF4OKCL2*FOF-FmIF*OKCLF- CFU-FMOF)

1.FPICLT-FPOCLT) .DELT

IF(ZTESTS.LT.O.O.AND.ZTESTS.LT.0.0)GO TO 1310

GO TO 1315

1310 AMHL=AhIHL+AMCL

CHt12=CHN2+CCN2

CHO2=CHO2+.CCO2

THL= (THL*AUHL.TCL*AMCL) /(AMHL4AMCL)

AMCL=0..0

'CCN2=0.0

CC02=0..0

1315 FN21F=FMIF.0 . 79.OKCLF

F021F=FMIF*0 .21*OKCLF

OKPF=0.0

IF(ZPL.GT.0.O)OICPF=1 .0

FIPs CFM-FUOF) *OKPF

FhI2rP=FIP.0 .79

F021P=Frp.0o.21

C

C*.'..** OXYGEN BALANCE

C

IF(AMHL.LE.0.0)GO TO 1320

FMHO2=CHO2/AMHL

GO TO 1325

1820 FU1402=0.0

1325 rF(ZTEST4 .GE.0.0)FO2IF=0.0

CH02=CH02+ (OKHL.0 . 21*FIF+OKHLI*FMHO2*FIF+OKHL2.FMHO2.FOF. (FO2IFIFM02B) +FO2IP+0 .21.FPIHLT-FMHO2.FPOI4LT) *DELT

CCO2=CC02i COKCL.0.21*FIF.OKCL1.0.21*FIF+OKCL2*0.21*FOF-FO2IF1FO2IP*S. 21* (FPICLT-FPOCLT) )*DELT

rF(ZTESTS.LT.O.O.AND.ZTEST6.LT.0.0.)CC02=0.0

C

c****** NITROGEN BALANCE

C

rF(AMHL.LE.0.)GO TO 1330

FhIHN2=CHN2/AMHL

GO TO 1335

1330 FMI1N2=0.0

1335 CI1N2=CHN2. (OKHL.0.79*FIF*OKHLI*FMHN2*FIF+OKI1L2*FIAHN2*FOF4FN2IF

1+FN21P+. 79*FPIHLT-FMHN2*FPDHLT)*.DELT

CCN2=CCN2* COKCL*0.79*FIF.OKCLI*0.79*FrF+OKCL2*0. 79*FOF-FN2IF1FN21P+ .79*(CFPICLT-FPOCLT))*.DELT

IF(ZTEST5.LT.O.O.AND.ZTEST6.LT.0.0)CCN2=0.0

C

C****** C02 BALANCE

C

rF(AMI4L.LE.O.0)GO TO 1340

FMC02=Ct4CO2/AMHL

GO TO 1345

1340 FUCO2=0.0

1345 CHC02=CHCO2. (OKHLI.FMCO2..FIF+OKHL2*FMCO2*FOF-FMC02*FPOHLT) .bELT

ii. TGC02+TWC02*TCC02+TFC02) /44 .0

C

C.* 18
C***.*** CO BALANCE

C

IF(AMHL.LE.0.O)GO TO 1360

FMCOI=CHCOl/AMHL

GO TO 1355

1360 FMCO1=0.0

1355 CHC01=CHCO1. (OKHLI*FMCO1*FIF+OKHL2*FMCO1*FOF-FUCO1*FPOHLT)

i#DELT.TGCOl/28 .0

C

C****** H20 BALANCE

C

XF(AMHL.LE.0.0)GO TO 1360

FMH2O=CHH2O/AMHL

GO TO 13865

1380 FMH2O=0.0

1365 CHH2O=CH1420+ (OKIIL1*FMH2O.FIF.OKHL2*FMH2O.FOF-FMH2O.FPOHLT) .DELT+

1 (TGH2O.TWH2O+TCH2O+TFH2O) /18.0

C

C****** HCL BALANCE

C.

IF(AMHL.LE.O.0)GO TO 1370

FMHCL=CHHCLfAMI4L

GO TO 1375

1370 FMHCL=0.0

1375 CHHCL=CHHCL+ COKHL1*FMHCL*FIF.OKHL2*FMHCL*FOF-FMHCL*FPOHLT)

1*DELT+TGHCL/38 .5

FMHO2=CH02/AMHL

'IF(AMCL.LE.V.0) GO TO 1380

FM02=CCO2/AMCL

1380 IF(ZTEST4 .GE.0.0)FMO2=FMHO2

C

C.****s CH4 BALANCE

C

IF(AMHL.LE.0.0)GO TO 1385

FMCH4=CHCH4/AMIIL

GO TO 1390

1385 FMCH4=0.0

1390 CHCH4=CHCH4+ COKHL1*FMCH4*FIF+OKHL2*FMCH4*FOF-FMCH4*FPOHLT) sOELT.

ITGCH4/18 .0

C

C.***** SMOKE BALANCE

C

VOLHL=AFLOOR* (ZR-ZM)

IF(VOLHL.LE.0.)VOLHL=1 .E+20

V1HL=VOLHL

C *FPSMOK=RATE OF SMOKE OUT OF ADDITIONAL FLOW PATHS CG/S)

FPSMOK= (A (2, 12) /VOLHL) *(-.FPOHLT*R*THLfPCOMP)

WSMI=DELT*A(2, 12) .OKHLI*VIF/VOLHL

WSMO=DELT*A(2, 12) *OKHL2*VOF/VOLHL

IF(VOLCL.LE.S.)GO TO 1392

WSMI=WSMI.DELT*B (2, 12) .OKCL*VIF/VOLCL

WSMO=WSMO.DELT*B (2, 12) *OKCL2*VOF/VOLCL

1392 CONTINUE

IF(VIF.GT.0.0)WSMI=0.0

IF(VOF.GT.0.O)WSMD=0.0

WSMIF=WSMIF-WSMI

WSMOF=WSMOF-WSMO

C

C. 19
C

C HEAT TRANSFER TO EQUIPMENT

C

C TYPES OF EQUIPMENT (IE):

C

C IE TYPE

C

C 1 SIMPLE HEAT SINKS - NO INTERIOR RADIOACTIVITY

C 2 PRESSURIZED - WITH POWDER ONLY (RADIOACTIVE)

C 3 PRESSURIZED LIQUID CONTAINERS (RADIOACTIVE LIQUID)

C 4 OPEN LIQUID CONTAINERS (RADIOACTIVE AQUEOUS)

C

C JE = NO OF EACH TYPE OF EQUIPMENT

C

C SPECIFY CONTAINER HEIGHT, WIDTH, MATERIAL TYPE, HEIGHT.OF

C BOTTOM OFF OF FLOOR, AND MASS OF CONTAINER

C

C HEQ(JE,IE)=HEIGHT OF CONTAINER (M)

C WD(JE,IE)=WIDTH OF CONTAINER (M)

C MATERE(JE,IE)=1,2 ........ 9 ACCORDING TO DATA BASE

C WMASS(JE,'IE)=MASS OF CONTAINER (KG)

C HTF(JE,IE)=HEIGHT OF BASE OFF OF FLOOR (M)

C MJE(IE)=NO. OF JE FOR EACH IE

C PF2 (JE)=FAILURE PRESSURE (ATM)

C PF3(JE)=FAILURE PRESSURE (ATM)

C P12(JE)=INTERNAL PRESSURE OF EQUIPMENT TYPE 2

C PI3(JE)=INTERNAL PRESSURE OF EQUIPMENT TYPE 3

C

C

C .**FIRST TYPE OF CONTAINER-SIMPLE HEAT SINK **

Ct

C IE=1 IS FOR INACTIVE EQUIPMENT (NO RADIOACTIVE SOURCES OR FAILURES

C EXPECTED

C

TGRAD=0.0 TO ZERO TOTAL RADIOATIVE RELEASES EACH TIME STEP

DO 1395 IE=1,4

EQ(IE) = 0.0

1395 CONTINUE

IF(EQUIP.EQ.0.0) GO TO 1475

IF(MJE(l).EQ.0) GO TO 1405

DO 2400 JE=2,MJE(1)

OKE2=1.

IF(TBCL(JE,1) .EQ.0.)OKE1=0.

UO=0.005*(ABS(THL*OKE1iTCL*(l.-OKEl)-TE1 (JE)))**.3333

IF (UO .LT .UMIN) UO=UMIN

QEI (JE)=-(ERAD/(ARAD*DELT))*(1.-OKE1).HEQ(JE,1)/(PI*

3-TEl (JE))

TEI(JE) =TE1 (JE) -DELT*QEl (JE) *ARHT (JE, 1)/I(WUASS (JE, 1).

1'.CPCA (MATERE (JE, 1)))

EQ (1)=EQ (1) QE1 (JE) *ARHT (JE, 1) *DELT

.1400 CONTINUE

C

C ***SECOND TYPE OF EQUIPMENT-PRESSURIZED POWDER **

C

1405 IF(UJE(2).EQ.0) GO TO 1430

DO 1425 JE=1,MJE(2)

OKE2=1.

IF(TBCL(JE,2) .EQ.0.)OKE2=0.

C. 20
UO= .005* CABS (TM-TE2 (JE))) ** .3333

IF(UO.LT.UMIN)UO=UMIN

QE2(JE)=..(ERAD/CARAD*DELT))*(l.-OKE2)*HEQCJE,2)/CPI*

lCWDCJE,2)/2.*HEQ(JE,2)))-SIG*CTM**4-TE2CJE)**4)

2/(l./EMIS(MATERE(JE,2))+..111)-UO*(TM-TE2(JE))

C

C FLUX TO INSIDE Q12(JE),,. INSIDE TEMP =T12(JE)

C

IF(FAIL2(JE).EQ.1.) GO TO 1415

PR=0.7

TB=0.6* (TE2 (JE).T12 (JE))

TS=TE2 (JE)

EL=HEQ (JE, 2) *(VGAS2 (JE)/ (VGAS2 (JE) *VPWD (JE)))

DFT=ABS (TE2 (JE) -T12 (JE))

WDT=WD(JE,2)

UIN=UINS (EL,TS,DFT,TINIT,WDT,TB)

GMOL=VGAS2 (JE) *273./(2. 24E-02*TINIT) +WH202 (JE) /18.

Q12 (JE) =UIN* (TE2 (JE) -T12 (JE))

TE2(JE)=TE2 (JE)-(QE2(JE)+Q12(JE))*DELT*ARHT(JE,2)/

1 (WUASS (JE,2) *CPCA (MATERE (JE,2)))

T12 (JE) =TI2 (JE)+QI2 (JE) *DELT*ARHT(JE,2) /(CPAIR*GMOL)

P121 (JE)=1 .0

P12 (JE) =PI21 (JE) *TI2 (JE) /TINIT

PTEST=P12 (JE) -PF2 (JE)

IF(PTEST.GE.0.0) FAIL2(JE)=1.0

C

C *PRESSURIZED POWER RELEASES OF VESSELS AT RISK

C

IF(FAIL2(JE) .GT.O.S) THEN

AMHL=AMHL* GMOL

ADS2=VGAS2 CJE) *273. /(2. 24E-02*TINIT)

CHO2=CHO2+FAIL2 (JE) *AD62* .21

CHN2=CHN2+FAIL2 (JE) *AD52* .79

CHH20=CHH2O.FAIL2 (JE) *WH202 (JE) /18.

NRST=S

DO 1410 JACT=1,10

IF(QRADS(JE,JACT) .EQ.0.0)GO TO 1410

CALL RST5 (QRAD5 (JE, JACT) ,PF2 (JE) ,VOLP (JE) ,PDENCJE, JACT), +GRAD,QMR, JACT)

GO TO 11501

1410 CONTINUE

END IF

C

C

C

GO TO 1420

1415 CONTINUE

QE2(JE)=2.*QE2(JE) P ai led vessel has 2 t~imes heat. transfer area TE2(JE)=TE2(JE)-QE2CJE)*DELT*ARHTCJE,2)/CWMASS(JE,2)*

1CPCA(MATERE(JE,2)))

1420 CONTINUE

EQ(2)=EQ(2) +QE2 (JE) *ARHT (JE,2) *DELT

1425 CONTINUE

C

C ***THIRD TYPE OF EQUIPMENT-PRESSURIZED LIQUID.VESSELS .*

C

1430 IF(MJE(3).EQ.0) GO TO 1460

DO 1455 JE=1,MJE(3)

OKE3=1.

IF(TBCL(JE,3) .EQ.0.)OKE3=0.

UO= .005* (ABS (TM-TE3 (JE) )) **.3333

C .21
IF(UO.LT.UMIN)UO=UUIN

QE3CJE)=-(ERAD/CARAD*DELT))*C1 .-OKE3)*HEQ(JE,3)/(

IPI.CWD(JE,3)/2.+HE.QCJE,3)))-SIG.(TM.*A-TE3CJE).*4)./

2(l./EMIS(MATERE(JE,3))..1112)-UOs(TM-TE3(JE))

C

C FLUX TO INSIDE = QI3CJE) , INSIDE TEM =T13(JE)

C

IF(PAIL3(JE).EQ.1.) GO TO 1445

TB=0.6* CTES (JE) .T13 JE))

TS=TE3 (JE)

EL=HEQ (JE, 3)

DFT=ABS (TE3 (JE) -T13 (JE))

WDT=W (JE, 3)

UIN=UINS(EL,TS,DFT, TINIT,WDT,TB)

.AI=ARHT(JE, 3)

Q3=UIN.AI. (TE3 (JE) -T13 (JE))

ANAIR=VGAS3 (JE) *273. /(2.24E-02*TINIT)

TIN=T.13(JE)+1.

DO 2435 K3=1,5

TRED=TIN/847.3

PG2=20. *.(-3. 1423/TRED+?8 .3610-EXP (-20.* (TRED- .163) .*2))

PG2=PQ2 753 .18

TRI=T13 (JE) /647.3

PG1=10..m(-3.1423/TR1+8.361-EXP(-20..(TR2-.163).*ý2))/753.I8

EhEL=WH203 (JE) -18. .VGAS3 (JE) *PG1/ (R*TI3 (JE))

EUL-2=WH203 (JE) -18. .VGAS3 (JE) *P02/ (R*TIN)

EMV=-EhIL2+EML

TVH2O=-VGAS3 (JE) .PQ2/ CReTIN)

TIN=T13 (JE) , Q3-ELV*EMV) /(CPL.EML2*CPAIR. (ANAIR.+rVH2O))

1435 CONTINUE

QIS (Jt)=-UIN. CTE3 (JE) -T13 (JE))

T13 (JE) =TIN

TE3 (JE) =TE3 (JE) - CQE-3 JE) +Q13 (JE)) .DELT*ARHT(JE, 3)

1/Wh4ASS(JE,3) *CPCA(MArERE(JE,3))

PI3 CJE) = ANAIR+TVI120) .ReTI3 (JE) /VGAS3 (JE)

PTEST=P13 (JE) -PF3(CJE)

IF(PTEST.GE.0.)FAIL3(JE)=l.

-C

C *PRESSURIZED LIQUID RELEASES OF VESSELS AT RISK

C

IF(FAIL3CJE) .GT.S.5) THEN

AMI4L=AMHLt (ANAIR+eWH203 (JE)/1s.)

CHO2=0 . 2*ANAIR+CH02

CHN2=CHN2*0. 79*ANAIR

CHH2O=CHH2O..WH203 CJE) /18.

NRST=8

DO 1440 JACT=1,10

IF(QRADS(JACT,JE).Eq.0.)GO TO 1440

CALL RST8(QRADB CJACT, JE) ,GRAD, QMR,.JACT)

GO TO 1501

1440 CONTINUE

EN151F

C

C

C

GO TO 1450

1445 CONTINUE

QE3 (JE) =2. *QE3 (JE)

TE3(JE)=TE3(JE)-QE3 (JE) eDELT*ARHT (JE,3) /WMASS (JE, 3)

2*CPCACUATERECJE, 3))

1450 CONTINUE

C.* 22
.EQ (3) =EQ (3) .QE3 (JE) eARHT (JE, 3) .DELT

1455 CONTINUE

C

C .. *FOURTH TYPE-UNPRESSURIZED LIQUID CONTAINERS(RADIVACTIVE LIQUID).*****

C

1460 IF(MJE(4).EQ.0) GO TO 1475

DO 1465 JE=1,MJE(4)

OKE4=1.

IF(TBCL(JE,4) .EQ.0.)OKE4=0.

TRS=TL (JE) /647.3

PVAP=10.**(-3.1423/TR5.t8.381-EXP(-20*(TRS-.163)**2))

1/753.18

RHOV=PVAP/ (R*TL (JE))

TBG=OKE4*THL+ (1 .0-KE4) *TCL

TFILM= (TL (JE) *TBG) .0.9-480.0

RHOGM=29 .0/ (RaTBG)

RHOVM=-18.0*RHOV.29.S.(1.S-PVAP)/(R*TL(JE))

DRHODX=11 .0/ (R*TL (JE))

ZETA=DRHODX/RHOVM

AK=AKSH(WD(JE,4) ,RHOVM,RHOGM,ZETA,PVAP,TL(JE) ,TBG)

C AK is Sherwood number mass transfer coefficient for

C non-boiling surface, U/sec.

WDW=-WD (JE,4).3.29

UTA=(2.2117E-343.662E-5s(TFILM)*s0.5)z/WDW**0.25

IF(TL(JE) .LT.373.2)U14=0.559*(ABS(TE4(JE)-TL(JE)))..0.41301-

IF(TL (JE) .GE.373 .2)U14=7 .8484E-4. CABS (TEA (JE).-TL (JE))) .3 .55.684

IF(VOL(JE).LE.0.) GO TO 1465

ARHT(JE,4)=PI..(WD(JE,4)**2/4.)+4.VOL(JE)/WD(JE,4)

ARBL(JE)=PI.(WD(JE,4)**2/4.)

UO=.05.*ABS(THLsOKE4+TCL*(l.-OKE4)-TE4(JE))**.333

IF (UO .LT .UMIN) UO=UMIN

QE4 (JE) =-UO. (THL*OKE4+TCL (1. -OKE4) -TE4 (JE))

1-(ERAD/(ARAD*DELT))*(1.-OKE4)*HEQ(JE,4)/(PI*(WD(JE,4)/2.+

2HEQ(JE,4)))-SIG*OKE4.(THL**4.-TE4(JE)**4)/

3(1./EMIS(MATERE(JE,4))+.1111)

REVAP=RHOV*ARBL (JE) *AK*18.

IF(TL(JE) .GE.373.2)REVAP=18.0'eQIL/2.28

QIL=U14 * (TEA (JE) -TL (JE) ) ARHT (JE, 4)+

1UT4*.(THLm*OKE44TCLu* l .-OKE4) -TL(JE)) .ARBL(JE)-

2-REVAPu.0.23eARBL(JE)*SIG'.OKE4*(THL**4 .-TL(JE).'.A.)

RBOIL (JE) =REVAP.60.

V18=VOL (JE) *1 . E+06

TLTEST=QIL*DELT/ (VIO*CPL)

IF (TL (JE) .GE .373.2) TLTEST=0 .0

TL (JE) =TL (JE) 4TLTEST

TEA (JE)=TE4 (JE)* (-QE4 (JE) .ARHT(JE, 4) sDELT-U14*

ICTE4CJE)-TL(JE))*ARHTCJE,4)*DELT)/CWMASSCJE,4)

2*CPCA (MATERE (JE,4)))

VOL (JE) =VOL (JE) -DELT*REVAP*1 .E-0B

CHH2O=CHH2O.REVAPuiDELT/18.

EQ(4)=EQ(4).QE4(JE)*ARHT(JE,4) *DELT

1485 CONTINUE

1475 CONTINUE

EQT=EQ (1) 4EQ (2) 4EQ (3) +EQ (4)

C

C C.

C NET MASS AND ENERGY CALCULATION C

C C

Ti HL=THL

C.* 23
GHL=VIHL*PICOM/ (R*T1HL)

QHL=(THL-TINIT) *CPAIR*GHL

QCOMB=TQCON+iHLRAD

QLOST= (QC+QWH+QF) *DELT+EQT

AIRIN= (OKHL*ABS (FIF) .eFPIHLT) *DELT

AIROUT= (OKHL2*- . *FOF+FPOHLT+OKHLI*ABS (FIF)) *DELT

THL-=TINIT* (QHL+QCOMB+QLOST-AIROUT*CPAIR* (THL-TINIT) ) /(CPAIR* * (GHL+'AIRIN-AIROUT))

TZL= (FIF*OKHL*TINIT*FM*TM) /(FIF*OKHL+FM)

IF (TSTEP .EQ. DELT) THL=TZL

QLOSSR=EQT/DELT4.QC*QW+QF

QLOSSN=QLOSSR* .003412

TQNETR=TQACTR+QLOSSR

TQNET=TQNETR* .003412

TMASSR= (TMASS.TWCO2+TWH2O+TCCO2+TCH2O+TFCO2+TFH2O) /DELT

.TMASSN=TMASSR*7 .93

TMOLEN= C CTGH2O.TCH2O+TFH2O*TWH2O) /18 .04 (TGCO2.tTCCO24.

ITFCO2+TWCO2)/44 .0.TGCO1/28..TGHCL/36.5*TGCH4/16.0)/DELT

HLR=QWH+QC

IF(ZM.LE.O.)HLR=HLReQF

OKDP=0.

IF(P2.LT.PCOMP)OKDP=1.

FHL=OKHL2a.OKDP*ABS (VOF) +FPOHLV.OKKL1 *ABS (VIF)

FCL=OKCL2*OKDP*ABS (VOF) +FPOCLV+OKCL*ABSS(VIF)

TCAV=TC (1,1)

TFAV=TF (1,1)

C

C

C CALCULATION OF RADIOACTIVE SOURCE TERMS

C

DO 1620 JACT=1,10

IF(NRAD(1).LT.1)GO TO 1480

NRST=l

DO 1480 1=1,9

DO 1480 IFORM=1,3

NJ=(C(IFORM* 10) -10)41l

IF(QRADI(NJ,JACT,IBO) .LE.O.)GO TO 1480

QT=QE-eQFC (I, J) .eQFRMAX-QRR (I)

RSMOK=YSMOK (I, J) *BRATE (I, J)

CALL RSTI(QRAD1(NJ,JACT,IBO) ,TEND(I,IBO) ,GRAD,OFUEL(I,IBO),

.tBRATE(I,J) ,RSMOKQT,VE-L,XMAX1(NJ,JACT) ,XMAX2(NJ,JACT),

*XMAX3(N, JACT))

GO TO 1601

1480 CONTINUE

DO 148S 1=7,9

IF(NRAD(2).LT.1)GO TO 148S

NRST=2

DO 1485 IFORM=-1,2

NJ= (1-6)4 (IFORM-1) *3

IF(QRAD2(NJ,JACT,IBO).LE.O.)GO TO 148S

IF(TEND(I,IBO) .EQ.TSTEP.AND.TEND(I,IBO) .NE.0.)

