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Theses and Dissertations Thesis Collection

1988

Computer model of an aviation gas turbine test facility.

Meaker, Michael J.

http://hdl.handle.net/10945/22974

NAVAL POSTGRADUATE SCHOOL

Monterey , California

THESISM lf\ q 5M-3

COMPUTER MODEL OF ANAVIATION GAS

TURBINE TEST FACILITY

by

Michael J. Meaker» » »

September 1988

Thesis Advisor: David Salinas

Approved for public release; distribution is unlimited

T2<*21?4

UNCLASSIFIEDiCURlTV CLASSIFICATION OF THIS PAGE

REPORT DOCUMENTATION PAGE

a REPORT SECURITY CLASSIFICATION

UNCLASSIFIEDlb RESTRICTIVE MARKINGS

». SECURITY CLASSIFICATION AUTHORITY

b DECLASSIFICATION /DOWNGRADING SCHEDULE

3 DISTRIBUTION. AVAILABILITY OF REPORTApproved for public release;

distribution is unlimited

PERFORMING ORGANIZATION REPORT NUMBER(S) 5 MONITORING ORGANIZATION REPORT NUMBER(S)

3 NAME OF PERFORMING ORGANIZATION

feval Postgraduate School

6b OFFICE SYMBOl(If applicable)

Code 69

7a NAME OP MONITORING ORGANIZATION

<. ADDRESS (Oty. State, and ZIP Code)

Monterey, California 93943-5000

7b ADDRESS (City, State, and ZIP Code)

Monterey, California 93943-5000

la. NAME OF FUNDING / SPONSORINGORGANIZATION

Jb OFFICE SYMBOL(If applicable)

9 PROCUREMENT INSTRUMENT IDENTIFICATION NUMBER

lc. ADDRESS (City. State, and ZIP Code) 10 SOURCE 0= FUNDING NUMBERS

PROGRAMELEMENT NO

PROJECTNO

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II. TITLE (Include Security Classification)

Computer Model of an Aviation Gas Turbine Test Facility

12 PERSONAL AUTHOR(S)MEAKER, Michael J.

13a. TYPE OF REPORT

Master's Thesis3b T -ME COVEREDFROM T

14 DATE OF REPORT (Year. Month, Day)

1988 September15 PAGE COUNT

127

16. SUPPLEMENTARY NOTATION

The views expressed in this thesis are those of the author and do not reflect the official

policy or position of the Department of Defense or the U.S. Government

17 COSA Ti CODES

FIELD GROUP SUB-GROUP

18 SuBjECT TERMS {Continue on reverse if necessary and identify by block number)

PHOENICS, Parabolic, Hyperbolic, FIINIT (Field Initialization

19 ABSTRACT (Continue on reverse if necessary and identify by block number)

A computer model of an aviation gas turbine test facility was developed and analyzed tocompare computer generated gas pressures, temperatures, and velocities to those of anactual, operational test facility. The computer model simulated the Royal Danish Air ForceTest Facility at the Skrydstrup Air Force Base, Denmark. The Parabolic, Hyperbolic, orElliptic Numerical Integration Code Series (PHOENICS) was used. The Computer Model outputcompared well with actual data obtained from the Denmark test facility. Tabular Data andFigures are presented.

20 DISTRIBUTION /AVAILABILITY OF ABSTRACT^UNCLASSIFIED/UNLIMTED SAME AS RPT DTlC USERS

21 ABSTRACT SECURITY CLASSIFICATIONUNCLASSIFIED

22a NAME OF RESPONSIBLE INDIVIDUALDavid Salinas

22b TELEPHONE (Include Area Code)

(408)646-342622c OFFICE SYMBOLCODE 69Sa

DDFORM 1473, 84 mar !3 APR edition may be used until exhausted

AH other editions are obsoleteSECL'R'TY CLASSIFICATION O^ TH'S PAGE

«US Government Printing Ottice 1986—60t 243

Approved for public release; distribution is unlimited,

Computer Model of anAviation Gas

Turbine Test Facility

by

Michael J. MeakerLieutenant Commander, United States NavyB.A. , University of North Florida, 1977

Submitted in partial fulfillment of therequirements for the degree of

MASTER OF SCIENCE IN MECHANICAL ENGINEERING

from the

NAVAL POSTGRADUATE SCHOOLSeptember 1988

ABSTRACT

A computer model of an aviation gas turbine test

facility was developed and analyzed to compare computer

generated gas pressures, temperatures, and velocities to

those of an actual, operational test facility. The

computer model simulated the Royal Danish Air Force Test

Facility at the Skrydstrup Air Force Base, Denmark. The

Parabolic, Hyperbolic, or Elliptic Numerical Integration

Code Series (PHOENICS) was used. The Computer Model output

compared well with actual data obtained from the Denmark

test facility. Tabular Data and Figures are presented.

111

The£i6M9<W543

TABLE OF CONTENTS

PAGE

I

.