1QRAD2(N, JACT, 10) =0.0

SMOKFR=SMOK (I, J) /OFUEL (I,180) /DELT

CALL RST2 (QRAD2 (NJ,JACT, IBO) ,IFORM, GRAD, QMR, JACT,SMOKFR,

OOFUEL (I, IBO) ,BRATE (I, J))

GO TO 1501

1485 CONTINUE

IF(NRAD(3).LT.1)GO TO 1490

NRST=3

IF(RRAD3(JACT).LE.O.) GO TO 1490

C. .24
T=THL-273 .0

IF(T.LE.30.)GO TO 1490

CALL RST3 (QRAD3 (JACT) ,GRAD,DELT,QIWR, JACT, T)

GO TO 1501

1490 CONTINUE

IF(NRAD(4).LT.1)GO TO 1800

NRST=4

DO 1500 IVES=1,10

T=TE4 (IVES) -273.0

IF(QRADA(IVES,JACT) .LE.O.) GO TO 1495

CALL RST'4(QRAD4 (IVES, JACT) ,VOL(IVES) ,IVES, TSTEP,T,VEL,

1TL(IVES) ,DELT,RBOIL(IVES) ,GRAD,QMR,JACT)

GO TO 1601

1495 CONTINUE

1500 CONTINUE

IFCNRADC7).LT.1)GO TO 1505

NRST=7

IFCQRAD7(JACT,IBO) .LE.0.) GO TO 1506

CALL RST7 (QRAD7 (JACT, IBO) ,SQ(JACT, IBO) ,GRAD, TSTEP,IBO, QMR, JACT)

1501 CONTINUE

TGRAD=TGRAD.GRAD

DO 1502 ISIZE=1,11

1502 GRF'ART(1, ISIZE)=GRPART( , ISIZE) +QMR(ISIZE, JACT)

GRPART(1, 12)=GRPART(1,12)..GRAD

WRADI=DELT*A (1,12) *OKHLI*VIF/VOLHL

WRADO=DELT*A (1,12) *OKHL2*VOF/VOLHL

IF(VDLCL.LE.0.)GO TO 1503

WRADI=WRADIiDELT.B (1,12) *OKCL*VIF/VOLCL

WRADO=WRADO+DELT.B (1,12) *OKCL2*VOF/VOLCL

1503 CONTINUE

IF(VIF.GT.0.0)WRADI=0.0

IF(VOF.GT.O.0)WRADO=0.0

WRADIF=WRADIF-WRADI

WRADOF=WRADOF-WRADO

GO TO (1480,1485,1490,1495,1410,1440,1505)NRST

1505 CONTINUE

1510 CONTINUE

C *FPRAD=RATE OF RADIOACTIVITY OUT OF ADDITIONAL FLOW PATHS

C (G/S) FPRAD=(A (1,12) /VOLHL) *(-FPOHLT*R*THL/PCOUP)

C

CSIAOKE=A (2, 12) /VOLHL

CGRAD=A(1,12)/VOLHL

C

C

C PARTICLE DEPLETION CALCULATIONS

C

!f(tst~ep.*q.deIt)zm=(amcl~r*tcl)/(afloor~pcomp)

CALL PDMECH

DO 1550 K=1,2

A(K,12)=0.

B(K,12)=0.

DO 1550 M=1,8

AFLOSS(M,K, 12)=0.

1650 CONTINUE

DO 1555 ISZ=1,11

DO 1955 JT=l,2

DO 1580 M=1,6

AýFLOSS(M,JT,ISZ)=FRAC(M,ISZ)*ALOSS(JT,ISZ)

C .25
AFLOSS CM, JT, 12) =AFLOSS CM, JT, 12) .AFLOSS (M, JT, ISZ)

1560 CONTINUE

DO 1585 M~=8,8

AFLOSS (U,JT,ISZ) =FRAC CM, ISZ) *BLOSS (JT, ISZ)

AFLOSS(M,JT,12)=AFLOSS(M,JT,12).AFLOSS(M,JT,ISZ)

1585 CONTINUE

A(JT,12)=A(JT, 12) .eA(JT,ISZ)

B(JT,12)=B(JT, 12) .B(JT, ISZ)

1556 CONTINUE

DO 1588 JT=1,2

ALOSS (JT, 12) =O.

BLOSS CJT, 12) =5.

DO, 1587 M=1i,S

1587 ALOSS (JT, 12) =ALOSS CJT, 12) .AFLOSS (M, .JT, 12)

DO 1568 M=6,8

1588 BLOSS(JT,12)=-;BLOSSCJT,12)*AFLOSSCM,JT,12)

DO 1569 ISZ=1,11

DO 21589 JT=1,2

ABLOSS=BLDSS (JT, ISZ)

IF (ZM.LE.0.)ABLOSS=ALOSS(JT,ISZ)

FUASS (JT)=FMASS (JT) +FRACF (ISZ) .ABLOSS

WAMSS(JT)=WAAS( I JT) .e.OFRACW(ISZ) *OSS(TIZ

CAMASS(JT)=AMASS(JT).FRACC(ISZ) *ALOSS(JT,ISZ)

1589 CONTINUE

DO 1570 JT=1,2

VENT=AFLOSS (5,JT, 12) +AFLOSS (7, JT, 12)

VEMASS (JT) =VEMASS (JT) +EFFIC*VENT

OUTVEN(JT) =OUTVEt4(JT) (1-EFFIC) *VEN4T

1570 CONTINUE

C

C

C PRINT OUTPUT FOR TIMESTEP

C

THLUC = 1.8 *THL - 480.0

IF(MOD(ITSTEP,IPRINT) .EQ.0.0) THEN

WRITE(10,270) TSTEP,PCOMP ,FMO2 ,ZHL,VIF,VOF,THLUC,TUASSR,TQACTR,

+QLOSSR, TQNETR

WRITE(8,246)TSTEP, (A(1,M) ,M=1,12)

WRITE(11,245)TSTEP, (AC2,M) ,M=1,12)

IF(ALOSS(1,12) .GT.O.)THEN

wRITE(3,410)TSTEP,AO(1,12) ,GRPAR7(1,12)*DELT,AFLOSS(8,1,12),

OALOSS(1,12) ,A(1,12) ,((AFLOSS(M,1,12)/ALOSS(1,12)),M=-1,5)

ELSE

wRITE(3,410)TSTEP,A0(1,12) ,GRPART(1,12)*DELT,AFLOSS(8,1,12),

*ALOSS(1,12) ,ik(,12)

END IF

IF (ALOSS (2,12) .GT.O.)THEN

WRITE(5,410)TSTEP,AO(2,12) ,GRPART(2,12)*DELT,AFLOSS(8,2,12),

*ALOSS(2,12) ,A(2 '12) ,((AFLOSS(M,2,12)/ALOSS(2,12)) ,M=1,5)

ELSE

wRITE(5,410)TSTEP,AO(2,12) ,GRPART(2,12)*DELT,AFLOSS(8,2,12),

OALOSS(2,12) ,A(2,12)

END IF

IF(ZM.LE.O.)GO TO 1571

WRITE(9,245)TSTEP, (BC1,M) ,M=1,12)

WRITE(13,245)TSTEP, (B(2,M) ,M=2,12)

IF(BLOSS(1,12) .GT.O.)THEN

wRITE-(4,420)TSTEP,80(1,12),AFLOSS(1,2,12),BLOSS(1,12),B(2,12),

*((AFLOSS(hI,1,12)/BLOSS(1,12)) ,M=-6,8)

C.* 26
ELSEI

WRITE(4,420)TSTEP,B0(1,12) ,AFLOSS(1,1,12) ,BLOSS(2,12),B(1,12)

END IF

IF(BLOSS(2,12) .GT.0.)THEN

WRITE(7,420)TSTEP,B0(2,12) ,AFLOSS(1,2,12) ,BLOSS(2,12) ,B(2,12),

O((AFLOSS(M,2,12)/BLOSS(2,12)) ,M=8,8)

ELSE

WRITE(7,420)TSTEP,B0C2,12),AFLOSS(1,2,12),BLOSS(2,12),BC2,12)

END IF

1571 CONTINUE

WRITE(12,245)TSTEP,FMASS(l) ,WAMASS(1) ,CMASS(1) ,VEMASS(l),

DOUTVEN (1)

TOTALRADMASS =FMASS(1) + WAMASS(l) + CMASS(1) +

VEMASS(l) +OUTVEN(l) + a(1,12)

WRITE (14,245) TSTEP, FMASS (2) ,WAMASS (2) ,CMASS (2) ,VEMASS (2),

DOUTVEN (2)

TOTALSMKMASS = FMASS(2) + WAMASS(2) *CMASS(2) + VEMASS(2) +OUTVEN(2) + a(2,12)

IF((PLOTANS .EQ. 'Y') .OR. (PLOTANS .EQ. 'y')) THEN

WRITE (15,10) TSTEP,ZHL,VIF,VDF,TQACTR, QLOSSR,TQNETR,TMASSR,

THLUC,FMASS(1) ,WAMASS (1),CMASS (1)

.WRITE(16,20) VEMASS(l) ,OUTVEN(l) ,A(1,12) ,FMASS(2),WAMASS(2),

CMASS(2) ,VEUASS(2) ,OUTVEN(2) ,A(2,12),

TOTALRADMASS,TOTALSMKýMASS,TSPEC,ZR

ENDIF

10 FORMAT(12(1X,GI1.5))

20 FORMAT(24(2X,Gll.S))

END IF

DO 1575 ISZ=1,12

DO 1575 JT=1,2

AO(JT, ISZ)=A(JT,ISZ)

BO (JT, ISZ)=B (JT, ISZ)

1575 CONTINUE

IF(TSTEP .GT.10000.)DELT=100.0

TSTEP=TSTEP+DELT

ITSTEP=ITSTEP*1

GO TO 1100

1516 CONTINUE

C

C

C PRINT OUTPUT FOR END OF FUEL AND/OR RUN

C

1516 TSTEP=TSTEP-DELT

CONSUM= (GTMASS/TFUEL) *100.0

IF (TFUEL . T .GTMASS) THEN

WRITE (3,315) TSTEP ,CONSUM

WRITE (4 ,315) TSTEP,CONSUM

WRITE (5,315) TSTEP, CONSUM

WRITE(7,315) TSTEP,CONSUM

WRITE(8,315) TSTEP,CONSUM

WRITE(9,315) TSTEP,CONSUM

WRITE(11,315) TSTEP,CONSUM

WRITE(13,316) TSTEP,CONSUM

WRITE(10,315) TSTEP,CONSUM

END IF

IF(TFUEL.GT.GTMASS) GO TO 1620

WRITE (3,320) TSTEP

WRITE (4,320) TSTEP

WRITE (5, 320) TSTEP

WRITE (7,320) TSTEP

C .27
WRITECS, 320) TSTEP

WRITE(9,320)TSTEP

WRrTE(11, 320) TSTEP

WRITE (13, 320) TSTEP

wRrTE(10, 320) TSTEP

1520 IF(TSPEC .GT. TSTEP) THEN

NBO (1) = FUE-L(1, 1) =500000 .0.

AREC (1, 1)=0.00000002

TBURN(1, 1)=500000.0

YSMOK (1, 1) =0

YSMOK (1, 2) =0.

YSMOK (1, 3) =0

DO 1525 r=2,9

NBO(I)=0

FUEL (1,1) =0.O

AREC(I,l)=0.0

TBURN(I, 1)=0.0

1262 CONTINUE

FLAG=1.

TSTEP=TSTEP +DELT

GO TO 1.085

END IF

GO TO 1535

1530 TSTEP=TSTEP-DELT

WRITE(3,326)TSTEP

wRITE(4,326)TSTEP

WRITE (5,325) TSTEP

wRrTE(7,326)TSTEP

WRITE (8,325) TSTEP

WRITE (9, 325)TSTEP

WRITE (11,325) TSTEP

wRITE(13, 325) TSTEP

WRITE (10,325) TSTEP

1535 CONTINUE

CLOSE (UNIT=3)

CLOSE (uNIT=4)

CLOSE (UNIT=5)

CLOSE (UNIT=7)

CLOSE (UNIT=S)

CLOSE (UNIT=9)

CLOSE (UNIT=11)

CLOSE (UNIT=13)

CLOSE (UNIT= 10)

CLOSE(UNIT=12)

CLOSE (UNIT=14)

STOP

C

C END OF MAIN PROGRAM

C

END)

SUBROUTINE THERMO (T, DIF, MATER)

COMMON,'PARAI/RHOO (15),CPCA(15) ,CPCAM(15)

COMMONIPARA2/COND (15) ,CONDM (15)

DT=T-273.

DIF= (COND (MATER) -DT*CONDM (MATER) ) /(RHOO (MATER) *(CPCA (MATER)

C.*28
.t*DT*CPCAM(MATER)))

RETURN

END

SUBROUTINE TEMP(M,DELT,T1,T2,YE1 ,YHI,YC1,TDIF,TP,TN,DX,TH2O,

+TC02,V,NFLAG)

COMMON/PARA1/RHOO (15) ,CPCA (15) ,CPCAM (15)

DOUBLE PRECISION AH

IF(M.NE.1.OR.NFLAG.EQ.1)GO TO 5

AE=DELT*EXP ((14.07-5557 .) T1) /80.

YE2=1.+CYEl-1.)*EXP(-AE)

IF(T2.LT.363.)YE2=YE1

AH=DELT*EXP ((28.31-20560.)/Tl) /80.

YH2=1 . e(YHI-1.) .DEXP (-AH)

IF(T1 .LT.473 .)YH2=YH1

AC=DELT*EXP ((18.8-19362 . )/T1)/60.

YC2=1l. (YC1-1 .) EXP (-AC)

IF(TI.LT.923.)YC2=YC1

QCON=-2 .82ES*5.(YE2-YE1) IDELT- . 87E+*5.(YH2-YHI) /DELT-4 .08E+6.

4 (YC2-YC1)JDELT

TH20=TH20+101 . *(YE2-YEI) .V+ 101 . *(YH2-YH1) .V

TC02=TC02+975 .. (YC2-YC1)*iV

YEI=YE2

YHI=YH2

YCI=YC2

GO TO 10

5 QCON=-0.0

10 CONTINUE

A=RHOO(M)ii(CPCA(M)e. T1-273.) .CPCAM(M))

T2=TI+ ((TDIF*DELT/DX**2) *(TN-2 . TI.TP) .iQCON.DELT/A)

RETURN

END

SUBROUTINE ENDPT(Tl1,T12,T21,T22,TN1,TPNI,TN2,TPN2,M,DX,

*QA,CKD,THLC,NFLAG)

COMMON/PARA2/CDND (15) ,CONDM (16)

COMMON/PARA3/EMIS (15) ,TINIT, UMwIN ,WRADF

COMMON/PARA7/FE,DELT, THL, TCL

UO=0 .005. (ABS (ml -TINIT) ) is.3333.

IF (UO.LT.UMIN)UO=UMIN

U=-0.005. (ABS (THLC-T1) ) ** .3333

IF (U.LT.UMIN)U=-UMIN

IF (NFLAG.EQ. 1) THEN

CON=-COND (M.)

QR=-WRAOF

QA=QR-U. (TCL-T11)

GO TO 5

rEND IF

TA= (Tll+T12) /2.

CON=COND (M) -(TA-273 .) .CONDM (U)

QR=-5.889E-llis(THL**i4-Tll*si4)/ (1 ./EMIS(M)4-0.1111)

QA=-U. (THLC-T11) +QR

5 T12= (U'.THLC+T22*CON/DX-QR) /(CON/DX+U)

Th2= (CKD*TPN2+UOisTINIT) /(CKD*UO)

RETURN

END

SUBROUTINE RST1 (Q,TEND, GR,OFUEL,BR,SMOK,QT,VEL,XMAX1 ,XMAX2,

.tXUAXs)

C

C THIS SUBROUTINE CALCULATES THE MASS RATE AND SIZE DISTRIBUTION OF

C RADIOACTIVE PARTICLES GIVEN OFF FROM BURNING CONTAMINATED

C COMBUSTIBLE SOLIDS. THE INPUT PARAMETERS ARE DEFINED BELOW.

C

C.29
C q= GRAMS OF RADIOACIVE CONTAMINANT OF THE COMBUSTIBLE

C IFORM =1 IF CONTAMINANT IS A POWDER

C 2 IFCONTAMINANT IS AN AIR DRIED NITRATE SOLUTION

C 3 IF A LIQUID NITRATE SOLUTION

C I = COMBUSTIBLE MATE RIAL TYPE

C TEND = THE TIME WHEN THE COMBUSTIBLE IS BURNED UP (SEC)

C TSTEP = THE CURRENT TIME STEP AT WHICH THE SUBROUTINE IS CALLED (SEC)

C DELT = TIME STEP INCREMENT

C JACT = RADIOACTIVITY IDENTIFIER (NUMERIC)

C OFUEL = ORIGINAL MASS OF COMBUSTIBLE (G)

C BOR = BURN RATE OF COMBUSTIBLE (Q/S)

C SMOK = RATE OF SMOKE GIVEN OFF IN THE TIMESTEP (G/S)

C VT TOTAL HEAT FLUX (KW/M2)

C VEL =AIR VELOCITY (M/S)

C J=.BURN MODE

C

C OUTPUT PARAMETERS ARE:

C

C GR =TOTAL MASS RATE OF RADIOACTIVE PARTICLES GIVEN OFF (G/SEC)

C QMR =MASS RATE OF RADIOAtTIVE PARTICLES GIVEN OF FOR EACH

C BIN (G/SEC)

C

C

COMMON/PARA5/rFORM, I,TSTEP, QMR (11,10) ,JACT, J

COMMON/PARA7/FE,DELT, TlL ,TCL

DIMENSION SFRAC(11 ,8)

C SFRAC IS THE FRACTION OF RADIOACTIVE PARTICLES IN EACH SIZE BIN FROM

C BURNING 1)PMMA-PWsVR CONT., 2)PMMA-NONPWDR CONT., 3)PS, 4)PVC OR PC,

C 5) WOOD OR PAPER, AND S)OTHER

DATA SFRACf2*0.0,0.042,0.043,2.O.05,0.215,0.415,0.11,0.075,0.0,

3*30.0,2.0.015,0.022,0. 128,0.47,0.19,0.125,0.035,

+0.0,0.086,0 1082,0.078,0.085,0.66,0.14,0.337,0*.078,0.05,0.025,

+0.05,0.1,0.075,0.055,0.05,0.04,0.122,0.226,0.08,0.09,0.11/

GR=0.

IF(I.GT.1)GO TO 10

IF(IFORM.GT.1)GO TO 5

GR=0 .06q/DELT

LF=1

GO TO 16

6 IF (IFORM. EQ.2) ORcO.007 .Q/ PELT

IF (IFORM. Eq.3) GR=0 .02.Q/DELT

LF=2

GO TO 16

10 IF(I.GT.2)GO TO 20

GR=0 .02*QfDELT

LF=3

16 Q=0.0

00 TO 90

20 CONTINUE

IF(I.GT.4)GO TO 30

SRATE=SMOK/OFUEL

IF(TFORM. LT. 3) GR=0.0227*Q.SRATE

IF (IFORM.EQ. 3) GR=0 .104*Q*SRATE

PMAX=XmAX1

XMAX1=XMAX1+GR*DELT

TMAX=0 . 05Q

IF (XMAX . GT .TMAX)THEN

GR= (TbIAX-PMAX) IOELT

Q=0 .0

C.*30
END IF

LF=4

GO TO 90

30 IF( BR .EQ. 0.0 ) GOTO 45

IF (I.GT.S)GO TO 40

IF(IFORM.GT.l)GO TO 35

IF (J NE.1) GR= . 64E-S*BR*Q

IF (J .EQ.1) GR=6 . 7E-4*Q*BR* CQ/OFUEL) *QT*VEL

IF (XMAX2 .EQ.0.0)GR=GR+1 .0E-4*Q/DELT

PMAX=XMAX2

XMAX2=XMAX2+GR*.DELT.

TMAX=0 .01*Q

IF (XMAX2 . T. TMAX) THEN

GR= (TMAX-PMAX) /DELT

Q=0.0

END IF

LF=6

GO TO 90 35 IF(IFORM.EQ.2)GR=7.40E-7*Q*BR*QT

IF (IFORM .EQ.3) GR=6 . 0E-8*Q*BR*QT

PMAX=XMAX3

XMAX3=XMAX3+GR*DELT

TMAX=0 .01*Q

ITF(XMAX3 .GT .TUAX) THEN

GR= (TMAX-PMAX) /DELT

Q=0 .0

END IF

LF=6

GO TO 90

40 TM = OFUEL / BR

45 GR=0.01*Q/TM

LF=6

90 DO 95 L=1,11

.QMR(L,JACT)=SFRAC(L,LF) *GR

95 CONTINUE

IF(TEND.NE.0. .AND.TSTEP.EQ.TEND)Q=0.

100 RETURN

END

SUBROUTINE RST2 (Q, IFORM, GR, QUR, JACT~, SMOKFR ,FUEL,BR)

C

C THIS SUBROUTINE CALCULATES THE MASS RATE AND SIZE DISTRIBUTION OF

C RADIOACTIVE PARTICLES GIVEN OFF FROM BURNING CONTAMINATED

C COMBUSTIBLE LIQUIDS. THE INPUT PARAMETERS ARE DEFINED BELOW:

C

C .Q = GRAMS OF RADIOACTIVE CONTAMINANT IN THE LIQUID

C IFORM = 1 IF CONTAMINANT IS NON OR SEMIVOLATILE

C 2 IF CONTAMINANT IS VOLATILE

C TM = THE TIME IT WOULD TAKE TO BURN ALL.OF THE COMBUSTIBLE LIQUID

C AT THE CURRENT BURN RATE (SEC)

C SMOKFR = SMOKE RATE / TOTAL GRAMS LIQUID FUEL (FRAC/S)

C JACT = RADIOACTIVITY IDENTIFIER (NUMERIC)

C FUEL = MASS OF COMBUSTIBLE (G)

C BR = BURN RATE OF COMBUSTIBLE (G/S)

C

C OUTPUT PARAMETERS ARE:

C

C GR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OFF DURING BURNING

C (G/SEC)

C QMR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OF FOR EACH

C BIN (G/SEC)

C

C .31
DIMENSION QMR(11,JACT) ,SFRAC(11)

DATA SFRAC/.05,.21,.16,.20,.11,..06,.08,.108,.029,.003,0.0/

GR=O.

IF(IFORM.GT.1)GO TO 10

GR=1 .38*SMOKFR*Q

GO TO 20

10 TM=-FUEL/BR

GR=. 84*Q/TM

20 DO 30 L=1,11

QMR CL, JACT) =SFRAC (L) *GR

30 CONTINUE

RETURN

END

SUBROUTINE RST3 (Q,GR,DELT,QMR, JACT,T)

C

C THIS SUBTOUTINE CALCULATES THE MASS RATE AND SIZE DISTRIBUTION OF

C RADIOACTIVE PARTICLES GIVEN OFF FROM HEATING CONTAMINATED SURFACES.

C INPUT PARAMETERS ARE:

C

C Q = GRAMS OF CONTAMINANT ON AFFECTED HEATED SURFACE

C T = TEMPERATURE OF THE SURFACE

C JACT = RADIOACTIVITY IDENTIFIER (NUMERIC)

C

C OUTPUT PARAMETERS ARE:

C

C GR =TOTAL MASS RATE OF RADIOACIVE PARTICLES GIVEN OFF (G/SEC)

C QMR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OF FOR EACH

C BIN (G/SEC)

C

DIMENSION QMR (11, JACT)

6 GR=1.379E-12*(T**2)*Q

Q=Q-GR*DELT

IF(Q.LE.0.0) GO TO 10

7 QMR(9,JACT)=.0002*GR

QMR dO, JACT) =. 1408*GR

QMRC11,JACT)=.SS*GR

.10 RETURN

END

SUBROUTINE RST4 (Q,VOL, IVES,TSTEP,T,VEL,TL,

IDELT,RBOIL, GR,QMR, JACT)

C

C THIS SUBROUTINE CALCULATES THE MASS RATE AND SIZE DISTRIBUTION OF

C OF RADIOACTIVE PARTICLES GIVEN OFF DURING THE HEATING AND BOILING

C OF UNPRESSURIZED RADIOACTIVE LIQUIDS.

C INPUT PARAMETERS ARE:

C

C = GRAMS OF RADIOACTIVE MATERIAL IN THE LIQUID

C VOL =MILILITERS OF RADIOACTIVE LIQUID IN THE CONTAINER AT THE

C CURRENT TIME STEP - CORRECTIONS MADE WITHIN THE SUBROUTINE

C TO REDUCE THE VOLUME AS THE LIQUID BOILS

C IVES =NUMBER OF THE VESSEL FROM WHICH SOURCE TERM IS GENERATED

C - UP TO 10 VESSELS CAN BE SPECIFIED.

C TSTEP =CURRENT TIME STEP (SEC)

C DELT =WIDTH OF THE TIME STEP INCREMENT

C TL =TEMPERATURE OF PREBOILING LIQUID

C VEL =VELOCITY OF AIR FLOW OVER RESIDUE AFTER BURNING

ýc RBOIL= BOILING RATE OF LIQUID

C JACT RADIOACTIVITY IDENTIFIER (NUMERIC)

C

C OUTPUT PARAMETERS ARE:

C

C .32
C GR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OFF DURING THE

C PREBOILING, BOILING, OR ENTRAINMENT OF RESIDUE (G/SEC)

C QMR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OF FOR EACH

C BIN (G/SEC)

C

C UNPRESSURIZED LIQUIDS ARE CONSIDERED PREBOILING IF THE BOILING RATE IS

C LESS THAN .4 ML/MIN, AND BOILING IF OVER THAT RATE. RELEASES FROM

C HEATING OF RESIDUE START WHEN THE VOLUME OF LIQUID IS DOWN TO ZERO

C AND THE LIQUID HAS BOILED AWAY. THESE RELEASES CONTINUE FOR TWO HOURS.

C IFLAG(IVES) EQUALS 2 WHEN THE LIQUID HAS BOILED AWAY SO THAT THE

C HEATING OF RESIDUE RELEASES ARE ONLY CALCULATED ONCE.

C

DIMENSION VOLC10) ,RBOIL(10) ,IFLAG(10) ,QMR(11,JACT)

GR=0.

IF(VOL(IVES).LE.0.) GO TO 30

IF(RBOIL(IVES).GE.0.4)GO TO 10

GR=9.57E-15*(TL**2) *Q

GO TO 20

10 IF(RBOIL(IVES).GT.0.6)GO TO 40

GR=5 .0E-10*Q

GO TO 20

40 GR= (5.74E-7*RBOIL (IVES) -3 .42E-7) *Q

GO TO 20

30 IF(IFLAG(IVES).EQ.2) GO TO 50

T2=TSTEP+7200.

IFLAG (IVES) =2

50 IF(TSTEP.LE.T2) GO TO 80

Q=0 .0

DO 55 L=1,11

QMR(L,JACT)=0.0

55 CONTINUE

GO TO 90

60 GR=(7.37E-12*T+7.61E-11*VEL)*Q

20 CONTINUE

QMR (9, JACT) =. O3*GR

QMR(10,JACT) =.42*GR

QMR (11, JACT) =. SS*GR

90 RETURN

END

C

C

SUBROUTINE RSTS(Q,PF2,VOL,PDEN,GR,QMR,JACT)

C INTERIM SUBROUTINE FOR PRESSURIZED POWDER RELEASES.

C RELEASE= F(PF2,Q) WHERE PF2 IS THE FAILURE PRESSURE

C OF THE CONTAINER AND Q IS THE SOURCE QUANTITY.

DIMENSION QMR (11, JACT)

PF2=PF2*1.013E+5 !Convert atm to Pa

XM=Q*1000.0 !Convert 9 to kg

VOID =VOL - (Q/PDEN)

VEL =((2 * PF2 * VOID)/XM)**0.5

GR=(lE+4 * (VEL**1.4))

QMR(1,JACT)=.OaGR

QMR(2, JACT)= .02*GR

QMR(3,JACT)=.02*GR

QMR(4, JACT)= .O15*GR

QMR(S,JACT)=.02*GR

QMR(6, JACT)=.O15*GR

QMR(7,JACT)=.07*GR

QMR(8, JACT) . 20*GR

QMR(9, JACT)=.11*GR

C. 33
QMR (10, JACT)=. 15*GR

QMR (11, JACT)=.318*GR

RETURN

END

C

C

SUBROUTINE RST6 (Q, GR, QMR, JACT)

C SUBROUTINE FOR PRESSURIZED LIQUID RELEASES.

DIMENSION QMR (11, JACT)

GR=0.1 * Q

QMR (1,JACT)=.O*GR

QMR(2, JACT)=.01*GR

QIAR(3, JACT)=.O15*GR

QUR (4, JACT)= .02*GR

QMR (5,JACT)=.O5S*GR

QMR (6, JACT) =.02*GR

QMR(7 ,JACT)=.09.GR

QMR(S,JACT)=.27.GR

QUR (9,JACT)=.15*GR

QMR (10, JACT) =. 18*GR

QMR (11 ,JACT)=.23.GR

RETURN

END

SUBROUTINE RST7 (Q,SQ,GR, TSTEP, IBO, QMR, JACT)

C

C

C

C THIS SUBROUTINE CALCULATES THE MASS RATE AND SIZE DISTRIBUTION OF

C PARTICLES GIVEN OFF FROM BURNING RADIOACTIVE PYROPHONIC METALS.

C INPUT PARAMETERS ARE:

C

C Q = GRAMS OF RADIOACTIVE MATERIAL BEING BURNED

C IBO =BURN ORDER OF RADIOACTIVE MATERIAL - DETERMINS WHEN.THE

C STARTS BURNING

C SQ =SIZE OF METAL PIECES (G)

C TSTEP =TIME STEP

C JACT =RADIOACTIVITY IDENTIFIER (NUMERIC)

C

C OUTPUT PARAMETERS ARE:

C

C GR =TOTAL MASS RATE OF RADIOACTIVE PARTICLES GIVEN OFF (G/SEC)

C QMR =MASS RATE OF RADIOACTIVE PARTICLES GIVEN OF FOR EACH

C BIN (G/SEC)

C

C SINCE THE SOURCE TERM IS CONSTANT OVER TIME IT ONLY NEEDS TO

C BE CALCULATED ONCE. HENCE rFLAG=l WHEN THE SOURCE TERM HAS BEEN

C CAt.CULATED SO IT WILL NOT BE ADDED TO THE TOTAL AT ANOTHER TIME.

C IT.IS ASSUMED THE RELEASE TAKES PLACE OVER 30 MINUTES.

C

DIMENSION IFLAG(100) ,QMR(11,JACT)

GRp:0.

IF(IFLAG(ISO).EQ.1)GO TO 10

T2=TSTEP+3800.

ZFLAG (IBO) =1

10 IF(TSTEP.LE.T2)GO TO 30

Q=0 .0

DO 40 L=1,11

QMR (L, JACT)=0.O

40 CONTINUE

C .34
GO TO 20

30 GR=1 . 86-14. (SQ**2) .Q

QMR(6, JACT)=.OOS*GR

QMR(7,JACT)=.036*GR

QUR(B, JACT)=.98.GR

20 RETURN

END

FUNCTION UINS(XI,X2,X3,X4,XS,XS)

DIMENSION CC (16) ,C1(18) ,C2 (16) ,C3 (18) , B(5) ,B(6) ,B2 (8) ,B3(6)

DATA CC/0.,32.,100.,200.,300.,400.,500.,800.,700., 800 .,900.

+,1000.,1500.,2000.,3000./

DATA C1/2*4.2E.08,3.18E.*06,1.78E+06,8.5E+05,4.44E+05,2.58E+05,

.+1.59E+06,1.06E.05,7.04E+04,4.98E.+04,3.8E+04,2.85E+04,7.45E+03,

+2.84E+03,816./

DATA C2/0.,3.25E+04,2.059E.04,9.lE.03,4.06E+03,1.86E+03,990.,

+530. ,366. ,206. ,138. ,95. ,38.1,9.22,2.025,0./

DATA C3/2.0.,32.,100.,200.,300.,400.,500.,800.,700.,800.,900.,

+1000. ,1500. ,2000. ,0./

DATA BB/0.,600.,1000.,2000.,3000./

DATA B1/2*.0133, .0231, .0319, .0471, .054/

DATA B2/0. ,1.96E-05,1.76E-05,1.52E-05,6.gE-06,0./

DATA B3/2*0.,SOO.,1000.,2000.,0./

XF=X2*1 .8-480.

XL=Xl*3 .28084

XD=X3*1 .8

DO 10 Iml,IS

IFCXF.LE-.CCCI))GO TO 11

10 CONTINUE

I1=16

11 GP=C1(Il)-C2(I1)*(XF-C3(I1))

GP=GP*X2/X8

GRPR=GPiXD. (XL**3 .) *0.7* (X2/X4) ..2

C

C GRPR = PRODUCT OF GRASHOFF NO. AND PRANDTL NO. (.7) FOR AIR

C

C COND OF AIR = AIRCON

C

DO 15 1=1,5

12=I

IF(XF.LE-.BB(I))GO TO 16

1S CONTINUE

12=6

16 AIRCON=Bl (12) +82 (12). (XF-B3 (12))

C

C CHANGE UNITS TO (KW/M-K)

C

AIRCON=AIRCON. 1 .7298E-03

WR=X5.3 .28084/4.

IF(XL.NE.0.0)GO TO 17

GPTEST=0 .0

GO TO 18

17 GPTEST=GRPR*WR/XL

18 BMUSS=0 . 085GPTEST

IF (GPTEST .GE.20.) BNUSS=0 .42* (GPTEST) ** .25

UINS=BNIJSS*AIRCON/WR

RETURN

END

FUNCTION AKSH(81,82,B3,B4,B5,BS,B7)

C AKSH calculate.s the evaporative mass transfer coeff. for

C vessel type four-open liquid surface

C.*35
C Product of Grashof and Schmidt number, GrSc, first assume C film properties as average between surface and bulk gas

TFILM2=(88.eB7)/2 .0

RHOFL4= (B2.B3) /2.0

ZETA2= (B4.11 .0/(8 .208E-5*B7*B3)) /2.0

XVAP=B5/2 .0

C Viscosity of steam air mixtures from CORRAL code

C ( WASH-1400, App.VII, Page VII-243)

TR=1 . BTFILM2

TRIPS=TR*SQRT CTR)

VST=0.003339*TRIP6/ (TR+e1224.2)

VAIR=0.S414. (TR/492.0)**0.768

PAS=(1.0.SQRT((VAIR/VST)*SQRT(18./29.)))**2./4.5704

PSA=(1.0.SQRT((VST/VAIR)*SQRT(29./l8.)))**2./3.6008

RMOL=XVAP/ (:1.0-XVAP)

VIAIX=VAIR/ (1. 0.RMOL*PAS) .VST/ Cl. S+PSA*RMOL)

Vk(IX=4 .134 E-04*VMIX

C VUIX has unit of KG/MS

C Diffusivity of steam/air mixtures from program BUBBLE

RU=0.300084

Al=0 .00214-0 .000492.RM

.SIG=3 .129

EPS=2 80.1

OMEGA=0 .7075.0.734 IaEPS/TFILM2

DIFF=Als (TFILM2.#1 .5) RM/ (OMEGA.SIG**2 .0)

DIFF=1 .OE-04.OIFF

C DIFF has unit of M*M/S

GRSC=(B1*s3 .0)*RHOFLM.9.8.ZETA2*XVAP/(VMIX*DIFF)

IF(RHOFLM.LT.B3 .AND. GRSC.GT.1.OE+e07)

1SH=0.14. (GRSC)**(1 ./3.)

IF(RIIOFLM.LT.B3 .AND. GRSC.LE.l.OE.07)

lSH=0. 54 *(GRSC)**.(0.25)

C Correlations 8.36C, P.283,.Natural Convection Heat and

C Mass Transfer, Y.J Al~uria, Pergamon, Oxford,1980.

.IF(RIIOFLM.GE.B3)SH=0.58a (GRSC) .a0.2

C Correlation 8.348 above

AKSH=SH*DIFF/B1

C AKSH has unit of U/S

RETURN

END

SUBROUTINE PDMECH

DOUBLE PRECISION XN,XM,RLOSS1,RLOSS2

REAL LR

COUMON/PARA8/FMH20, FMHO2, FMHN2, FMCOI, FMCO2, LR, WR,Z,

@ZM,TAVWH,TAVWC,TCAV,TFAV,PCOMP,FHL,FCL,DPART(11),

*HLR,FRAC(8,12),DX,GRPART(2,12),A(2,12),B(2,12),

0A0(2,12),BO(2,12),ALOSS(2,12),BLOSS(2,12),FRACF(11),

*FRACW(l1) ,FRACC (11) ,FLAG

COUMON/DEPL/VCL, RLOSS2, VSET1, AFLOOR ,VHL, XM, XN, RLOSS1

COMMON/PARA? /FE, DELT, THU TCL

AFLOOR=LR*WR

THAVW=-(THL+tTAVWH)/2.

TCAVW= (TCL+eTAVWC) /2.

TAVC= CTHL*TCAY) /2.

TAVF= (THL+TFAV) /2.

.AHL=2. *(ZR-ZU) *(LR+WR)

ACL=2 . ZU. CLR.*WR)

VHL= (ZR-ZU) aAFLOOR

.VCL=ZM*AFLOOR

XMID= (4*AFLOOR*FE) /VHL

XNCFMHO2.*FMHN2+eFMCOI+.FMC02

C .36
CALL VISC (THL, FMH2O, FMHO2 ,FMHN2 ,FMCO1 ,FMCO2,AMWH,VISMIX,AKG)

CALL VISC(TCL,0.0,0.21,0.79,0.0,0.0,AMWC,VISAIR,AKG2)

RHOGASH=AMWII*PCOMP/(C.08206*THL) ! RHO IN KG/M**3

VT=1.E-B*-HLR/CCAFLOOR+eAHL)*RHOGASH) WVT IN M/S

RHOGASH=RHOGASH/ 1000. MRHO IN G/CM**3

CALL VDIFFU(FMH2O,XNC,PCOMP,AMWH,THAVW,RHOGASH,VDW)

CALL VDIFFU(FMH2O,XNC, PCOMP,AMWH,TAVC,RHOGASH,VDC)

CALL VDIFFU(FMH2D,XNC,PCOMP,AMWH,TAVF,RHOGASH,VDF)

DO 5 ISZ=l,ll

CALL DIFFU(DPART(ISZ) ,VISMIX,THL,AMWH,PCOMP,DIFUS, CM, ELAM)

CALL VSETL(CM,DPART(ISZ) ,VISMIX,AMWH, PCOMP,THL, RHOGASH, VSETI)

CALL VBROWN(THL, THAVW,VISMIX, RHOGASH,DX,DIFUS,VBDW)

CALL VBROWN(THLJ TAYC, VISMIX, RHOGASH,DX,OIFUS,VBDC)

IF(VCL.LE.0.)THEN

CALL VBROWN (THL, TAVF,VISMIX,RHOGASH,DX,DIFUS,VBOF)

TVSET=VSET1 *AFLOOR

TVBD= (VBDC.VBDF) *AFLOOR.VBDW*AHL

TVTH=VT* (AHLe2. *AFLOOR)

TVD= (VDC+iVDF) *AFLOOR.VDW*AHL

FLOOR=CVSETI.VBDF+eVT.VDF) sAFLOOR

WALL= (VBDW.VT.VDW) *AHL

CEIL= (VBDC+eVT.VDC) *AFLOOR

TVHL=TVSET+TVBD+TVTH+TVDtFHL

RLOSSI=TVI4L/VHL

FRACC6,ISZ)=0.

FRAC(7,ISZ)=0.

FRAC CS, ISZ) =0.

FRACF (ISZ) =FLOOR/TVHL

EX1=EXP (-RLOSSI*DELIt)

DO 3 JT=1,2

A(JT,ISZ)=AO(JT,ISZ)*EX1.(GRPART(JT,ISZ)/RLOSS1)*(l.-EX1)

ALOSS(JT,ISZ)=RLOSSI*(AO(JT,ISZ)*(EX1-1.)/-RLOSS1.GRPART(JT,

o ISZ) *DELT/RLOSS1.GRPART (JT, ISZ) *(EXI-1 .)/RLOSS1**2.)

BCJT,ISZ)=0.

BLOSS(JT, ISZ)=O.

3 CONTINUE

GO TO 4

END IF

TVSET=VSET1 *AFLOOR

TVBD=VBDC *AFLOOR4VBDW* AHL

TVTH=VT* (AHL+eAFLOOR)

T VD=VDC *AFLO OR VD W* AHL

CEIL= (VBDC.VT+eVDC) *AFLOOR

WALL= (VBDW.VT.VDW) *AKL

TVHL=TVSET+TVBD.TVTH.TVD.FHL

RLOSS1=TVHL/VHL

CALL DIFFU(DPAR.T(ISZ) ,VISAIR,TCL,AMWC, PCOMP,DIFUS,CM, ELAM)

CALL VSETL(CM,DPART CISZ) ,VISAIR,AMWC,PCOMP,TCL,.RHOGAS,VSET2)

TVCL=VSET2*AFLDOR.FCL.FE

FLOOR=VSET2*AFLOOR

RLOSS2=TVCL/VCL

IF(FLAG.EQ.1.)THEN

EX1=EXP (-RLOSSI*DELT)

EX2=EXP (-RLOSS2*DELT)

XX= (VSET1*AFLOOR/VHL) /(RLOSSI-RLOSS2)

DO 10 JT=1,2

ACJT,ISZ)=AO(JT,ISZ):EXI ~ B(JT,ISZ)=BO(JT,ISZ) EZX+,X*XA0(JT,ISZ)*(EX2-EX1)

ALOSS (JT, ISZ) =A0 (JT, ISZ) * I-EXI)

BLOSS(JT,ISZ)=(BO(JT,ISZ)+XX.AO(JT,ISZ))*(l-EX2).RLOSS2*XX*

GAO CJT, ISZ)* CEXl-1) /RLOSSI

CAT 3
10 CONTINUE

00 TO 8

END IF

TV=TVHL.tTVCL

XN= (-RLOSS1-RLOSS2-SQRT(RLOSS2**2 . RLOSS1**2 .- 2 .*RLOSS1*RLOSS2

0* (VSETI*XMID) /VCL) )/2.

XM=--RLOSS2-RLOSSI-XN

DO 6 JT=1,2

CALL DEPLETE(AO(JT,ISZ) ,BO(JT,ISZ) ,GRPART(JT,ISZ) ,A(JT,ISZ),

0B(JT,ISZ) ,ALOSS(JT,ISZ) ,BLOSS(JT,ISZ))

6 CONTINUE

FRAC (6, ISZ)=VSET2*AFLOORfTVCL

FRAC (7,ISZ)=FCL/TVCL

FRAC (8,ISZ)=-FE/TVCL

FRACF (ISZ) =FLOOR/TVCL

4 FRAC (1,ISZ) =(TVSET) /TVHL

FRAC.(2, ISZ) =TVBD/TVHL

FRAC (3,ISZ) =TVTH/TVHL

FRAC (4, ISZ) =TVD/TVHL

.FRAC (5,ISZ) =FHL/TVHL

FRACW (ISZ) =WALL/TVHL

FRACC (ISZ) =CEIL/TVHL

5 CONTINUE

RETURN

END

SUBROUTINE VISC(TB,XH2O,X02,XN2, XCO,XCO2 ,AMW,VISMIX,AKG)

DIMENSION Y(5) ,VS(5) ,WM(5) ,Z(5) ,PHI(5,5) ,VK(6)

SQRTTB=SQRT (TB)

EPSH20=809 .1

EPS02=113 .0

EPSN2=91 .5

EPSCO=120.