INTRODUCTION 1

A. BACKGROUND 1

B. NATURE OF THE PROBLEM 1

1. STRUCTURAL DEGRADATION 1

2 . OBSOLESCENCE 2

3 . NOISE 2

4. AIR POLLUTION 3

C. TYPES OF TEST FACILITIES 3

1. RUN-UP PAD 3

2. SOUND SUPPRESSORS 4

3. OPEN TEST STAND 4

4. HUSH HOUSE 4

5. FULLY ENCLOSED TEST CELL 4

D. RESEARCH GOAL 5

II. TEST FACILITY OPERATION 7

III. DESCRIPTION OF PHOENICS 10

A. WHAT IS PHOENICS 10

B. HOW PHOENICS WORKS 10

C. PHOENICS INPUT LANGUAGE 14

D. MODEL GEOMETRY 14

1. CYLINDRICAL-POLAR COORDINATE SYSTEM 14

2. BODY-FITTED COORDINATE SYSTEM 15

IV

.

3. CARTESIAN COORDINATE SYSTEM 15

E. POROSITY AND BLOCKAGE 16

F. SOURCE AND BOUNDARY CONDITIONS 18

G. INITIAL CONDITIONS 20

H. MAXIMUM/MINIMUM VALUES 20

I. UNDER-RELAXATION FACTORS 21

J. PROGRAM RUN PROCEDURES 22

IV. MODELING THE DENMARK TEST FACILITY 24

A. MODEL DESCRIPTION 24

B. MODEL BOUNDARY CONDITIONS ANDTURBULENCE MODELS 28

V. ANALYSIS OF RESULTS 30

A. OBTAINING A FINAL SOLUTION 30

B. COMMON SENSE APPROACH 31

1. PRIMARY AIR INLET 31

2. TEST BAY 32

3. SECONDARY AIR INLET 35

4. AUGMENTOR TUBE 36

5. EXHAUST STACK 39

C. COMPUTER DATA AND FIELD DATA COMPARISON 4

D. CONSERVATION EQUATION BALANCES 41

E . CONVERGENCE 42

F. SUMMARY 44

VI . RECOMMENDATIONS 45

A. INTRODUCTION 4 5

B. BFC 4 5

C. PHOTON 4 5

D. ALTERNATE TURBULENCE MODELS 46

E. GRID REFINEMENT 46

F. BAFFLE MODELING 46

APPENDIX A Ql CODE 47

APPENDIX B EARTH OUTPUT 61

APPENDIX C FIGURES 87

LIST OF REFERENCES 117

INITIAL DISTRIBUTION LIST 118

VI

LIST OF FIGURES

FIGURE PAGE

C.l Denmark Jet-Engine Test Facility 88

C.2 Staggered-Grid Cell Configuration 89

C.3 Cartesian Cell Configuration 90

C.4 PHOENICS Data Group Catagories 91

C.5 CONPOR Porosity And Blockage 92

C.6 COPYQ1 EXEC And JCL Files 93

C.7 RUNSAT EXEC File 94

C.8 RUNSAT JCL File 95

C.9 RUNEAR EXEC And JCL Files 96

CIO Test Facility Side View (Y-Z Plane) 97

C.ll Test Facility Top View (X-Z Plane) 98

C.12 Vertical Y-Z Plane Zones 99

C.13 Horizontal X-Z Plane Zones 100

C.14 Ql Method-Of-Pairs Coding Sequence 101

C.15 EARTH Method-Of-Pairs Output 102

C.16 System Domain Grid (X-Z Plane) 103

C.17 System Domain Grid (Y-Z Plane) 104

C.18 H vs Y-Axis at IY=1 to IY=10 105for IX=1 and IZ=16

C.19 W vs Y-Axis at IY=1 to IY=10 106for IX=1 and IZ=16

C.20 H vs X-Axis at IX=1 to IX=5 107for IY=5 and IZ=16

VII

C.21 W vs X-Axis at IX=1 to IX=5 108for IY=5 and IZ=16

C.22 H vs Y-Axis at IY=1 to IY=10 109for IX=1 and IZ=20

C.23 W vs Y-Axis at IY=1 to IY=10 110for IX=1 and IZ=20


C.25 W vs X-Axis at IX=1 to IX=5 112for IY=5 and IZ=20

C.26 H vs Z-Axis at IZ=21 to IZ=26 113for IX=1 and IY=13

C.27 V vs Z-Axis at IZ=21 to IZ=26 114for IX=1 and IY=13


C.29 V vs X-Axis at IX=1 to IX=5 116for IY=13 and IZ=23

vm

I. INTRODUCTION

A

.

BACKGROUND

The United States Navy desires to provide standardized

test facilities for the testing of its aviation gas turbine

jet engines (Ref 1)

.

Today's high performance and high technology jet

engines require accurate, consistent, and controlled

testing to assess performance throughout the jet engine's

entire operational range Modern day test facilities must

incorporate state of the art equipment and instrumentation

such that jet engines may be tested in or out of the

aircraft, around the clock, and year round.