EPSCO2=190.

SIGH2O=2 .841

S1002=3 .433

SIGN2=3 .681

SIGCO=3 .69

SIGC02=3 .996

AMW=-XC02*44 . XCO.28. +XH2DO18 . *X2*32 .*XN2u.28.

OMH2O=0 .765*0. 82*EPSH2O/TB

VISH20=2 .8693E-05*SQRT (18. .TB) /((SIGH2O**2 .) *OMH2O)

0M02=0 .765*0. 82*EPS02/TB

OMN2=0 .765+0. 82.EPSN2/TB

OMCO=0.766*0.82*EPSCO/TB

OMCO2=0 .78650. 82*EPSCO2/TB

VIS02=2 .8693E-5*SQRT (32. *TB)/I( (SIG02**2 .) .0M02)

VISN2=2 .6693E-5*SQRT (28. *TB) /((SIGN2**2 .) *OMN2)

VISCO=2 .6693E-5.SQRT (28. *TB) /(C(SIGCO**2 .) *OMCO)

VISC02=2 .6693E-5'.SQRT (44. *TB) / ((SIGC02.*2 .) .OMC02)

AKGH20= (. 326BugSQRTTB-3 .9179) /10000.

AKOO2= ( .2982*SQRTTB-2 .4884)/10000.

AKCN2= ( .2695.SQRTTB-2 .0577)/10000.

AKOCO= C.2583 *SQRTTB-1 .9407) /10000.

AKGCO2= ( .2795'SQRTTB-3 .1296) /10000.

C AKG IN WATTS/CU/K

Y (1)=XH20

Y (2)=X02

Y(3)=XN2

Y(4)=XCO

Y(S)=XC02

VS (1)=VISH2O

C .38
VS(2)=VISO2

VS (3) =VISN2

vs (4) =VISCO

VS (5) =VISCO2

VK(1) =AKGH2O

VK(2) =AKGO2

,VK (3) =AKGN2

VK (4) =AKGCO

VK (6) =AKGCO2

WM (1) =18.

WM(2)=32.

WM(3)=28.

WM(4)=28.

WM(S) =44.

DO 301 J=1,6

DO 301 I=1,6

301 CONTINUE

DO 302 I=1,6

DO 302 .1=1,g

Z(I)=Z(I)4.Y(J)*PHI (I,J)

.302 CONTINUE

AKG=0.

VISMIX=0.

DO 303 I=1,0

VISMIX=VISMIX+Y (I) *VS (I) /Z (I)

AKG=AKG+Y (I) *VK (I) /Z (I)

303 CONTINUE

C

C VISMIX IN POISES. CALCULATIONS USE BSL PAGE 24

C

RETURN

END

SUBROUTINE DIFFU(DPART,VISMIX,TAV,AMW,PGAS,DIFUS, CM,ELAM)

C

C THIS SUBROUTINE CALCULATES PARTICLE DIFFUSIVITY, DIF(N)

C AS A FUNCTION OF PARTICLE SIZE

C

C INPUTS:

C DPkRT, VISMIX, TAY, AMW, PGAS

C

C CUNNINGHAM FACTOR, CM AND ELAM, MEAN FREE PATH OF GAS

C

P1=3.14159266

ELAM=1 .245E-02*(C(TAV/AMW) ** .5)*VISMIX/PGAS

IF(DPART.LT.I.E.+3)GO TO 95

RATD=ELAM/DPART

CM=1..2.492*RATD.+0.84*RATD*EXP(-0.435/RATD)

GO TO 90

95 CIA=1.

90 CONTINUE

DIFUS=1 .38E-18*TAV.CM/ (3.*PI*VISMIX*DPART)

C

C OUTPUT: DIFFUSIVITY, DIFUS IN CM**2/SEC

C

RETURN

END

SUBROUTINE VSETL (CM,DPAR-, VISMIX,AMW, PGAS, TAV, RHOGAS ,VSETI)

C CALCULATE SETTLING VELOCITIES NOW (VSET1)

C.*39
G=980.

RG=82 .06

VSETI=G*CM* (OPART) .2 ./(18 . VISMIX)

C

C FOLLOWING TAKEN FORM BNWL-1328, PAGE 12-13

C

RHOGAS=AMW*PGASJ (RG*TAV)

FDRE2=1 .3333*RHOGAS*G*(C(DPART) **3. ) /(VISMIX**2)

IF(FDRE2.GT.9.6.AND.FDRE2.LT.93.6)RE=(FDRE2/27.)**(l./1.13)

IF(FDRE2.GE.93.6.AND.FDRE2.LT.410.)RE=(FDRE2/24.32)**C1./2.227)

IF(FDRE2.GE.410..AND.FDRE2.LT.1.07E+4)RE=(FDRE2/15.71)**

0(1./i .417)

IF(FDRE2.GE.1.07E..4 .AND.FDRE2.LT.2.45E+S)RE=(FDRE2/8.4T7)**

e(1./1.609)

IF(FDRE2.GE.2.45E+S)RE=(FDRE2/1.194)**(1./1.867)

IF (FDRE2 .GT. 9.6) VSETI =RE*VISMIX/ (DPART*RHOGAS)

VSETI=VSET1/100. !YSET1 IN M/S

RETURN

END

SUBROUTINE VBROWN(T, TAVO, VISMIX, RHOGAS,DELTAX,DIFUS, VBD)

IF(T.LT.TAVG)THEN

VBD=0.

GO TO S

END IF

DELTAT= (T.-TAVG)

GR= (980.1 (VISMIX/RHOGAS) **2.) *DELTAT/TAVG* (DELTAX**3)

SC=VISMIX/ (RHOGAS*DIFUS)

VBD=0.13* (GR*SC) ** (1./3.) *(DIFUS/DELTAX)

S CONTINUE

RETURN

END

SUBROUTINE VDIFFU(XH20,XNC,PCOMP,AMW,TAVW, RHOGAS,VD)

AAP=3 .2437814

BP= . 868263E-03

CP=1 .17023793E-08

DP=2. 1878462E-03

X2A=647 .27-TAVW

IF(X2A.LE.o.)GO TO 90

XPONEN=- (X2A/TAVW) *(AAP*BP*X2A+CP* (X2A**3.) )/ (1. .DP*X2A)

P2A=218 .167*10. **XPONEN

PSAT=XH2O*PCOMP

IF(P2A.GE.PSAT)GO TO 90

IF(XH20.LE.0.)GO TO 5

HC=4 . 02E-02* (XH2O/ (XNC-XH20) )**0 .8

IF(HC.GT.0.16889)HC=0.15889 .!HC in watt/(cmn2*k)

GO TO 10

5 HC=0.

10 CONTINUE

XLAM-2267.

FLUX= (HC/XLAM) *(THL-TAVW)

if(flux.It.o.)flux~o

VD=(1.0-0.13*XNC).FLUX/RHOGAS/100. !VD IN M/S

GO TO 100

90 VD=O.

100 RETURN

END

SUBROUTINE DEPLETE(AU, 60, XM ,A, B,ALOSS ,BLOSS)

DOUBLE PRECISION XN,XM, RLOSS1 ,RLOSS.2,B2,A, B,ALOSS,BLOSS

COMMON/DEPL/VCL, RLOSS2 ,VSET1 ,AFLOOR,VHL,XM,XN, RLOSS1

COMMON/PARA7 /FE, DELT, THL,TCL

CS=-FE*BO/VCL+RLOSS2 .AO+XMII

C .40
DO=XMI*RLOSS2

A2= (VSETI*AFLOOR) /VHL

B2=-RLOSS2

XO=A2 *AO

YO=A2*CO

ZO=A2 *DO

XMIN=-300/DELT

IF (XM.LT.XMIN) XM=-XMIN

IF (XN.LT )(MIN) XN=XMIN

IF (82.LT.XMIN) 82=XMIN

EXI=EXP (XM*DELT)

EX2=EXP (XN*DELT)

EX3=EXP (82 *DELT)

D2=XM-XN

D2=XM-B2

D3=XN-.B2

A= (AG*(XM*EXI-XN*EX2) +CO*(EX1-EX2))/DID+DS* (1 .1(XM*XN)+

OEX2/ (-1 *XN*DI) *EX1/ (XM*Dl))

TI=EX-3/ (D2*D3)

T2=EXI/ (D2*D I)

T3=EX2/ (D3*- .*DI)

B=XO* (82*T1*XM*T2+XN*T3) +BO*EX3+YO* CTl+T2*T3) .ZO*

o (-1 / (B2*XM*XN) +T2/XM+T3fXN.+Tl/B2)

EX4=EXI-1.

EXS=EX2-1.

EX6=EX3-1.

ALOSS=AO* (EX4-EXS) /Dl+CO* (EX4/XM-EXS/XN) /D1.DS'.(DELT/

*(XM*XN).EXS/(-1.*D1*XN**2.)+EX4/(D1*XL4**2.))

ALOSS=ALOSS*RLOSS 1

T4=EX6/ (D2*D3)

TS=EX4/ (D2*DI)

T6=EXS/ (-1 .*D1'D3)

BLOSS=80.EX6/B2.XO* (T4.rS+T8) .YO* (T4/B2.+T5/XM

G*.T6/XN).ZO* (DELT/ (-1. *B2*XhI*XN) .eTSfXM**2 .i.T6/XN**2.

G+T4/B2**2.)

BLOSS=BLOSS*RLOSS2

RETURN

END

C .41

APPENDIX D

FIRIN PARAMETER DEFINITIONS

TABLE D.1. TABLE0.1. Variables with Only One Dimension

Name

Al

ABLOSS

AD 52

AE

AFLOOR

AHL

AI

AIRIN

AIROUT

AK

AMC L

AMHL

,ANAIR

ARAD

AWl

AW2

BTMAX

CC N2

CC02

CGRAD

CHCH4

CHCO1

CHCO2

CHH20

CHHCL

CH N2

CH02

CKDC

CKDF

CKDW

CONSUM

C P

CPAIR

CPL

C SMOKE

DELP

DELT

DEN OMi

DENOM2

OFT

DR

DR HOD X

Description

Constant used in concrete decomposition model

Total mass of particles depleted onto floor, g

Moles of air above powder in type 2 vessel, g moles

Equiva 'lent wal~l area receiving direct flame radiati .on, mn3

Floor area , m 2 Wall area in the hot layer, mn2

Equipment area exposed to heat transfer for type 3 equipment, in

'Air flow into hot layer, g mole

Airflow out of hot layer, g mole

Sherwood number mass transfer coefficient for nonboiling surface,

rn/s

Moles of gas in cold layer, g mole

Moles of gas in hot layer, g mole

Moles of air in vessel type 3, g mole2

Total area of equipment exposed to 2flame radiant heat transfer, mn

One wall area (length x height) m 2

Other wall area (width x height5, Mn

Maximum burn time, s

Moles of nitrogen in cold layer, g moles

Moles of oxygen in cold layer, g moles3

Concentration of radioactive particles in the hot layer, gum3

Moles of methane in the hot layer, g moles

Moles of carbon monoxide in the hot layer, g moles

Moles of carbon dioxi'de in the hot layer, g moles

Moles of water vapor in the hot layer, g moles

Moles of hydrochloric acid in the hot layer, g moles

Moles of nitrogen in the hot layer, g moles

Moles of oxygen in the hot layer, g moles

Conductivity/DXC, intermediate in ceiling heat transfer

calculations, kJ/m

Same as CKDC for floor

Same as OKDC for wall

Percent of total fuel consumed in the fire

Heat capacity, kJ/g mole K

Heat capacity of air, kJ/g mol~eK

Heat capacity of water, k.J/cm K3 Concentration of smoke in the hot layer, g/m3

Compartment pressure minus alternate flow path pressure, bars

Time step increment, s3

Denominator in filter plugging model for inlet filter, (atm s)/M3

Denominator in filter plugging model for inlet filter, (atm s)/m3

Change in temperature across the walls of equipment types 2 and 3, K

Equivalent diameter of floor, im

Denjity of air minus density of water vapor over type 4 vessel,

guM

D.1
TABLE 0.1. (contd)

Name Descri ption

DX Distance between vertical wall nodes, m

DXC Distance between ceiling nodes, m

DXF Distance between floor nodes, m

DXW Distance between wall nodes, m

EFFIC Efficiency of filters at start of fire, fraction

EIG Ignition energy available from previo s time step, kJ/m 2

EIGN Total ignition energy available, kJ/m

EL Height of gas layer in equipment types 2 and 3, m

ELV Constant in determining internal temperature and pressure of

type 3 equipment

EML Intermediate in determining internal temperature and pressure of

type 3 equipment, g

EML2 Intermediate similar to EML, g

EMV Intermediate similar to EML, g

EQT Total heat transferred to equipment, kW

EQUIP Equals 1 if modelling equipment option is implemented

ERAD Radiative heat flux to equipment from flame,k FCL Volumetric flow rate of gas into cold laye5 m /S

FE Volumetric flow of gases into hot layer, m 3/ FHL Volumetric flow rate of gas into hot layer, m3/

FIF Molar flow rate thru inlet filter, g mle/s

FIP Molar flow rate into the plume, g mole/s

FLAG Equals 1 if fire has stopped burning

FM Molar flow rate of gases into hot layer, g mole/s

FMCH4 Molar fraction of methane in the hot layer

FMC01 Molar fraction of carbon monoxide in the hot layer

FMC02 Molar fraction of carbon dioxide in the hot layer

FMH20 Molar fraction of water vapor in the hot layer

FMHCL Molar fraction of hydrochloric acid in the hot layer

FMHN2 Molar fraction of nitrogen in the hot layer

FMHO2 Molar fraction of oxygen in the hot layer

FMIF Molar flow rate of gases into the flame, g mole/s

FMO2 Mole percent of oxygen in the cold layer

FOB Molar rate of oxygen consumed, g mole/s

FMOF Molar flow rate of gases out of the flame, g mole/s

FN21F Molar flow rate of N2 into the flames from the cold layer, g mole/s

FN21P Molar flow rate of N2 into the plume

F021F Molar flow rate Of 02 into the flame from the cold layer, g mole/s

F021P Molar flow rate of 02 into the plume

FOF Molar flow rate through outlet filter, g mole/s

FPICLT Molar flow rate into cold layer from alternate flow paths, g mole/s

FPOCLT Molar flow rate out of cold layer to alternate flow paths, g mole/s

FPOCLV Volumetric flow rate of gases from the cold layer out alternate flow

paths,.m /s

D .2
TABLE D.1. (ctd (con'td)

Name

FPOHLT

FPO HLV

F PRAD

FPSMOK

FUN

GHL

GMOL

GR

GRAD

GTMASS

HLR

H LRAD

I

I BO

IE

I FORM

I FP

IGNITE

I NPUTFILE

IPRINT

ISIZE

I SZ

ITSTEP

I VES

1W

J2

J3

JACT

JACTO

JE

JF

JFORM

JT

JW

K

K3

LR

Description

Molar flow rate out of hot layer to alternate flow paths, g mole/s

Same as FPOCLV but for hot layer, m3/s

Mass flow rate of radioactive particles out of additional flow

paths, g/s

Rate of smoke out of additional flow paths, g/s

Molar flow rate of unreacted gases out of the flame, g mole/s

Total moles of gas in hot layer, g mole

Total moles of gas inside equipmpnt type 2, g miole/s

Acceleration due to gravity, m/s

Mass of radioactive material made airborne from release mechanism, g

Mass burned from all fUels, summed over time, g

Heat loss to room surfaces in hot layer, kW

Radiative heat from the fire to the hot layer, WJ

Fuel type

Burn order

Type of equipment

Form of radioactive material for release mechanisms 1 and 2

Number of alternate flow path

Equals 1 if autoignition energy option implemented

Dummy name for file holding input data

Number of iterations between printouts

Bin size for radioactive particle size distributions

Bin size for radioactive particle size distributions

Number of time steps

Number of vessels for radioactive release mechanisms 4, 5, and 6

Vertical wall nodes

Ventilation conditions ( 1 = overventilated, 2 =serniventilated.,

3 = underventilated)

Integer used to initi~alize arrays,

Nodes in ceiling

Integerused to initialize arrays

Radioactivity identifier

First JACT printout, 0

Nodes i~n wall, ceiling, floor

Number of equipment of type IE

Floor nodes

Form of radioactive material for release mechanism

1 = radioactive, 2 = smoke

Horizontal wall nodes,

Same as J

Iterations for determining internal T and P of type 3 vessel

Length of room, m

D.3
,TABLE D.1. (contd) (ond

Name

M

MATERC

MATERF

MATERW

MI BO

N2X2 IF

N2X2OF

NC

NFLAGC

NFLAGF

N FLAGW

NFP

NJ

NR ST

NT

NW

OKCL

OKCL1

OKCL2

OKCLF

OKDP

OKEl

OKE2

OKE3

OKE4

OKHL

OKHL1

OKHL2

OKHL F

OKPF

P1

PiCOM

P2

PCOMP

PG1

PG2

P I

PINIT

PLOTANS

PLP

P NC

PNW,

Description

Single integer for type of construction material1

'Ceiling construction material

Floor construction material

Wall construction material

Maximum burn order

Size equivalent of inlet filter in multiples of 2' x 2', integer

Same as N2X2IF except for outlet filter, i'nteger

Lowest vertical wall node in hot layer

Equals 1 when heat lransfer calculations are made for ceiling nodes

in the cold layer

Same as NFLAGC, but for wall nodes

Same as NFLAGC, but for floor nodes

Number of alternate flow paths

Combination of IFORM and I to make one parameter

Number of the radioactive source term mechanism

Vertical wall node

Number of wall nodes in the-hot layer

Equals 1 if flow is from cold layer out inlet filter.

Equals 1 if flow is from inlet filter to compartment cold layer

Equals 1 if outlet filter is in cold layer

Equals 1 if base of the fire is in the cold layer

Equals 1 if flow is into compartment through inlet vent

Equals 1 if the hot layer transfers heat to equipment type 1

Equals 1 if the hot layer transfers heat to equipment type 2

Equals 1 if the hot layer transfers heat to equipment type 3

Equals 1 if the hot layer transfers heat to equipment type 4

Equals 1 if flow from inlet filtter is into compartment hot layerEquals 1 if flow is from compartment hot'layer'out of inlet filter

Equals 1 if outlet filter is in hot layer

Equals 1 if base of the fire is in the hot layer

Equals 1 if plume height greater than 0.0

Initial pressure on other side of inlet vent, atm

Compartment pressure in previous time step, atm

Initial pressure on other side of outlet vent, atm

Compartment, pressure, atm

Intermediate pressure in determining internal T and P for type 3

equipment, atm

Intermediate pressure in determining internal ýT and P for type 3

equipment, atm

Initial pressure in fire compartment, atm:

Equals "Y" if user wants to output data to files to

graphics packages

Compartment pressure, bars

Number of vertical wall nodes in cold layer

Number of vertical wall nodes in'hot layer

be input to

DA.
TABLE D.1. (contd)

Name Description

PR Prandi number

PTEST Test to see if the internal pressure of vessels type 2.and 3 exceed

rupture pressure

PVAP Vapor pressure of radioactive liquid in type 4-vessels, atm

Q3 Heat rate to equipment type 3, kW

QC Convective heat transfer to the ceiling, kW2

QCA Convective heat transfer to the-ceiling: kW/m2_

QCOtMB Convective and radiative heat from the fire to the hot.-layer, kJ

QE-. External heat flux, kW/m 2 (negative of QFA),,

QF Convective heat transfer to the floor, kW2

QFA Convective heat transfer to the floor, kW/m2

QFRMAX Maximum radiative heat flux from flame to fuel,, kW/m2

QHL Heat in the hot layer, UJ

QIL Heat transferred to liquid in type 4 vessel, kW

QLOSSN Heat loss rate to all surfaces, Btu/h.

QLOSSR Rate of heat loss to all surfaces, kW

QLOST Heat loss to all surfaces, UJ 2

QT Total heat flux to burning fuel, kW/m

QW Convective heat transfer to-*the wall, kW

QWB Convective heat transferred to the wall in the hot layer for one

time step, kW/m 2

QWC Convective heat transfer to the wall in the cold layer,, kW

QWD Convective heat 2transfer to the wall in the cold layer for one

time step, kW/m2

QWH Convective heat transfer to the wall in the hot layer, kW

QZ Intermediate in Zukowski plume equation

QZM- Intermediate in Zuk 2wski plume equation

R Gas constant, atm m /g mole K

RESISTI Initial filter resistance of inl~et filter, atm m/s

RESISTO Initial filter resist-ance of outlet filter, atm m/s

REVAP Boil-off rate of liquid in type 4 vesse, ml/s

RHOGM Density of air above type 4 vessel,.g/m

RHOV Molar density of radioactive liquid evaporated from-type 4 equip-.

ment, g moles/rn

RHOVM Density of air and vapor above type.4 vessel , g/m3

RSMOK Smoke release rate, g/s,

SCALE Linear interpolation value for scaling combustion parameters to

lower and oxygen concentrations

SIG Stefan-Boltzmann constant, kW/m2 K4 '

SMOKER Weight fraction of fuel that is emitted as smoke

T Floor temperature, C

T1HL Temperature of-.the hot layer in the previous time--step, K

TA Temperature of air through inlet filter, K2 2

TAREC Total burning surface area of combustib~les, m

TAVWC Average wall temperature in the cold layer, K,

TAVWH Average wall temperature in the-hot layer, K

D.5
TABLE 0.1.. (contd)

Name Description

TB Average temperature of ty pe 2 and 3 equipment wall, K

TBG Temperature of the air above liquid in type 4 vessel, K

TCO Initial ceiling tempeerature

TCAV Ceiling temperature, KL

TCCO2 Carbon dioxides released from ceiling concrete in time step, g

TCH20 Water released from ceiling concrete in time step, g

TCL Temperature of the cold layer, K

TECL Time when the outlet ventilation duct and fire elevation are in hot

layer, s

TFAV Floor temperature, K

TFC02 Carbon dioxide released from floor concrete in time step, g

TFH20 Water released from floor concrete in time step, g

TFILM Film temperature above liquid in type 4 vessel, K

TFUEL Total weight of fuel, g

TGCH4 Total weight~of CH4 generated from all fuels in each time step, g

TGCO1 Total weight of CO generated from all fuels in each time step, g

TGCO2 Total weight of C02 generated from all fuels in each time step, g

TGH20 Total weight of H20 generated from all fuels in each time step, g

TGHCL Total weight of HCL generated from all fuels in each time step, g

TGRAD Total rate of radioactive particles generated in each time step, g/s

THL Temperature of the hot layer, K

THLC Temperature of gases touching the floor, K

THLUC Temperature of the hot layer, F

TIF Temperature of air through outlet filter, K

TIN Internal temperature of equipment type 3, K

TINIT Ini 'tial temperature in compartment, K

TLTEST Increase in temperature of liquid in type 4 vessel, K

TM Temperature at interface of hot layer and plume

TMASS Mass burned in the fire from all fuels for-current time step, g

TMASSN Mass burned in the fire plus concrete decomposition products for

current time step, lb/hr

TMASSR TMASSN in g/s

TMC Carbon in combustion products for one time step, g

'TMCL Chlorine in combustion products for one time step, g

TMH Hydrogen in combustion products for one time step, g

TMO Oxygen in combustion products for one time step, g

TMOLEN Total moles generated in the fire for current time step, g mole/s

TOF Temperature outside the flame (near the tip of the flame in the

plume), K

,TOTAL-RADMASS Total cumulative mass of radioactive material emitted from fire, g

TOTAL-SMKMASS Same as TOTAL-RAD-MASS, but for smoke, g

TQACT Total heat release from all fuels in each time step, UJ

TQACTN Rate of heat release from all fuels in each time step, Btu/hr

TQACTR TQACTN in kw

TQCON Convective fraction of TQACT, UJ

D.6
TABLE 0.1.(cnd (contd) . I

Name

TQ N T

TQ NETR

TQRAD

TR1

TR 5

TRED

TS

TSMOK

TSPEC

TSTEP

TSTEPO

TVH20

TWC02

TWH20

TWO

TZL

U14

UIN

UM IN

uO

UT4

V10

Vi HL

VC

VEL

VENT

VF

VIF

VOF

VOL CL

VOLKL

VOLRM

VW

WDT

WDW

WR

WRAD

WRADF

WRAD I

WRAD IF

WRADO

WRADOF

Description

Net heat to gases in current time step, Btu/hr

TQNET in kW

Radioactive fraction of TQACT, kJ'

Intermediate in determining internal, T and P of type 3 equipment

Temperature intermediate in vapor pressure equi'pment for equipment

type 4, K

Intermediate in determining internal T'and Pof type 3 equipment

Temperature outside vessel type 2 ,and.3', K

Total weight of smoke generated from all fuels-in'each time step., g

Maximum time step, s

Time step, 's

First time step printout, 'O,'Os

Intermediate in determining internal T ,and P of type 3-equipmentCarbon dioxide released from wall concrete in time'-step, g

Water released from wall, concrete, in time step, g

Init-ial wall temperature, K

Hot layer temperature'in the initial time step,: K

Into nal heat transfer coeffi~cient to liquid in type 4, vessel,

kW/mEK2

Internal heat transfer coefficient, kW/m K

Minimum convective heat transfer coefficient, kW/K

Outside convective heat transfer coefficient, kW/K

Heat transfer from top of-type.4 vessel,. kW/m2K

Volume of liquid in type 4 vessel,,' ml

Hot layer volume in previous time step

Ceiling volume x Al for conc6rete decompos'itiorn model'

Volumetric flow of gases into the plume divided 'by "combustion area,

m/s . .

Mass of particles challenging the outlet filters,g

Floor volume x Al for concrete decomposition model

Flow from inlet filter, m/s

Flow from outlet fil er, m/s

Cold layer volume,

Hot layer volume, m,

Fire compartment vo'lume,..m3- Wall volume exposed to hot 'layer x Al~.for concrete decomposition

model

Width of vessel type 2 and 3S m,

Width of vessel type 4, ft

Width of room, m

Radiative heat from the fire. to the cold l 'ayer, kJ,2 Radiative heat flux from the fliame'to the wall, kW/mn

Radioactive particles: on inlet filter from current time. step, g

Radioactive particles,,on,,inlet filter, g,

,Radioactive particles on'outlet filter from current time step, g

Radioactive particles on outlet filter,-g

0.7
TABLE D.1. (contd)

Name Description

WSMI Smoke deposited on inlet filter from current time step, g

WSMIF Smoke deposited on inlet filter, g

USMO Smoke deposited on outlet filter from current time step, g

WSMOF Smoke deposited on outlet filter, g

WSMOKE Smoke mass in the hot layer, g

WTOT1 Total loading on inlet filters from smoke and radioactive

particles, g

WTOT2 Same as WTOT1, but for outlet filters, g

XCEIL Ceiling thickness, m

XFLOOR Floor thickness, ml

NWALL Wall Thickness, m

ZETA Density of air minus water vapor/Density of air plus water vapor

above type 4 vessel

ZFIRE Fire elevation above floor, m

ZFLAME Flame height, m

ZHL Hot layer thickness, m

ZIF Elevation of midpoint of inlet vent, m

ZM Height of cold layer, m

ZOF Elevation of midpoint of outlet vent, m

ZPL Plume height, m

ZR Room height, m

ZTESTI Change in pressure across inlet filter,' atm

ZTEST2 Elevation of inlet filter minus height of cold layer, m

ZTEST3 Height of cold layer minus elevation of outlet filter, m

ZTEST4 Fire elevation minus cold layer height, m

ZTEST5 Hot/cold layer interface-minus fire elevation, m

ZTEST6 Hot/cold layer interface minus center line of exhaust ventilation, m

ZW Distance between wall nodes, m (vertical)

ZZ Room height minus (elevation of fire and flame height)

D .8
TABLE 0.2. Dimensioned Variables

Name Description

A Mass of particles in hot layer in current time step, g

AO Mass of particles in hot layer in previous time step, g

AFLOSS Mass of particles depleted from fire compartment by mechanism of

release, g

ALOSS Total mass of particles depleted'from hot layer by all mechanisms,

g ARBL Boiling area of type 4 vesselsm

AREC Burning surface area of combustiibles, m2

ARER Equipment area exposed to flame radiant he 2t tra .nsfer, m12

ARHT Equipment area exposed to heat transfer, m

B Mass of particles in cold layer in current time step, g

BO Mass of particles in cold layer in previous time'step, g

BLOSS Total mass of particles depleted from cold layer by all mechanisms,

g BRATE Mass burn rate, g/s

CMASS Mass of particles depleted onto ceiling, g

COND Thermal conductivity of construction material, kJ/m s K

CONDM Slope of change in thermal conductivity with temperature, kJ/m

CPCA Heat capacity of construction material, kJlkg K

CPCAM Slope of change in heat capacity with temperature,.kJ/kg

DFP Equivalent diameter of alternate flow path, m

DPART Average particle size for bins, micron

EMIS Emissivity of construction material

EQ Heat transfered to equipment, kJ

FAIL2 Equals 1 if type 2 vessel fails

FAIL3 Equals 1 if type 3 vessel fails

FMASS Mass of particles depleted onto floor, g

FPICL Flow into cold layer from alternate flow paths,T3/

FPIHL Flow into hot layer from alternate flow paths, m ý

FPOCL Flow out of cold layer to alternate flow paths, T/s

FPOHL Flow out of hot layer to alternate flow paths, m /s

FRAC Fraction of total loss attributed to each depletion mechanism for

each bin size

FRACC Fraction of particles depleted during current time step that

deplete onto ceiling

FRACF Same as FRACC, but for floor

FRACW Same as FRACC, but for wall

FUEL Mass loading of combustibles, g

GCH4 Weight of methane generated per materials for-each time step, g

GCO1 Same as GCH4, but for carbon monoxide, g

GCO2 Same as GCH4, but for carbon dioxide, g

GH20 Same as GCH4, but for water vapor, g

GHCL Same as GCH4, but for hydrochloric acid, g

GRPART Mass rate of particles generated in current time step, g/s

HEATC Net heat of complete combustion, kJ/g

HEATV Heat required to generate a unit mass of vapor, kJ/g

D.9
TABLE 0.2. (contd),

Name Description

HEQ Vessel height exposed to flame

HFP Elevation of alternate flow path above floor, m

HTF Base height of vessel above floor, inMASS Mass burned from each fuel during each time step, g

MATERE Construction material of specified'vessel

MJE Maximum number of each type of vessel

NBO Indicates use of autoignition energy option.

NRAD Number of inputs to each radioactive release mechanisms

OFUEL Original mass loading of combustibles,g

OKFHL Equals 1 if alternate flow path is-i~nthe 'hot layer

OKFP Equals 1 if alternate flow path is opened

OKPFI Equals 1 if flow is from alternate-flow paths into compartment

OKPFO Equals 1 if flow is out of compartment through alternate-flow paths

OUTVEN Mass of particles that escape out the' vent, g

PDEN Theoretical gens~ity of-powder invol~ved in powder pressurized

release, g/mf

PF2 Failure pressure of vessel type 2, atm

PF3 Failure pressure of vessel'type 3, atm

PFP Initial pressure on other side of alternate' flow path, atm

P12 Internal pressure of type 2 equipment; atm

P121 Initial internal pressure of type 2 equipment, atm

P13 Internal pressure of type 3 equipment, atm

QACT Total heat release from burning during each time step, UJ

QCHEAT Energy at which combustible auto ignites, kJ/m

QCON Convective fraction of QACT, UJ

QE1 Heat transferred to equipment type'1, kW/m2

QE2 Heat transferred to equipment type'2, kW/m2

QE3 Heat transferred to equipment type 3, kW/m2

QE4 Heat transferred to equipment type 4;, kW/m2

QFC Convective heat flux from flame to fuel,.kWI 2

QFRR Radiative heat flux from flame to fuel, W/m

Q12 Heat transfer inside vessel type 2, kW/m 2 Q13 Heat transfer inside vessel type,3', kW/m2

QMR Mass rate of radioactive materials-in each size bin-, g/s

QRAD 'Radiative fraction of QACT, kJ

QRAD1 Mass of radioactive material for release mechanism 1, g

QRAD2 Same as QRAD1, but for mechanism 2,ý g

QRAD3 Same a's QRAD1, but f orý mechan ism 3, g

QRAD4 Same as QRAD1,' but for mechanism 4, g

QRAD5 -Same as 'QRAD1', but for mechanism 51, g

QRAD6 Same as QRADl1, 1-but for mhechani sm 6, g

QRAD7 Same as QRAD1, but for mechanism 7, 'g2 QRR Fuel material surface reradiation, kW/m 2

QWA Convective heat transfer to the wall, kW/M2

RBOIL Boiling rate of liquid in vessel type ~,ml,/Tin

RHOO Density of tonstructionomaterial, kg/in

SMOK Weight of smoke generated per materials each time step, g

0.10
TABLE D.2. (contd)

Name Description

SMSZ Fraction of smoke particles in each bin

SQ Size of individual pyrophoric metal pieces, g

TBCL Time the hot layer starts heat transfer to equipment, s

TBURN Maximum burning time based on amount of fuel and burn rate, s

TC Temperature of ceiling nodes, K2

TDIFC Thermal diffusivity of ceiling,,2m /s

TOIFF Thermal diffusivity of floor, Is

TDIFW Thermal, diffusivity of wall, mT/s

TEl Temperature outside vessel type 1, K

TE2 Temperature outside vessel type 2, K

TE3 Temperature outside vessel type 3, K

TE4 Temperature outside vessel type 4, K

TEND, Time at which fuel is burned up, s

TF Temperature of floor nodes, K

TFP Time alternate flow path develops, s

T12 Initial temperature inside vessel type 2, K

T13 Initial temperature inside vessel type 3, K

TL Initial temperature of liquid in vessel type 4, K

TSTART Time at which fuel starts burning, s

TW Temperature of wall nodes, K

VEMASS Mass of particles that deplete onto the vent,9 VGAS2 Volume of gas above powder for type 2 vessel:, VGAS3 Volume of gas above liquid for type- 3 vessel, m

VOL Volume of liquid in type 4 ve isel, m

VOLP Volume of type 3 container, m 3

VPWD Volume of powder in type 2 vessel, m3

WAMASS Mass of particles depleted ont~o wall, g

WD Vessel width exposed to flame, m

WFC Weight fraction of carbon in fuel

WFCL Weight fraction of ch-lorine in fuel

WFH Weight fraction of hydrogen in fuel

WFO Weight fraction of oxygen in fuel

WH202 Moisture content of powder in type 2 vessel, g H20

WH203 Weight of liquid in type 3 vessel, g

WMASS Weight of vessel when empty, kg

XA Combustion efficiency

XC Convective fraction of XA

XMAX1 Cumulative amount of radioactive powder made airborne from burning

contaminated combustible solids, g

XMAX2 Same as XMAX1, but for air dried nitrate instead of powder, g

XMAX3 Same as XMAX1, but for nitrate solution instead of powder, g

XR Radiative fraction of XA

YCC Fraction Of CO2 escaped from heated-concrete ceiling,

YCF Same as YCC, but for floor

YCW Same as YCC, but, for wall

YEC Fraction of evaporable water escaped from heated concrete ceiling

YEF Same as YEC, but for floor

D.11
TABLE D.2. (contd)

Name Description

YEW Same as YEC, but for wall

YFCH4 Fractional yield of methane

YFC01 Fractional yield of carbon monoxide

YFC02 Fractional yield of carbon dioxide

YFH20 Fractional yield of water vapor

YFHCL Fractional yield of hydrochloric acid

YHC Fraction of chemically bonded water escaped from heated concrete

ceiling

YHF Same as YHC, but for floor

YHW Same as YHC, but for wall,

YSMOK Fractional yield of smoke

ZCL Midpoint of equipment height above floor, m

D. 12
APPENDIX E

OUTPUT FILES FROM PROBLEM ONE

TABLE E.I. PR1NT.DAT File from Problem One

OUTPUT FOR COMPARTMENT EFFECTS

COMPARTMENT OXYGEN NOT LAYER VOLUMETRIC FLOW RATE HOT LAYER MASS BURN HEAT GEN. HEAT LOSS HEAT TO TIME P:RESSURE CONC. THIC191ESS INLET OUTLET TEMPERATURE RATE BY FIRE TO WALLS FIRE GAS (SEC)'-ATM) (VOL FRACT) (U (M**3/S) (M*3/S (F) G/S) KW) KW) KW)

a. Do .9960 0.2100 0.8000 1.5son -1.568" 76.4880 8.0eon 0.6806" 8.880 0.06 28.68 0.9964 0.2100 0.4032 1.3815 -1.6186 216.3065 10.5429 359.7845 -344.5267 15.2378 46.06 0.9953 0.2180 0.7918 1.3966 -1.6034 112.2788 10.5414 359.7131 -334.4488 25.2722 60.00 0.9953 0.2100 2.2342 1.4002 -2.5998 111.9967 10.5402 359.8726 -326.0384 33.8382 88.90 0.9953 0.2100 1.4399 1.4083 -1.5997 112.5072 10.5392 359.6376 -319.4371 40.2005 168.88 6.9964 0.2100 1.7348 1.3921 -1.6679 113.56822 10.5382 359.8662 -313.7724 45.8348 128.88 0.9958 0.2100 2.0868 1.3317 -1.6683 112.2149 2.4388 21.3886 -36.0367 -14.6481 148.68 0.9949 0.218" 2.1883 1.5158 -1.4844 108.0533 2.4313 21.3928 -35.8402 -14.4474 160.88 0.9949 0.2100 2.3844 1.5158 -1.4842 104.7199 2.4314 21.3944 -34.5921 -13.1978 1890.8 0.9949 0.2100 2.5359 1.5150 -1.4858 182.9597 2.4315 21.3953 -33.1885 -11.7932 208.90 0.99s0 0.2100 2.7035 1.5139 -1.4861 99.8523 2.4318 22.3959 -31.8250 -10.4291 22.0.0 0.9950 0.2100 2.8890 1.5120 -1.4888 97.7054 2.4317 21.3984 -38.5638 -9.1674 24.0.8 0.9950 0.2100 3.0347 1.5104 -1.4896 96.0493 2.4317 21.3988 -29.4329 -8.0351 280.88 0.9949 0.2100 3.1986 1.5249 -1.4751 94.4550 1.5307 8.7864 -23.37680 -14.5896 288.88 0.9949 0.2100 3.3578 1.5187 -1.4813 92.8679 1.5307 8.78865 -21.9379 -13.1514 3900.8 1.8889 0.2846 3.5284 -2.6842 -6.6842 106.1581 162.9438 3011.3425 -2803.8683 1207.4742 320.80 1.6012 0.1983 3.8534 -0.3350 -3.3513 160.8075 163.5692 3023.8186 -1887.4059 2138.4127 340.80 1.8084 0.1917 4.88800 -1.9335 -3.5355 244.6716 156.0823 2873.3374 -894.4583 1978.8792 360.88 1.0102 0.1843 4.8080 -1.5290 -2.1880 333.2971 162.2772 2998.0436 -1782.0354 1296.0081 386.68 1.0010 0.1787 4.8680 -0.1180 -0.8657 376.4951 102.0798 2418. 659 -2131.2954 286.7705 408.88 1.8001 8.1693 4.0886 -0.8084 -0.6889 391.8969 102.6818 2432.3267 -2222.4307 209.8960 428.88 0.9996 0.1618 4.86080 0.0409 -0.5935 403.3688 103.0873 2441.9312 -2279.2924 162.7397 m440.88 0.9995 0.1544 4.0689 0.0613 -0.5324 412.2040 103.3489, 2448.1277 -2312.1697 135.9580 460.88 0.9984 0.1470 4.8808 0.1823 -0.4379 417.3847 168.1799 2384.3577 -2318.2805 -13.9229 480.88 0.9948 0.1416 4.8688 0.5976 -0.2393 402.8802 91.1003 1943.5426 -2106.7486 -162.2059 506.68 0.9945 0.2377 4.9006 0.6326 -0.2166 383.6743 83.9528 1690.6804 -1853.5245 -162.9105 520.00 0.9948 0.1344 4.8868 0.6009 -0.2215 388.3522 78.0900 1496.5461 -1642.6213 -246.0752 548.88 0.9951 0.1317 4.8000 0.5837 -0.2272 351.2458 73.2433 1341.2505 -2478.75668 -129.5061 5680.00 0.9954 0.1293 4.90609 0.5293 -0.2305 338.0438 68.8902 1213.8297 -1329.1017 -125.2720 580.88 0."657 0.1272 4.98868 0.4982 -0.2313 326.4149 65.1799 1107.2998 -1210.6246 -103.3147 680.68 6.9959 8.1253 4.8880 0.4703 -0.2302 316.8846 61.9039 1816.8616 -1218.1426 -93.2868 828.88 0.9962 0.1236 4.6800 0.4450 -8.2274 306.8351 58.9819 939.0893 -1023.9113 -84.8220 840.68 0.9964 0.1221 .4.0680 0.4220 -0.2235 298.4929 58.3526 871.4800 -949.1132 -77.8532 660.80 0.9965 0.1207 4.088 0.4011 -0.2187 290.9198 53.9684 812.0829 -883.8624 -71.5375 680.88 0.9987 0.1194 4.8000 0.3818 -0.2133 284.8035 51.7922 759.6112 -825.7933 -68.2821 780.88 0.9969 0.1182 4.0880 0.3641 -0.2075 277.6532 49.7940 712.6201 -774.3571 -61.7370 720.80 0.9970 0.1171 4.8800 0.3477 -0.2015 271.7943 47.9497 670.5220 -728.3805 -57.7785 740.88 0.9971 0.1161 4.8800 0.3326 -8.1955 2"0.3646 46.2397 632.5888 -686.8120 -54.3032 760.80 0.9972 0.1151 4.8000 0.3185 -0.1894 261.3131 44.6478 598.0068 -849.2415 -51.2346 780.80 0.9974 0.1142 4.0000 0.3064 -0.1834 266.5963 43.1803 5886.473 -815.0513 -48.5840 800.80 0.9975 0.2134 4.0000 0.2932 -0.1775 252.1777 -41.78659 537.7449 -583.8048 -46.0599 820.80 0.9976 0.1126 4.0680 0.2818 -0.1718 248.0281 40.4550 511.2757 -555.1332 -43.8575 848.80 0.9977 0.1119 4.0080 0.2711 -0.1662 244.1151 39.2194 486.8686 -528.7318 -41.8830 868.80 0.9977 8.1111 4.80080 0.2611 -0.1669 240.4213 38.0519 484.2953 -504.3385 -40.0432 88.0.0 0.9978 0.1105 4.8000 0.2517 -0.1557 238.9252 36.9484 443.3596 -481.7365 -38.3769 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY. 896.00801 SEC

900.80 0.9969 8.1114 4.80010 1.0510 -0.0177 222.0959 0.0000 0.0008 -392.3703 -392.3703 92.0.0 0.9924 0.1148 4.98000 0.8778 -0.0462 281.6803 0.0000 0.8000 -258.5387 -258.5387 940.80 0.9943 8.1169 4.80900 0.6680 -8.0807 288.1795 0.000 0.8000 -183.4785 -183.4785 960.80 0.9954 8.1186 4.88001 0.5289 -8.0999 178.5825 0.800" 0.0009 -137.2334 -137.2334 988.68 0.9962 8.1199 4.8080 0.4391 -0.1107 171.3725 8.800 0.0000 -1W6.6377 -106.6377 18"00.8 0.9967 0.1211 4.80800 0.3778 -8.1268 165.7341 0.800" 8.680 -85.3472 -85.3472
TABLE E.2. SMKCL.DAT File from Problem One

OUTPUT FOR SMOKE SOURCE TERM

MASS IN COLD LAYER, G AIRBORNE HOT LAYER TOTAL AIRBORNE FRACTION OF LOSSES DUE TO: TIME,S AT TO (+t) SETTLING(-) LOSSES (=) AT T SETTLING OUT VENT PLUME GAS

0.00 `0.OOE+00 0.OOE+00 0.00E.00 0.8OE*00 0.0000 0.0000 0.0000 20.00s 0,63E-01 0.64E-02 0.70E-03 0.68E-01 0.0117 0.3576 0.6308 40.00 0.X1E+00 0.87E-02 0.16E-02 0.11E+00 0.0125 0.3977 0.5898 60.00 0.28E+00 0.72E-02 0.23E-02 0.16E+00 0.0133 0.4390 0.5477 80.00, 0.21E+00 0.76E-02 0.30E-02 0.21E+00 0.0139 0.4713 0.5148 100.00 0.26E+t00 0.77E-02 0.39E-02 0.26E.+00 0.0151 0.4720 0.5129 120.00 0.29E+00 0.79E-02 0.31E-02 0.29E+00 0.0247 0.8295 0.1467 140.00 0.33E+00 0.74E-02 0.36E-02 0.34E+00 0.0280 0.8369 0.1350 180.00 0.37E+00 0.70E-02 0.41E-02 0.37E+00 0.0288 0.8598 0.1215 180.00 0.39E+00 0.68E-02 0.48E-02 0.39E+00 0.0293 0.8808 0.0898 200.00 0.41E+00 0.66E-02 0.56E-02 0.42E+00 0.0300 0.8996 0.0704 220.00 0.41E+00 0.63E-02 0.64E-02 0.41E+00 0.0301 0.9008 0.0693 240.00 0.41E+00 0.61E-02 0.73E-02 0.42E+00 0.0300 0.9007 0.0092 260.00 0.39E+00 0.80E-02 0.80E-02 0.39E+00 0.0318 0.9448 0.0235 280.00 0.36E+00 0.68E-02 0.93E-02 0.38E+00 0.0315 0.9451 0.0235 300.00 0.28E+00 9.91E-02 0.80E-02 0.29E+00 0.0030 0.3471 0.6499 320.00 0.36E-01 0.29E-01 0.34E-02 0.31E-01 0.0035 6.2373 0.7592 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: S90.0000 SEC

TIME EXCEEDS USER SPECIFIED TIME AT: 1000.0000 SEC

m
TABLE E.3. SMKHEXAT File from Problem One

OUTPUT FOR SMOKCE SOURCE TERM

MASS IN HOT LAYER, 6

AIRBORNE GENERATED ENTRAINE TOTAL AIRBORNE FRACTION OF LOSSES DUE TO:

TIME,S AT TO (+) BY FIRE (*) W PLUME (-) LOSSES (z) AT T SETTLING 8. DIFFUS THERMOPH. DIFFUSIO. OUT VENT

6.6 G.662.6 0.062+90 D.66E.6 6.66266 6.620 6.66E60 0.0060866 0.0006 6.66011 *g.g 26.66 6.lSE*02 9.17E.01 0.44E-03 0.90E-02 9.17E+02 0.7060 0.2961 S."605 6.0606 6.66 406.66 :.32E+02 6.17E+61 0.86E-03 9.98E-02 0.33E+02 6.6868 6.3668 S."648 0.0000 6.66 66.66 0.48E+02 0.17E+01 0.12E-02 9.12E-01 9.60E+02 6."878 0.3273 6.0049 6.066 6.66 80.06 0.86E+02 0.17E+01 0.16E-02 0.12E-01 0.87E+02 6.8411 0.3538. 0.0061 0.6006 6.0006 166.66 0&822i.62 0.17E+92 0.20E.62 0.12E-01 0.83E+02 0.6347 6.3603 6.0665 6.0606 0.6666

126.66 0.96E+02 0.27E+00 0.45E-03 0.13E-01 0.96E+02 6.6267 0.3721 0.6612 0.6666 6.0666

146.00 0.98E+02 0.27E+00 0.47E-03 0.12E-01 0.98E+02 0.6287 6.3701 0.0012 0.0666 6.0666

166.66s 6.10E+03 0.27E+00 0.48E-43 0.112E-01 9.10E+03 0.6297 6.3693 6.0011 6.0066 6.06666

1860.66 0.18E+03 0.27E.60 0.43E-03 0.11E-01 0.120+03 6.6316 6.3686 0.0016 0.6666 6.6666i

266.66 0.21E+03 0.27E+00 0.39E-03 9.162-61 0.11E+03 6.6338 0.3853 6.0016 0.6066 90.666

220.66 0.21E+03 0.27E+60 0.44E-03 60.99E-02 0.22E+03 6.8382 0.3829 D.6069 6.0666 6.6666

246.66 0.11E+03 6.27E+66 0.62E-03 0.98E-02 0.11E+03 0.6362 0.3629 0.6609 0.0666 6.6666

280.66 0.11E+03 0.28E+66 0.19E-03 0.94E-02 0.21E+03 6.6345 0.3647 0.0066w 0.6666 6.6666

286.660 0.12E+03 0.28E+00 0.22E-03 0.91E-02 6.122E+03 0.6464 0.3589 6.6667 .0.6666 .6666

866.66 0.17E+03 0652E+02 06.2E;--0 0.16E+01 0.22E+93 6.0666 8.0035 0.0063 6.6666 6.9906

326.66 0.89E+03 06.2E+02 0.25E2-4 6.712+66 0.74E-63 6.0403 0.0418 6.0027 8.666 0.9126

346.66 6.11E+04 06.1E+02 6.662+66 9.17E+02 0.12E+94 6.W662 6.6651 6.6663 6.6666 S.9922

366.66 6.526+04 06.2E+02 6.662+66 6.15+62 6.12E+64 0.0033 6.6681 0.6.68 6.0666 6.9878

386.66 0.17E+64 6.43E+02 0.662+00 0.46E+01 0.17E+04 6.6117 0.0299 0.6639 0.66660 0.9545 466.66 6.172+64 0.43E+01 0.0662+00 0.33E+01 0.17E+04 6.0161 6.6414 6.6658 6.6666 6.9367

426.66 0.17E+84 0.43E61 9.0662+00 0.292+01 9.17E+04 6.6185 6.6486 6.6676 0.6666 6.9265 446.66 6.17E+64 0.43E+26 0.00E+00 0.28E+01 6.172+64 6.6264 6.06530 0.0079 6.6666 6.9187

466.66 0.17E+04 0.69E+02 6.662+66 0.22E+01 0.27E+04 0.6244 6.6631 6.6696 0.6666 0.9636 486.66 9.18E+04 0.122+02 0.96E+00 0.142+01 0.28E+84 6.6419 6.1657 6.6146 6.6666 0.8378 M 566.66 0.19E+04 0.152+02 6.662+66 0.14E+01 0.20E+84 6.6465 6.1136 6.6137 6.6666 0.8262

5A 26.6 Do 21E+64 0.172+02 6.662*60 0.16E+01 6.212+64 6.6464 0.1164 6.6117 6.66 06.315 546.66 6.23E+04 6.182+62 6.662+66 9.16E+01 0.23E+04 6.6462 6.1676 6.6101 6.6666 8.8367

586.66 0.24E+04 0.19E+02 0.662+96 0.182+01 0.24E+04 6.6463 0.1047 0.6689 0.6666 8.8461

586.66 0.26E*04 0.20E+02 6.662+66 0.192+01 0.26E+64 6.6468 6.1063 0.6079 0.6666 6.6418 666.66 0.28E*04 0.20E+02 0.662+00 0.20E+01 9.282+64 0.6475 6.1030 6.6672 0.6666 0.6422

626.66 0.30E+04 0.21E+02 0.662+00 0.212+01 0.302+04 6.6485 8.1632 0.6666 0.6666- 6.8416 846.66 6.322+64 0.21E+02 6.662+60 0.222+01 6.322+04 0.6497 0.1039 S.6662 0.6666 6.8402

886.66 0.332+64 0.21E+02 6.662+66 0.232+01 0.342+64 6.0611 6.1656 6.6658 0.6666 6.6382

686.66 6.352+64 0.212+62 6.662+66 6.242+61 60.352+64 6.06526 6.1664 6.0665 0.6666 9.8355

766.66 0.372+04 0.20E+02 6.662+66 0.242+61 8.372+64 0.6642 6.1081 6.0662 0.6666 0.8325

726.66 6.39E+64 6.20E+02 6.662+66 0.252+01 0.392+84 6.0659 0.1099 6.0665 0.6666 0.8291 74.0.6 0.412+64 0.20E+02 6.662+66 6.252+61 6.412+64 6.06577 0.1126 0.6648 0.6666 6.8255

766.66. 0.422+64 6.202+62 6.662+66 6.282+61 0.42E+64 6.6596 6.1142 6.4664 0.6666 6.8215

7860.66 0.442+04 6.262+62 .6.662+66 9.26E+61 0.44E+04 6.6616 9.11865 0.466 0.6666 0.0174

866.6 0 6 .462+04 0.20E+02 6.662+66 6.26E+01 0.462+04 0.6638 6.1189 0.6643 0.6666 6.8232

826.66 6.472+04 0.192+02 0.962+66 6.272+61 0.482+64 6.0665 6.1214 6.6642 6.0666 8.80688

846.66 0.492+04 0.19E+62 8.662+00 6.27E+61 0.49E+64 6.6678 6.1239 6.6641 6.6666 6.6643

866.66 0.512+64 6.19E+62 6.662+66 0.272+61 06.12+04 6.6699 6.1285 0.0048 6 .6666 6.7997 8666.0 0652E+04 6.19E+62 6.O6E+00 6.272+61 06.22+64 6.6726, 0.1290 0.0039' 0.0666 0.7958 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 896.666 SEC

966.66 06.3E+04 0.662+86 6.662+66 6.862+66 06.32+04 0.2519 0.4260 6.0168 6.6666 0.3113

926.66 0.532+64 6.662+66 6.80E+00 0.12E+01 06.3E+04 0.1743 6.27065 0.6647 0.6666 .6.5565 946.66 06.32+84 6.662+66 9.662+00 6.162+61 0.63E+04 6.1263 6.1835 6.0023 6.6666 0.6879 966.66 06.3E+04 6.662+66 6.662+66 0.19E+01 06.3E+04 6.1103 6.1519 6.6061 6.6666 6.7383 986.66 06.3E+04 6.662+66 6.662+66 6.26E+01 06.32+64 6.1634 6.1362 6.0011 0.66 6.7593 1666.66 06.2E+04 6.98E+66 90.66+66 0.212+61 06.2E+04 6.1663 0.1272 9.g 6 .6666 6.7717

TIME EXCEEDS USER SPECIFIED TIME AT: 1666.6666 SEC
TABLE E.4. RSTCL.DAT File from Problem One

OUTPUT FOR RADIOACTIVE SOURCE TERM

MASS IN COLD LAYER, G AIRBORNE HOT LAYER- TOTAL AIRBORNE

TIME,S AT TO (*) SETTLING(-) LOSSES (=) AT T 0.006 8.06E*00 0.00E+00 O.66E+00 6.66E+00 20.66 'S.23E-03 . .29E-04 0.37E-06 0.26E-03 46.06 0.46E-03 0.31E-04 0.75E-;05 0.60E-03 66660 0.70E-03 0.31E-84 0.11E-04 0.72E-03 80.66 6.88E-03 0.32E-04 6.16E-64 0.90E-03 1"6.66 0.20E-02 0.32E-04 0.19E-04 6.10Ea-02

126.66 0.12E-02 0.31E-64 0.18E-04 0.12E-02 146.66 0.23E-02 0.29E-44 0.17E-04 0.13E-02 16916 0.24E-02 0.27E-04 0.20E-04 0.24E-02 186.66 0.24E-02 0.26E-04 0.22E-64 0.24E-02 266.00 0.24E-02 0.24E-"4 0.25E-04 0.24E-02 220.66 0.24E-02 0.23E-04 0.28E-04 0.24E-02 240.66 0.24E-02 0.22E-04 0.31E-04 0.23E-02 266.66 0.12E-02 0.21E-04 0.32E-04 0.22E-02 280.66 0.21E-02 0.20E-04 0.38E-64 0.X1E-02, 3"6.00 0.21E-02 0.71E-03 0.45E-03 0.13E-02 320.00 0.24E-02 0.12E-02 0.14E-02 0.12E-02 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 890.0M6 SEC

TIME EXCEEDS USER SPECIFIED TIME AT: 1000.0000 SEC

FRACTION OF LOSSES DUE TO:,

SETTLING OUT VENT - PLUME GAS 0.6666 6.0000 0.0606 6.1328 6.3138 06.534 0.1453' 0.3442 .6.1065 0.1645 0.3762 0.4093 6.1578 0.4062 0.4397

6.1521 0.4064 0.4416 0.2262 0.6582 0.1156 0.2424 0.8623 0.20653, 0.2418 6.6711 6.0870 0.2412 0.6886 6.0702 6.2402 0.7046 6.06552 0.2353 0.7201 0.6548 0.2366 0.71560 6.06560 6.2349 0.7486 0;0186, 0.2277 0.7536 0.0187 0.0374 0.3351 0.6276 0.0884 0.2171 0.6946

rri
TABLE E.5. RSTHL.DAT File from Problem One

OUTPUT FOR RADIOACTIVE SOURCE TERM

MASS IN NOT LAYER, Q

AIRBORNE GENERATED ENTRAINED TOTAL AIRBORNE FRACTION OF LOSSES DUE TO:

TIME,S AT T@ (.) BY FIRE (-) W PLUME (-) LOSSES (=) AT T SETTLING B. DIFFUS THERMOPH. DIFFUSIO. OUT VENT 0.0 --. 60E*06 O.OeE00 D.OE 00 0.E+00 8.90E+00 9.0000 0.0000 0.0000 0."090 0.0000 2.06 0.2-1 04E0 .2f-Os 0.42E-04 0.47E-92 0.6889 0.3111 0.0030 0.0000 0.0000 40.00 0.89E-01 0.47E-02 6.38E-06 0.46E-04 0.04E-02 0.6704 0.3287 0.0029 0.0000 0.0000 60.00 0.13E*00 0.43E-02 0.53E-06 0.48E-64 0.14E+00 0.8488 0.3484 0.0030 0.0000 0.0000 80.00 8.18E+00 0.43E-02 0.86E-05 0.61E-04 0.18E+00 0.8244 0.3724 0.0032 0.0000 0.0000 100.00 0.22E+00 0.43E-02 0.86E-06 9.62E-04 0.22E+00 0.6166 0.3802 0.0032 0.0000 0.0000 120.00 0.26E+90 0.13E-04 0.28E-06 0.61E-04 0.26E+00 0.8062 0.3930 0.0000 0.0000 0.0000 240.00 0.26E.00 0.23E-04 0.18E-06 0.47E-64 0.26E+00 0.6093 0.3900 0.0007 0.0000 0.0000 160.08 0.26E+00 0.13E.-04 0.17E-06 0.44E-04 0.26E+00 0.8128 0.3887 0.0007 0.0000 0.0000 180.00 0.25E*80 0.13E-64 0.18E-05 9.41E-04 0.26E+00 0.6169 0.3835 0.0008 0.0000 0.0000 200.00 0.25E+00 0.13E-04 0.14E-06 8.38E-64 8.26E+00 0.6190 0.3804 0.0008 0.0000 0.0000 220.00 0.26E+00 0.13E-04 0.16E-06 0.38E-84 9.26E+00 0.8229 0.3774 0.0006 0.0000 0.0000 240.00 0.26E+00 0.13E-04 0.17E-05 0.34E-04 6.26E.00 0.6247 0.3748 0.0005 0.0000 0.000 280.00 0.26E.00 0.13E-04 0.60E-06 6.33E-04 0.26E..00 0.8282 0.3714 0.0005 0.0000 0.0000 280.00 0.26E+60 0.13E-04 0.67E-06 0.31E-84 0.26E+00 0.6326 0.3870 0.0004 0.0000 0.0000 300.00 0.18E+.01 0.1SE-01 0.28E-03 0.14E-01 0.16E+01 0.0518 0.0024 0.0003 0.0000 0.9455 320.00 0.18E*01 9.18E-01 0.96E-03 0.29E-02 0.19E+01 0.4185 0.0176 0.0017 0.0000 0.5844 340.00 0.16E+01 0.17E-01 0.OOE*00 0.27E-01 9.18E+01 0.0627 0.00131 0.0002 0.0000 0.9439 300.00 0.17E+01 0.28E-01 0.OOEEs'0 9.19E-01 0.17E+91 0.0050 0.0045 0.0007 0.0000 0.9098 380.00 0.17E+01 0.16E-06 9.66E+t00 9.82E-02 8.17E+01 0.2659 0.0131 0.0030 0.0000 0.7180 400.00 0.28E+01 0.27E-06 9.OOE*00 9.47E-62 9.18E+02 0.3292 0.0169 0.0040 0.000 0.8498 420.00 0.28E+01 0.18E-06 900E..00 0.41E-02 0.16E+01 0.3588 0.0190 0.0047 0.0000 0.6195 -440.00 0. 16E+01 0.19E-06 0.OOE+00 0.37E-02 0.26E+91 0.3744 0.02" 0.0052 0."080 0.5998 4"0.00 0.16E+01 0.19E-05 909E+00 0.32E-02 6.l5E*01 0.4129 0.0234 0.0059 0.0000 0.5578 400.00 0.1SrE+01 0.18E:-5 0.80E*00 0:23E-02 0.26E+02 0.5507 0.0312 0.0072 0.0000 0.4109 Mr 50000*9 016E+.I ' 1E-0 0.06E+00 022E-02 0.16E+01 0.6720 0.0324 0.0065 9.0000 0.3891 5n 20.00 0.16E+01 0.14E-06 0.90E.00 8.22E-92 0.15E*01 0.5684 0.0321 0.0058 0.0000 0.3909 540.00 9.14E+01 0.13E-06 0.60E+00 0.21E-02 0.14E*01 0.5574 0.0318 0.0049 0.0000 0.4059 560".00 0.14E+01 0.12E-05 6.OOE+W0 0.21E-02 6.14E+01 0.6613 6.0317 0.0044 0.0000 0.4126 500.00 0.14E*01 0.11E.-06 0. am*"0 0.20E-02 8.14E+02 0.5472 0.0318 0.0039 0.0000 0.4170 600.00 0.14E+01 0.10E-06 9.60E+00 0.20E-02 9.24E+01 0.5447 0.0320 0.0036 9.0000 0.4197 820.00 0.24E.01 9.97E-06 0.OO0E*00 0.19E-02 8.14E+01 0.5435 0.0324 0.0033 0.0000 0.4208 040.00 0.23E+01 0.91E-06, 0.60E+00 0.19E-02 9.13E+01 0.6432 0.0328 0.0031 0.0000 0.4209 660.00 0.23E#01 0.08E-68 09.OE.0 9.18E-02 0.23E+01 0.5437 0.0333 0.0029 0.0080 0.4201 8600.00 0.13E+.01 0.91E-06 0.80E*00 6.18E-02 0.13E+02 0.5447 0.0339 0.0028 0.0000 0.4186 700.00 0.19E+01 0.77E-66 0.80E.00 0.17E-02 0.23E+02 0.5461 0.0348 0.0028 0.0000 0.4267 720.00 0.13E+01 0.74E-06 0.60E*00 0.16E-02 0.13E+01 0.5478 0.0353 0.0025 0.0000 0.4144 740.00 0.13E+01 0.70E-06 0.6OE.0 0.16E-02 0.23E#02 0.5490 0.0361 0.0024 . 0.0000 0.4129 780.00 0.12E*01 0.87E-06 0.90E400O 0.16E-02 0.12E+01 0.5516 0.0389 0. 0023 0.0000 0.4092 700.00 0.12E+01 0.86E-06 0.OOE.00 0.15E-02 0.12E*61 0.5536 0.0378 0.0022 0.000 0.4084 800.00 0.12E+.01 0.62E-08 0.80E*W0 0.14E-02 0.12E+01 0.5555 0.0387 0.0022 0.0000 0.4037 820.00 0.12E+01 0.60E-06 0.60E*00 0.14E-02 6.12E+01 0.6576 0.0398 0.0021 0.0000 0.4009 849.00 0.22E+01 0.68E-06 0.80E*00 0.13E-02 0.12E*01 0.5593 0.0405 0.0020 0.0000 0.3981 860.00 0.12E+01 0.66E-08 0.80E+00 0.13E-02 0.12E*01 0.5611 0.0415 0.0020 0.0000 0.3954 880.00 0.22E+01 0.64E-06 0.90E*.0 9.12E-02 0.12E.01 0.5828 0.0426 0.0019 0.0000 0.3928 ALL. COMBUSTIBLE MATERIALS WERE CONSUMED BY: 890.0000 SEC

900.00 0.11E+01 0.46E-06 0.OO1E*00 0.77E-03 9.11E+01 0.8647 0.0035 0.0024 0.0000 0.:694 292.00 6.11E*01 0.37E-06 0.80Ee00 0.84E-03 0.12E+02 0.7802 0.0542 0.004 .0000 01843 940.00 0.11E+01 0.31E-06 0.010Eýt00 0.93E-03 8.11E+01 0.8937 0.0486 0.0009 0.01000a 0.2589 960.00 6.11E+01 0.28E-00 0.60E+00 0.97E-03 8.11E#01 0.6509 0.0427 0.0006 0.0000 0.3059 980.00 9.11E+01 0.26E-06 9.80E+10 0.98E-03 0.1XEt9l 0.6264 0.0405 0.0005 0.0000 0.3327 1000.00 9.11E*01 0.23E-00 0.98E+00 0.97E-03 0.11E+01 0.6109 0.0392 0.0004 0.0000 0.3495

TIME EXCEEDS USER SPECIFIED TIME AT: 1000.0000 SEC
TABLE E.6. SSZCL.DAT File from Problem One

OUTPUT FOR SMOKE SOURCE TERM

MASS IN COLD LAYER., 0

PARTICLE DIAMETER (MIC TIME 0.100 0.173 0.387 '0.592 0.794 0.995 1'.430

8.00 0.0002.00 0.OOOE.00 0.80E+200 0.0002.00 0.000OE+80 20.00 0.9000E00 0.274E-04 0.360E-03 0.992E-03 0.178E-02

40.00 0.000E.00 0.525E-04 0.674E-03 0.192E-02 0.344E-02

60.00 0.0002.00 0.780E-04 0.981E-03 0.279E-02 0.501E-02

80.00 0.0002.00 0.983E-04 0.227E-02 0.381E-02 0.847E-02

100.00 0.000200 0.220E-03 0.651-02 0.433E-02 0.778E-02

120.00 0.0002.00 0.139E-03 0.274E-02 0.501E-02 0.8982-02

140.00 0.0002.00 0.180E-03 0.2012-02 0.6782-02 0.104E-01

180.00 0.000E.:00 0.178E-03 0.222E-02 0.6362-02 0.1142-01

180.00 0.0002.00 0.1882-03 0.2382-02 0.878E-02 0.1222-01

200.00 0.OOOE+t00 0.1962-03 0.2462-02 0.704E-02 0.127E-01

220.00 O.OOOE.00 0.1982-03 0.260E-02 0.711E-02 0.129E-01

240.00 0.0002.00 0.184E-03 0.2472-02 0.703E-02 0.127E-01

280.00 V.OOOE.00 0.180E-03 0.231E-02 0.677E-02 0.122E-01

280.00 0.000E*00 0.187E-03 0.2162-02 0.8292-02 0.114E-01

300.00 0.0002,00 0.868E-04 0.2142-02 0.332E-02 0.5982-02

320.00 0.000200 0.147E-04 0.1862-03 0.628E-03 0.9492-03

ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 890.0000 SEC

TIME EXCEEDS USER SPECIFIED TIME AT: 1000.0000 SEC

0.0002.00 0.0002+00

0.219E-02 0.123E-01

0.4252-02 0.2392-01

0.619E-02 0.3472-01

0.7992-02 0.4492-01

0.9582-02 0.538E-01

0.1122-01 0.6232-01

0.1282-01 0.712S-01

0.1412E-01 0.7912-01

0.1502-01 0.8442-01

0.1582-01 0.877E-01

0.1582-01 0.8082-01

0.1582-01 0.8742-02

0.1602-01 0.838E-01

0.1392-01 0.779E-01

0.7332-02 0.4102-01

0.117E-02 0.8582-02

ROHS)

3.460 7.750 14.140

0.0002.00 0.0002.00 0.0002.00

0.4062-01 0.0002.00 0.0002.00

0.7832-01 0.0002.00 0.002.00

0.114E+00 0.0002.00 0.0002.00

0.147E.00 0.0002.00 0.0002.00

0.1762.06 0.0002,00 0.60002.00

0.2032.00 0.0002.80 0.0002600

0.2342,00 0.0002.00 0.0002.00

0.2672.00 0.60002.00 0.0002.00

0.2732.00 0.0002.00 0.0002.00

0.2832,00 0.90002.00 0.0002,00

0.288E.00 0.0002.00 0.000E.00

0.2802.00 0.0002.00 0.0002*00

0.2688200 0.0002.00 0.0002*00

0.247E+00 0.90E0020 8.e0002*00

0.1302.00 0.0002.00 0.0002.00

0.217E-01 0.0002.00 0.0002.00

20.000 TOTAL

0.0002.00 0.000E+00

0.0002.00 0.5822-01

0.0002.00 0. 1132,00

0.0002.00 0.1842.00

0.0002*00 0.2112.00

0.0002,00 0.253E+00

0.0002.00 0,.292E*00

0.0002.00 0.3372,00

0.0002.00 0.3712.00

0.0002.00 0.3942,00

0.000E.00 0.4092.00

0.0002,00 0.413E*00

0.0002.00 0.4082*00

0.0002.00 0.3882*00

0.000E.00 0.3592.00

0.0002.00 0.1882,00

0.000E.00 0.311E-01

M

C.)
TABLE E.7. SSZHL.DAT File from Problem One

OUTPUT FOR SMOKE SOURCE TERM

MASS IN 140T LAYER, 0

PARTICLE DIAMETER (MICRONS) TIME 0.100 8.173 0.387 0.692 0.794 0.995 1.480 3.460 7.760 14.140 20.000 TOTAL

0.00 0. 000E.00 0. 000E.00 0. 000 .00 0. +0E00 0.G +0E00 0.090OE+00 G0. +0E00 0. 000E+00 0. 000E+00 0. OOOE*00 0.000OE+00 0. 000 .00 20.00 0. 000 +00 0.749E+00 0.192E*t0l 0.233E+01 0.233E+01 0.183E+02 0.466E+01l 0.280E.01 6000OE+00 0.000E+00 0.080E+00 0.188Ei.02 40.00 0.000E+00 6.160E-01 0.384E+i01 I.467E+01 0.467E+01 0.387E402 0.933E+02 0.580E+01 0.O60E.00 0.080E+00 0.800E+00 0.333E+02 60.00 0.000E.00 0.225E+92 0.676E+01 0.701E*01 0.701E+01 0.561E*01 0.240E.+02 0.840E+01 6.060E+00 0.000E-00 0.000E*00 0.499E+02 80.00 O.000E+00 0.300E.02 0.767E.+01 0.934E+02 0.934E+01 0.734E+02 0.187E+02 0.112E+02 0.000E+00 0.OOOE+tOO 0.00E.00 0.888Ei.02 100.00 0.000E+00 0.374E+02 0.959E*t0l 0.227E+02 0.117E+t02 0.91?E*01 0.233E+02 0.240E+02 0.OOOE+00 0.000E*t00 0.000 +00 0.832Ei.02 120.00 0.900E+00 0.430E+02 0.120E*02 0.234E+02 0.134Ei.02 0.105E*02 0.288E.+02 0.262E+02 G.000E+00 0.OOOE*00 0.000E+t00 0.968E+02 140.00 0.OOOEi.00 0.441E+01 0.213E*02 0.138E+02 0.138E+02 0.108E+02 0.276E+02 0.266E+02 0.000E+00 0.000E.+00 0.000E+00 0.981E+02 180.00 0.000E.00 0.469E+01 0.216E*t02 0.141E*02 0.241E+02 0.111E*02 0.282E+02 0.289E+02 0.OOOE+00 0.000E+00 0.000E+00 0.101Ei.03 180.00 0.OOOE+00 0.484E+01 0.119E*02 0.146E+92 0.246E+02 0.114E*02 0.290E+02 0.273E+02 0.800E+00 0.9OOE+00 0.000E+00 0.103Ei.03 200.00 0.OOOE+00 0.476E+01 0.122E*t02 0.249E+02 0.249E+02 0.117E+02 0.297E*t02 0.277E+02 0.000 +00 0.0OOE+00 0.OOOE+00 0.108E+03 220.00 6.000E*00 0.487E+02 0.128E+t02 0.252Ei.02 0.162Ei.02 0.120E*02 0.304E.+02 0.281E+02 S.000E+00 9.000E*00 0.000E.00 0.108E+03 240.00 0.900E+.00 9.498E+01 0.228E+902 0.266E+02 0.156E+02 0.123E*02 0.311E*02 0.285E+02 0.000E*00 0.OOOE'00 9.000E+00 0.111E4.03 260.00 0.000E+00 0.610E+01 0.232E+t02 0.280E+02 0.180E+02 0.126E*02 0.319E+~02 0.289E+02 0.000E+00 0.000E+00 O.OOOE*00 0.113E*03 280.00 0.090E+00 0.622E+02 0.134E*02 0.163E+02 0.183E+02 0.128E+02 8.328E+02 0.193E+02 0.000E.00 0.8W0it00 0.000E*00 0.116E+03 300.00 0.000E+00 0.979E+01 0.261E+t02 0.306E+02 0.306E+02 0.240E*02 0.611E+02 0.387E+92 0.000E.*00 6.000E+00 0.000 *00 0.218E.03 320.00 0.00+200 0.331E+02 0.848E.02 0.103E+03 0.103E+03 0.811E+02 0.206E.03 0.226E+03 0.0002.00 0.006E.00 0.000E+00 0.7372.03 340.00 0.000.0 0.629E+02 0.133E+03 0.162E.03 0.182Ei.03 0.227E+03 0.323E+03 0.295E+03 0.0002.00 0.000E+00 0.0002.00 0.115E.04 300.00 0.0002+00 0.878E+02 0.1742.03 0.212E,03.0.212E4.03 0.166E.03 0.423E+03 0.266E+03 0.0W02+00 0.08002.0 0.0002.00 0.151E.04 380.00 6.0002.00 0.767E+02 0.294E*03 0.238E.03 0.238E+03 0.1862.03 0.473E.03 0.288E.03 0.0002.0" 0.0002.00 0.0002.00 0.169E.04 400.00 0.0002.00 0.7592.02 0.294E+03 0.2372.03 0.237Ei+03 0.188E.03 8.474E+03 0.287E+03 0.0002+00 0.099E.00 0.0002+00 0.189E.04 420.00 0.0002+00 0.763E+02 0.1962.03 0.239E+03 0.239E+03 0.1882.03 0.4782.03 0.269E.03 0.80002.00 0.0002.00 0.000E*00 0.170E+04 440.00 0.000200 9.770E.02 0.12982.03 0.2412E.03 0.241E.03 0.1902.03 9.483E.03 0.2922.03 0.000E+00 0.0002.00 0.0002.00 0.172E.04 460.00 0.0002.00 0.790E.02 0.200E+03 0.244E.03 0.2462.03 0.1922,03 0.489E+03 0.296E*03 0.0W02+00 0.08002.00 0.000E+00 0.174Ei.04 480.00 0.0002.00 0.8172.02 0.210E+03 0.266E+03 0.267E+03 0.202E403 0.613E+03 0.310E+03 0.0002+00 0.0002.t00 0.000E+00 0.183E.04

rr 500.00 0.0002.00 0.873E+02 0.2252.03 0.274E.03 0.274E+"0 0.216E.03 0.649E+03 0.331E.03 0.000.90 0.0002.OE00 0.000E.+00 0.196E+04 520.00 0000.0 0.939E.02 0.2422.03 0.295E+03 0.296Ei.03 0.232E403 8.5912.03 0.367E+03 0.000E+00 0.0002.t0 0.8000+00 0.211E.04 4 540.00 0.0002+00 0.101E+63 0.262E*03 0.318E.03 0.318E.03 0.2502.03 0.637E+03 0.384E.03 0.0002.00 0.0002.00 0.0900E+00 0.2272.04 5680.00 0.000 +00 0.109E+03 0.280E.03 0.342E+03 0.343E.03 0.289E+03 9.686E.03 0.413E.03 0.0002.00 0.0002.00 0.0002.00 0.2442.04 560.00 9.006E+00 0.127E.03 0.302E*03 0.3672.03 0.388E+03 0.2899E+03 0.738E+03 0.443E.03 0.0002.00 0.000E.00 0.0900.00 0.262E.04 600.00 0.0002.00 0.126E.03 9.322E.03 0.393E+03 0.393E.03 0.309E.03 0.787E+03 0.474E+03 9.000E+00 0.0002.00 0.A0002+00 0.280E+04 620.00 0.0002.00 9.133E+03 0.343E+03 0.482.E03 0.419E.03 0.329E.03 0.839E+03 0.506E+03 0.0002.00 0.0002.00 0.000E.00 0.299E+64 640.00 0.0002.00 0.141E.03 0.364E.03 0.444E+03 0.445E.03 0.3502.03 0.8902.03 0.638E.03 0.0002.00 0.000E+00 O.OOOE+00 0.317E.04 600.00 9.000E.00 0.149E+03 0.386E.03 0.470E+03 0.471E.03 0.370E+03 0.942E.03 0.687E+03 0.000E.00 0.000E.00 6000OE+00 0.336E.04 680.00 0.OOOE.00 6O.1572.03 0.406E+03 0.496E.03 0.496E+03 0.3902.03 0.993E+03 0.697E.03 0.8 .OOOEi. 0 0.020 00 .0002.00 0.364E.04 700.00 0.000E.00 8.1652i.03 0.427E+.03 0.521E+03 0.622E+03 0.410E+03 0.104E+84 0.828E.03 0.000E.00 0.000E+00 0.0002.00 0.372E.04 720.00 6.060E200 0.173E+.03 0.447E+03 0.648E.03 0.547E.03 0.430E+03 0.109E+04 0.658E+03 0.0002.00 0.000E.00 0.000E+00 0.390E.04 740.00 0.00024+00 0.181E+03 0.467E.03 0.571E.03 0.572E.03 0.460E+03 0.124E+04 0.687E+03 0.0002+00 0.0002.00 0.0002.00 0.407E.04 760.00 0.0002.00 0.189E.03 0.487E+03 0.696E+03 0.696E.03 0.4692.03 0.229E.04 0.717E+03 0.0002.00 0.0002.00 0.0002..00 0.426E+04 790.00 9.000E+00 0.196E+03 0.607E+03 0.620E+03 0.621E.03 0.488E*03 0.124E+04 0.745E+03 0.0002+00 0.0002.00 0.OO+E00 0.442E.04 800.00 0.00024+00 0.204E.03 0.5272.03 0.644E+03 0.646E+03 0.507E+03 0.129E+04 0.774E.03 0.0002.00 0.0002.00 0.8000E+00 0.459E+04 820.00 0.0002+00 0.211E+03 0.5462.03 0.6672.03 0.668E.03 0.5252+03 0.234E+04 0.802E.03 0.0002+00 0.0002.00 0.0002+00 0.478E+04 840.00 0.000&E.00 0.218E+03 0.566E403 0.690E+03 0.691E.03 0.644E+03 0.138E+04 0.829E+03 0.0002.00 0.0002.00 0.0002.00 6.492E+04 860.00 0.0002+00 0.228E+03 0.5832.03 0.713E*03 0.7142.03 0.5682E+03 0.1432.04 0.856.+03 0.0002.00 0.0002.00 0.0002.00 0.608Ei-04 880.00 0.0002+00 0.232E+03 0.6022.03 0.736E+03 0.737E+03 0.5792.03 0.148E+04 0.8832.03 0.0002+00 0.0400E00 0.002A.00 0.524E+84 ALL COMBUSTIBLE MATERIALS WERE CONSLUM BY: 890.000 SEC

900.00 0.0002.00 0.236E.03 0.6102.03 0.7462.03 0.747E+03 0.5872.03 0.1502+04 0.894E+03 0.0002.00 0.0800.00 0.000 .00 0.631E.04 920.00 0.0002.00 0.236E+03 0.8092.03 0.744E.03 0.746E.03 0.587E*03 0.1492.94 0.8922.03 0.0002.00 0.00OE+00 0.0002+00 0.631E+04 940.00 0.0002.00 0.234E+03 0.607E*03 0.742E+03 0.744E.03 0.5852.03 0.1492+04 0.8892+03 0.0002+00 0.0002.00 0.0002+00 0.629E+04 960.00 0.0002.00 0.2332.03 0.6052.03 0.740E+03 0.742E.03 0.683E.03 0.1482.94 0.8852.03 0.0002.00 0.0002.00 0.0002+00 0.5272+04 980.00 0.0002.00 6.2322.03 0.603E.03 0.7372.03 0.739E.03 0.5812.03 0.1482.04 0.8812.03 0.0002.00 0.0002.00 0.0002.00 0.626E+04 1000.00 0.0002.00 0.231E.03 0.6002.03 0.7352.03 9.7372.03 0.5792.03 0.147E.04 0.876E.03 0.0002.00 0.0002.00 0.0002.00 0.523E.04

TIME EXCEEDS USER SPECIFIED TIME AT: 2009.098W SEC
TABLE E.8. RSZCL.DAT File from Problem One

OUTPUT FOR RADIOACTIVE SOURCE TERM

MASS IN COLD LAYER, 0 PRIL IMTR(I

TIME 0.100 0.173 0.387 0.592 0.794 0.995 1.480 0*00. 0E00 0. 000E+6 .OE00 0. 0E00E 0..00 0. 000E.00 00 0. 00.0 SE-tO0. O.OOE+bo 20.00 0.869E-07 0.328E-00 0.117E-06 0.362E-06 0.367E-06 0.306E-05 0.907E-06 40.00 0.13SE-08 0.630E-06 0.226E-06 0.700E-06 0.691E-06 0.694E-06 0.176E-64 60.00 0.200E-06 0.922E-06 0.32GE-05 0.102E-04 0.101E-04 0.863E-06 0.26GE-04 80.00 0.24GE-08 0.12BE-06 0.423E-06 0.132E-04 0.130E-04 0.112E-04 0.330E-04 100.00 0.269E-06 0.243E-06 0.60SE-06 0.158E-04 0.168E-04 0.134E-04 0.395E-04 120.00 0.284E-06 0.16GE-06 0.500E-06 0.182E-64 0.180E-04 0.164E-04 0.466E-04 140.00 0.309E-00 0.189E-06 0.664E-06 0.20SE-04 0.208E-04 0.17SE-04 0.621E-04 1 '80.00 0.;23E-08 0.2"6E-06 0.72SE-05 0.227E-04 0.225E-04 0.292E-04 0.669E-04 180.00 0.337E-08 0.227E-06 0.761E-06 0.240E-04 0.237E-04 0.203E-04 0.699E-64 200.00 0.33BE-06 0.224E-06 0.783E-05 0.24SE-04 0.243E-04 0.208E-64 0.81SE-04 22G.00 0.334E-00 0.221E-06 0.78SE-05 0.24SE-64 0.243E-04 0.20SE-04 0.624E-04 240.00 0.344E-08 0.207E-06 0.786E-06 0.238E-04 0.237E-04 0.202E-04 0.596E-04 280.00 6.357E-06 0.198E-06 0.709E-05 0.228E-04 0.224E-04 0.192E-04 0.563E-04 280.00 0.370E-06 0.181E-05 0.841E-06 0.206E-04 0.20SE-04 0.174E-04 0.614E-04 300.00 0.967E-07 0.89SE-06 0.347E-06 0.10SE-04 0.112E-04 0.102E-04 0.380E-04 3206.00 0.368E-08 0.264E-07 0.227E-06 0.80SE-08 0.994E-06 0.232E-05 0.109E-04 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 890.0000 SEC

RONS) 3.460 7.750 14.140 20.000 60.00OE+00 0.8000E+t00 0. OBOE*tO0 00 OE-t00 0.721E-04 0.866E-04 0.333E-04 0.469E-84 0.141E-03 0. 185E-03 0.638E-04 0.B9SE-04

0.20SE-03 0.23SE-.03 0.90SE-04 0.124E-03 0.262E-03 0.30SE-03 0.113E-03 0.142E-03

0.311E-03 0.363E-03 0.232E-03 8.166E-03 0.356E-03 0.416E-03 0.146E-03 0. 163E-03 0.404E-03 0.469E-03 0.269E-03 0.168E-03 0.43SE-03 0.604E-03 0.165E-03 0.260E-03 0.469E-03 0.623E-03 0.2eGE-03 0.158E-03 0.4OBE-03 0.626E-03 0.182E-03 0.252E-03 0.486E-03 0.614E-03 0.162E-03 0.242E-03 0.449E-03 0.487E-03 0.13BE-03 0.129E-03 0.422E-03 0.447E-03 0.121E-03 0.113E-03 0.382E-03 0.39GE-03 0.'101E-03 0.963E-'04 0.320E-03 0.363E-03 0.437E-03 0.132E-03 0.115E-03 9.261E-03 0.384E-03 0.609E-03

TOTAL

0.OOOE-t00

0. 25SE-03

0. 499E-03

0. 717E-03

0.89B9E-03

0. IOSE-02 0. 11ITE-02

0. 131E-02

0. 140E-02 0. 144E-02

0. 145E-02

0. 141E-02

0. 134E-02

0. 123E-02 0. 109E-02

0. 133E-02

0. 121BE-02

TIME EXCEEDS USER SPECIFIED TIME AT: 1000.000 SEC

rri
TABLE E.9. RSZHL.DAT File from Problem One

OUTPUJT FOR RADIOACTIVE SOURCE TERM

MASS IN NOT LAYER, 0

PARTICLE DIAMETER (MICRONS) TIME 6.260 0.173 0.307 0.592 0.794 0.995 1.460 3.460 7.7560 24.146 20.6OW 0.600.606.060+0 6.6602.6 6.6662.00 0.62.6.00 6600 2.66W 0 0.6062966 0.6662.60 6. 666E*06 0.0062+66 0.666E.06 6.O66E600 26.66 06.73E-02 0.8992E-02 0.641E-02 0.852E-02 6.489E-02 6.268E-02 0.343E-02 0.568E-02 6.1162-62 0.141E-63 0.104E-63 40.6 M6.228E-01 6.160E-01 6.1282-01 0.2712E-01 6.9362-62 06.12E-02 0.807E-02 0.102E-61 0.237E-02 0.284E-03 0.211E-63 86.66 0.153E-02 9.289E-01 0.192E-01 0.266E-01 6.1412E-61 6.7682-62 0.1032-01 0.249E-02 0.364E-02 6.4162-63 0.283E-03 86.66 0.174E-02 6.3682-61 6.2562-61 0.341E-61 0.2872-01, 0.102E-61 0.137E-01 6.1952-61 0.476E-02 06.282-63 6.292E-03 166.66 0.194E-62 0.4472-61 0.319E-01 6.4252-61 0.234E-61 0.1282-01 0.1712-01 0.240E-01 06.5862-02 6.847E-03 0.327E-03 126.66 0.207E-2- 6.5662E-61 0.367E-01 0.476E-01 0.262E-01 0.143E-61 0.1912-01 0.287E-01 0.8653E-02 6.7142-03 0.362E-03 146.66 6.2662-61 0.499E-61 0.367E-01 0.476E-01 0.262E-01 0.143E-01 6.191E-01 0.267E-61 0.644E-02 0.701E-03 0.396E-03 166.66 0.2682-61 0.4992-01 2.357E-01 0.4762-01 6.2822-01 0.143E-61 0.191E-01 6.2862-61 6.6382-62 6.6912-03 6.4182-63 166.66 0.2082-61 6.4982-61 0.367E-01 6.4752-61 0.2822-01 0.143E-61 6.1912-61 6.2852-61 0.6362-02 0.884E-03 6.4462-63 2606 6 .2652-61 6.4982-61 0.356E-01 6.4752-61 0.2822-61 0.1432-01 0.191E-01 6.2852-61 0.823E-02 0.6792-63 0.473E-03 226.66 6.2652-01 0.497E-01 6.3562-61 6.4752-61 0.2612E-61 6.143E-01 0.191E-61 0.284E-61 06.87E-62 6.6752-63 6.5601E-03 246.00 6.2652-61 0.4972-61 6.3582-61 0.4752-61 0.2612E-01 0.1432-61 6.191E-01 0.284E-61 0.8122E-62 0.674E-03 06.282-63 286.66 6.2052-61 6.4982-61 6.368E-01 0.4742-61 0.262E-02 6.1432-01 6.191E-01 0.284E-01 0.807E-02 0.8732-63 06.652-63 286.66 0.204E-61 6.4962-61 6.8562-61 0.474E-01 6.281E-61 6.142E-01 6.1962-61 0.2632-01 6.6622-02 0.673E-63 06.82E-63 300.66 6.2622-01 6.4912-61 6.9152-61 0.10652.00 6.9352-61 0.814E-01 0.308E.00 06.872.66 0.157E+00 0.107E.00 0.179E-01 326.66 0.2662-61 0.488E-01 6.9682-61 0.104E.00 0.982E-02 6.8262-01 0.312E.00 0.682.E+0 0.175266+0 0.136200 6.168E.66 346.6 W6.183E-61 6.444E-61 0.827E-01 6.9482-61 6.923E-01 6.7632-01 0.2912.00 .6.80E.66 0.177E.00 6.2512E00 6.1752.66 366.66 0.1262E-02 9.3932-01 9.734E-61 6.8462-01 06.43E-62 0.6962-01 6.284E.00 0.5462.66 0.1762.66 0.16280E66 .2362.66 386.66 6.151E-01 6.3882-61 0.887E-01 0.788-2-6 0.807E-02 0.864E-01 0.251E.00 0.518E+00 0.172E66 0.8262E.66 0.248E.06 466.66 6.147E-61 6.359E-61 06.72E-61 0.769E-61 0.7962-01 6.6462-61 0.245E+00 6.562.66 0.1882+00 6.152.66E0 0.233E.66 426.66 0.144E-02 0.363E-01 9.6869E-61 0.758E-61 6.7782-61 06.282-61 0.2412.00 6.497E.66 6.264E+66 6.149E.00 0.219E+00 446.6 "6.142E-61 6.347E-01 0.849E-01 0.744E-01 0.764E-01 6.8182-61 0.237E.00 0.48992+00 0.162.660 0.144E+00 0.207E.66 486.66 0.1462-61 0.342E-01 6.639E-61 6.7332-61 9.753E-01 6.810E-61 6.234E.00 0.482E.66 0.152.67E0 0.139E.66 0.198E.00 480.66 6.1382-61 6.3382-61 0.833E-01 6.7282-61 0.746E-2- 06.042-01 0.232E.66 6.4772.66 0.152.66E0 0.235E.66 6.186E+06 566.66 0.137E-02 6.3352-61 0.829E-01 0.721E-01 9.7412E-02 6.6662-01 0.2362.00 0.474E.66 6.153E.00 0.231E.00 0.177E+06 526.66 0.1352-61 0.332E-01 06.24E-61 0.7628-01 6.7362-61 6.5982-61 0.229E.66 0.479E2006.152.666+0.127E.00 6.16882*66 546.66 0.134E-61 6.329E-01 0.826E-01 0.712E-61 0.731E-61 06.92E-01 6.2272.66 0.4882.66 6.1492.66 6.124E+00 6.1860E66 586.66 0.133E-02 6.327E-61 6.8152-61 0.768E-61 6.7282-61 06.88E-01 0.2282.+" 6.4832.66 6.1472.06 9.120E.66 6.1512.66 586.66 0.132E-62 0.324E-01 06.11E-61 0.761E-61 8.7212E-61 0.584E-01 0.2242.66 0.459E+00 6.1452.W06 .1172.66 0.144E.66 8W00.6 0.130E-61 0.321E-01 6.8682-61 06.982-61 6.7162-01 .6.86E-01 6.223E.66 0.458E.60 0.243E.66 0.113E.00 6.1382.66 826.66 0.129E-61 0.329E-01 6.8022-61 0.891E-61 0.7112E-61 0.5762-61 0.221E.00 0.462E.66 0.2412.660 8.1102,00 0.129E.66 646.66 6.1282-61 6.3628-01 6.597E-01 06.888-2-6 6.7662-61 06.722-01 0.220E.00 0.448E.66 0.239E.06 0.1072.88 0.1222.60

886.66 0.127E-61 0.3142-01 06.93E-61 0.882E-61 0.702E-61 6.5682-01 0.2182E+" 0.4452.00 6.1372.66 6.1642.66 6.1182.66 886.66 6.1282-61 0.311E-61 06.89E-01 06.77E-61 0.897E-01 6.6852-01 9.217E.66 0.442E.66 0.238E.66 6.10662.66 0.1162+00 766.66 6.1252-01 0.309E-01 06.852-61 0.673E-01 06.92E-01 .6.81E-01 0.2152.66 0.439E+00 0.2342.66 0.974E-01 0.104E.66 726.66 0.124E-61 6.3682-61 0.581E-01 6.6882-61 6.8882-61 6.5582-61 0.214E.66 0.43526E+0 6.1322.66 6.9452-61 0.9832-01 746.66 0.123E-01 6.304E-01 06.772-01 06.642-61 0.684E-61 06.54E-61 0.2132.66 0.432E+06 0.1362+66 6.917E-61 5.930E-01 766.66 6.122E-61 6.302E-01 06.74E-01 6.686-61 06.88E02-6 6.5512E-01 0.2112.66 0.429E.66 0.129E.00 0.890E-61 0.881E-01 786.66 0.121E-61 6.36K02-6 6.5762-01 0-6.85802- 0.6762-61 6.5482-61 0.2162.66 0.427E.66 0.127E.00 0.883E-61 0.833E-61 8"60.6 0.120E-61 6.2982-61 6.587E-01 0.6.83E-01 06.72E-2- 06.452-61 0.209E.00 0.424E.66 0.128E.66 6.8382-61 6.7882-61

826.66 6.129E2-6 6.2982-1 6.56832-61 0.649E-2-6 6.8882-61 06.422-01 0.208E.00 0.421E.66 0.1242.00 6.8132-61 0.7482-01 846.66 0.182E-61 0.2942-01 8.5680-01 06.482-61 6.8652-01 06.39E-01 0.207E.66 0.4182.66 0.122E.66 0.789E-01 0.7082-01 886.66 0.127E-61 6.2922-01 06.57E-61 0.842E-02 .6.81E-61 06.362-61 0.20682.00 0.418E+00 0.1212.660 0.76882-01 0.887E-61 886.66 0.117E-02 0.29K02-1 06.54E-61 6.839E-61 6.858E-01 06.34E-02 0.205E.66 0.4132.66 0.1262.660 6.743E-01 0.8312-01 ALL COMBUSTIBLE MATERIALS WERE CONSUMED BY: 896.6666 SEC

rM

TOTAL 6.6002.66

0.4882-61

0.940E-01

0. 1382.66

6. 1802.66

0. 223E.00

6.2482.66

6.2482.66

0. 24 72.66

6.2472.66

6.2472.66

6.2472.66

6. 2482.66

0. 2482.66

0. 2482.66

6.1622.601

0. 1782.61

0. 1782.61

6.12742.61

6.1702.61

0. 1652.01

0.1280E+01

6.1582.61I

0 6.132.61

0. 1562.01

0. 1482.01

0. 1482.01

6. 1442.01

0. 142E+2.0

6.12462.61

0.1382.61

6.12382.01

0. 134E.02

6. 1322.61

6.12362+61

6. 1282.01

6.12272.01

0. 125E.01

6. 1242.01

6. 1222+61

0. 121E+02

6.1192.61

0.1182.01

6.1172.01

0.115E.01

6. 1142.61

0.1142.01

0.1123E.01

6. 1122.61

0.21112.01

0.118E+01

9W.066 0.182E-01 0.2892-01

926.66 0.152S-61 6.2882-61 946.66 6.1152-01 0.287E-02 960.6 6 .1142-02 6.2862-01

986.66 0.114E-01 0.285E-01 160M0.0 0.113E-01 0.284E-01

06652E-01 06837E-01 6.866E-01 06.322-01

06.512-01 6.8382-61 6.6552-01 06.31E-61

06.492-61 06.342-01 0.6.83E2-61 .6.30E-01 06.482-61 06.322-61 6.8512-61 06.282-61

06.482-01 0.630E-01 06.49E-01 0.5262-01

06.43E-01 0.827E-01 0.848E-01 06524E-01

0.204E.00 0.411E+90 0.2182.66 6.7222-01 0.204E.66 0.410E+66 0.117E.66 6.7622-61 0.203E.66 0.469E.66 9.116E.00 0.8822-01 0.203E.00 0.4072.66 0.2126E+0 0.8822-01 6.202E+66 0.406526 0.1142E66 0.8422-01 0.201E.00 0.403E.66 0.112E.00 06823E-01

0. 598E-01

5.6.588-61

0..538E-01

06. 5608E-81 6. 4782-61

0.460E-01

TIME EXCEEDS USER SPECIFIED TIME AT: 1666.6000 SEC
TABLE E.10. ARAD.DAT File from Problem One

OUTPUT FOR RADIOACTIVE SOURCE TERM

TIME ACCUMULATED MASS (0) ON:

(S) FLOOR WALL CEILING VENTS ENVIRON

*10.0 O.OOE.160. 16.000 U9 .OSSE+00 0.00 +00.1 S. +00.1

28.00 0.240E-06 0.811E-05 8.113E-03 0.573E-05 0.287E-08 40.W 0.10SE-04 0.327E-84 0.233E-03 0.260E-04 0.122E-07 60."6 0.260E-04 6.728E-64 0.366E-03 0.59SE-04 8.298E-07

80.60 0.467E-04 9.227E-03 0.479E-03 0.222E-03 0.664E-07

116.06 0.723E-04 0.194E-03 U.665E-03 OI.8E-.83 9.900E-07 220.06 0.20SE-03 0.274E-03 0.730E-03 0.267E-03 0.134E-06 140.006 .244E-03 0.362E-03 0.943E-03 0.370E-93 0.18SE-08 180.16 0.289E-03 0.428E-03 0.944E-03 0.496E-03 9.248E-06 1890.16 0.241E-03 0.499E-03 0.103E-02 0.640E-03 0.320E-08 200.16 8.298E-03 0.566E-03 0.112E-02 0. 808E-03 9.403E-08 220.106 .361E-03 0.63SE-83 0.119E-02 0.994E-03 0.497E-66 240.00 0.43DE-63 6.760E-63 8. 126E-02 8. 28E-02 08.62E-08 260.10 0.603E-93 9.764E-03 0.132E-02 0.244E-92 0.710E-08 280.16 0.682E-03 08.2SE-03 0.13SE-02 0.289E-02 0.846E-08

.316.16 0.673E-03 0.957E-03 0.149E-02 O.161E-91 0.764E-06

320.16 0.244E-02 0.122E-02 0.188E-02 0.330E.-02 0.16E-04 340.00 0.297E-02 0.160E-62 0.193E-02 0.297E+00 9.989E-64

386.16 0.262E-02 0.197E-02 0.222E-02 0.485E*8 0.262E-03

388.16 8.432E-021 0.23&E-02 0.263E-02 0.616E*001 0.258E-03

416.16 0.692E-02 0.274E-02 0.283E-62 0.6521E+00 0.278E-03

420.16 0.744E-02 0.312E-02 0.323E-02 0.678E*00 0.299E-93 446-00 0.887E-01 0.349E-02 6.343E-02 0.801E+00 0.392E-03 460.16 0.202E+00 0.388E-02 0.372E-02 0.622E+00 0.311E-03

480.06 0.226E+00 0.420E-02 0.40DE-02 0.834E.+00 0.317E-03 m 560.16 0.128E+00 0.463E-02 0.427E-02 0.643E+00 0.322E-03 6 28.16 0.141E+00 *.48SE-02 0.463E-02 0.651E.88 9.328E-03 548.16 0.163E+00 0.618E-02 9.47E-92 0.6880E+08 9.33SE-03 CD S868.006 .2865E6 0.64SE-02 0.602E-02 0.869E+00 0.334E-03

668.16 O.177E+OO 0.674E-082 9.62SE-02 8.677E*. 8.339E-03

608.160.288E00.1 0. 602E-02 8. 548E-02 O.OSSE0E1 9. 343E-03

628.16 0.299E.86 9.62SE-02 6.67DE-02 0.694E+90 0.347E-03

640.16 0.210E+00 9.664E-82 0.591E-02 0.702E.16 0.361E-03

688.16 0.220E.86 9.890E-02 9.612E-02 0. 716E.1 O.355E-03

68.0.6 9.230E*00 9.76SE-02 0.633E-02 8.717E..16 0.359E-03

716.160 .239E+0068.729E6-2 0.8653E-02 9. 724E+00 0.362E-03 720.00 8.2496.16 0.763E-62 0.672E-02 8.731E+00 8.3686-03

740.16 0.2576.16 0.7766-82 08.92E-02 0.738E.16 0.369E-03

760.16 0.2866E+00 0.799E-02 0.711E-02 0.744E+00 0.372E-03 780.16 0.2756E+00 0.822E-02 0.729E-02 0.760E+00 0.375E-03

816.16 0.283E+00 0.944E-02 0.747E-02 0.7566.10 8.3786-03

820.16 0.290E+00 0.868E-02 0.7656-62 0.761E+00 0.381E-03

840.16 0.2986.00 0.887E-02 0.783E-02 0.767E+00 0.384E-03

660.16 0.306E+00 0.908E-02 0.801E-02 0.772E+00 0.3986E-03

888.16 0.3126.16 0.9296-02 6.818E-02 0.7776.16 0.3696-03

916.16 8.3196.16 0.949E-82 0.834E-02 6.7886.16 0.39M6-03

928.16 0.3266.160 0.967E-02 8.8506-02 6.7816.16 0.392E-93

940.16 0.333E.88 0.9856-42 0.8656-02 0.7836.88 0.392E-03 960.16 0.3396.16 6.1166-81 0.879E-02 0.786E+00 0.393E-03

980.1060.346E+00 0.102E-01 0.892E-02 0.789E+00 0.3956-03

1816.16 8.3526.16 0.1036-01 0.905E-02 9.792E.88 8.3966-03
TABLE E.11. ASMK.DAT File from Problem One

OUTPUT FOR SMOKE SOL1RCE TERM

TIME ACCUMULATED MASS (0) ON: (S) FLOOR WALL CEILING VENTS ENVIRON 6. . ".6E6 a.6636 so.6663.F66 0.663.6 6.406E+00 2066681364 6. mom3-62 623GE-01 6124E-062 0.822E-066 40.6 6.174E-93 ".62E-02 6.4783-01 6.565E-02 0.283E-06 WO.6 6.419E-03 :.249E-02 9.7830-01 0.137E-01 0.687E-05 80e.6 W6.7853.43 6.265E-61 0.997E-01 6.255E-01 0.128E-04

166.66 6.1363.42 0.424E-02 6.127*.06 6.410E-01 0.21@E.-"

120.66 6.1983-42 6.5953.41 6.156366* 0.685E..61 0.317E-"4 140.66 0.286E3-02 .7763-61 0.183E.00 6.895E-61 6.4483-64

166.006.8953-42 0.969E-01 0.207E.60 0.122E+06 0.620E-84 186.66 0.5263-62 0.114E.66 6.2293.M06 .161E.00 0.866E-64 266.66 0.6603-02 6.183.66M 6.2563.66 6.267E.6 0.1643-03

22.0.6 0.860E-02 0.1493.00 6.2603.66 0.261E.00 0.231E-03

240.6 "6.107E-01 6.1663.66 0.287E.66 0.328E446 0.162E-03

2".66 0.131E-02 0.264E.00 6.3643.66 6.8953.66 6.1983-68

280.66 0.158E-01 6.2013.66 6.3263.66 6.4773.66 0.239E-03

366.66 6.1863-61 6.2223.66 6.8383.66 0.214E..01 0.107E-02'

826.66 0.202E-01 6.3233.66 6.40663.66 6.6633.61 0.332E-62

846.66 0.8963446 0.604E.00 06.813.66 0.100E03 0.5603E-01

880.66 0.1103.01 0.20653.02 6.9553.66 6.257E.63 6.1283.66

886.66 0.218E+01 0.2683E+01 0.142E+01 0.382E+038 0.1813.66

466.66 6.8193.61 0.223E.02 0.190E.01 0.397E+03 6.1993.66

42.0.6 0.421E.61 0.285E.01 0.2393.61 0.426E.68 6.2133.06

446.66 0.528E.61 0.346E.01 0.288E.61 0.461E+03 0.228E+00 486.66 6.6273.61 6.4693.61 0.339E.61 0.474E+08 0.237E.66

486.00 0.732E+.61 8.472E.01 0.389E.01 6.4803.68 6.2443.66 5660.66 0. 44E+02 06.373.61 0.442E+61 0.499E+03 0.250E.66 6 26.66 6.9643.61 6.6653.01 6.497E.61 06.11E+03 6.256366* -646.66 0.169&.02 0.6763&01 0.555E+61 065243408 0.262E*00 5B6.66 0.1283E.62 0.751E+01 6.6173.61 06.5883.6 6.2693.66

560.66 6.1363.62 6.683.610 0.682E.61 0.564E+03 0.277E.66

666.66 6.1543.62 0.9143.61 0.7563.01 06.70E+03 0.286E3.66

626.66 0.171E.62 0.2663+02 0.822E.61 06.883+03 6.2943.66

646.66 0.189E.62 6.1603.62 6.8973.61 0.60663.63 6.633.66 "06.66 0.208E.02 0.219E.02 0.9763.61 6.86253.6 6.8183.66

686.66 0.220E.62 0.129E.02 0.106E.62 0.645E34 0.8283.660 7W6.66 0.249E.62 0.139E.62 0.114E.02 .6.685034 6.833.660 726.66 6.2713.62 6.1563442 6.1283.6P2 6.6853.63 0.3483.660 746.66 0.294E.62 0.162E.62 6.1383.62 0.706E3.6 6.8583.66 766.66 0.818E.02 6.273E.62 6.142E.62 6.7273.63 6.3643.66 786.66 0.344E.62 6.1653.62 6.1523.62 0.749E.68 0.3753.66 866.66 0.370E.62 0.2973.62 0.1623.62 0.770E+3.6 6.8853.66 826.66 0.3973.62 6.2163.62 0.173E.62 0.7923.68 0.3963.66

846.66 0.4253.62 0.2233.62 0.184E442 0.8183.603 6.4673.66

866.66 6.4543.62 0.2363.62 6.1953.62 6.883.680 6.4183.66 886.66 0.484E.62 0.2563.602 0.206E.62 0.856.6E+3 6.4203.66 966.66 06.5153.2 6.2643.62 6.2173.62 0.872E.63 6.43883.6 926.66 06.453.62 0.2763.62 6.2283.62 6.8763.68 0.438E.66 946.66 06.753.62 0.288E.62 0.2383.02 6.8853.68 0.443E.00 966.66 0.6053.62 6.3663.62 0.248E.62 0.898E.63 6.4493.66 986.66 0.6343.62 0.810E.62 0.2573.02 0.913E.63 0.457E.00 1666.66 0.86834402 0.321E.02 .2663.62 6.929E.63 6.4653.66

NUREG/CR- 3037

PNL -4532

RZ

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34 Pacific Northwest Laboratory

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MAC FORM 335 U.S. NUCLEAR REGULATORY COMMISSION I REPORT %UMBER lAs,gpose r) TOC, ad Val N6. I*"y

%AC. 1102

30.22BIBLIOGRAPHIC DATA SHEET NUREG'/CR-3037

$11 INSTRUCTIONS ON TH4E REVERSE PNL-4532 2. TITLE AND SUBTITLE 3 LEAVE BLANKC

User's Manual for FIRIN: A Computer Code to Estimate

.Accidental Fire and Radioactive Airborne Release in

Nuclar Failiies4 uelCycl DATE REPORT COMPLETED

MONTH YEAR

S AUTHOMISI M.K. Chan November 1988

M.Y. Ballinger MONTH AERPOTISEDAA Y 

P.C. Owczarski I __________________________________________ February 1989 7PERFORMING ORGANIZATION NAME AND MAILING ADDREFSS 1MI.lde Zo Coda S. PROJECT ITASK/WORK UNIT NUMBER

Pacific Northwest Laboratory _______________

Ri~chland, WA 99352 9. FIN OR GRANT NUMBER

B2481

10. SPONSORAING ORGANIZATION NAME AND MAILING ADDRESS (Melude Zip Co*.I I Ia. TYPE OF REPORT

Division of Industrial and Medical Nuclear Safety

Office of Nuclear Material Safety and Safeguards _______________

U.S. Nuclear Regulatory Commnission u.PERIOD COVERED thwfusme mina

Washington, D.C. 20555

12. SUPPLEMENTARY NOTES

13. A6STRACT 400 ýf5 Of orUJ

The U.S. Nuclear Regulatory- Commission has sponsored a research program to better

estimate the source term, or amount and characteristics of radioactive material made

airborne, from several types of accidents. The most concentrated work has been

done on fires, resulting in'the development of FIRIN, a compartment fire code that, estimates the release and distribution of radioactive materials within a room

from fires involving radioactive materials. The User's Manual describes the

technical basis of the code and provides input and output-information for code

users.

14 DOCUMENT ANALYSIS - 8. KEYWOROSIDE1SCRIPTORS 15 AVAILABILITY

Source Term Computer ModelsSTEMN

Fire Nuclear Fuel Cycle unlimited

Radioactive

Accident Analysis 16. SECURITY CLASSIFPICATION

0. IOENIPIERBSIOPEN.ENOSO TERMS "

unclassified

1, NUMBEII OF PAGES

is PRICE

* U.S. GOVERNMENT PRINT ING OFF ICE :1989- 242-.863 108151




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