B. NATURE OF THE PROBLEM

Presently, 7 5 Navy and Marine Corp activities worldwide

operate 81 Jet Engine Test Facilities (Ref 1) . Of these,

60 are fully operational and 51 are over 25 years old.

Immediate problem areas which hinder operational needs

include: structural degradation, obsolescence, noise, and

air pollution.

1. Structural Degradation

High jet engine exhaust gas temperatures and water

impingement on diffusers and interior concrete walls have

caused cracking and spalling of test facility interiors.

Concrete reinforcing rods exposed to a hot, moist

environment will corrode and thereby reduce structural

integrity. Noise reduction baffles and exhaust gas turning

vanes are being damaged by flying concrete debris.

Replacement of baffling and turning vanes is required as

often as every three years. The maintenance requirements

navy wide has significantly increased the workload and

operational costs of the Navy Public Works Department.

2

.

Obsolescence

Several of the test facilities require major

modernization or even complete replacement due to current

aircraft designs and test requirements. Examples of

modernization include improved engine handling systems and

engine thrust stands. Increased access to engine

components and test points greatly improves testing

efficiency. Additionally, with today's high technology

engines, state of the art data acquisition systems are

required.

3

.

Noise

Most of the older test facilities use water for

exhaust gas cooling. The water and the high exhaust gas

temperature deteriorates the acoutic baffling silencing

capabilities. The increased . noise level degrades the work

environment. Worker efficiency is reduced and the high

test facility interior sound levels are being suspected of

contributing to engine deterioration. State of the art

engines using thinner, lighter materials are more sensitive

to acoustic fatigue (Ref 1)

.

4 . Air Pollution

Today's high power and high mass flow engines

constitute a major problem to the environment. Visible

particulate matter is emitted in excess of allowable

environmental pollution standards. By Executive Order

Number 11282, May 26, 1966 (Ref 2), Jet Engine Test

Facilities must meet local laws concerning the environment.

Judicial action by the state of California against Jet

Engine Test Facilities within California (Ref 3) has

identified a need to address pollution control measures

during the design, construction, and operation of Jet

Engine Test Facilities.

C. TYPES OF TEST FACILITIES

The Navy operates five types of Jet Engine Test

Facilities (Ref. 1) . Each facility utilizes some form of

hold down device for the engine or the aircraft and

instrumentation to monitor the performance of the engine.

Each facility must be designed such that several engine

types may be tested (e.g., turboprop, turbofan, turboshaft,

turbojet) . The types of facilities are:

1. Run-up Pad

The simplest test facility is the run-up (power

check) pad. Normally, the engine is tested while installed

in the aircraft. Therefore, the aircraft acts as the hold-

down device. The run-up pad is usually located in remote

locations due to high noise levels encountered during

testing.

2

.

Sound Suppressors

These are usually equipment packages which are used

to reduce inlet and exhaust noise from a tied down

aircraft. The sound suppressors may be used to augment or

to substitute for the run-up pads.

3

.

Open Test Stand

This is an outdoor test facility which supports and

constrains the engine during test. Due to noise levels,

the open test stand must be located in a remote area.

Portable sensors and instrumentation are utilized to

monitor engine performance.

4

.

Hush House

This is a total aircraft enclosure. It permits

round the clock and year round testing. Normally on twin

engine aircraft, only one engine may be tested in full

after burner. The other engine is held at idle.

5. Fully Enclosed Test Cell

This test facility is normally capable of testing

several types and sizes of jet engines. The engines may be

in or out of the aircraft. The facility is normally

equipped with all the necessary instrumentation and data

gathering equipment required to perform routine or complex

testing after jet engine rework or overhaul. Testing may

be performed round the clock and year round.

The type of test facility to utilize at an activity is

dependent upon several factors. Availability of military

construction funds, required control of noise and emissions

(environmental concern) , amount of maintenance testing, and

military and civilian manpower requirements are all key

factors.

D. RESEARCH GOAL

To provide quality jet engine testing, to comply with

local environmental standards, and to ensure fleet

readiness, the Navy embarked on a comprehensive program in

1984 to upgrade and to modernize as necessary all jet

engine test facilities under its cognizance. To this end,

it was necessary to review existing jet engine test

procedures and to examine jet engine test facilities to

determine which facilities met desired criteria.

Additionally, the Navy decided to explore the feasibility

of the computer modeling of aviation gas turbine jet engine

test facilities. It was felt that if a computer model

could accurately represent an actual operational test

facility then a computer model could also be used to

predict the operation of future proposed test facilities.

The purpose of this research was to computer model the

Royal Danish Test Facility and to compare computer

generated temperatures, pressures, and velocities with

actual data obtained in the field and to investigate

techniques necessary to make computer simulations of flow

and temperature fields useful for predictive purposes.

II. TEST FACILITY OPERATION

The basic geometry of the Denmark test facility is

shown in Figure C.l. For simplicity all storage areas,

engine preparation rooms, and control modules are not

included. The test facility is basically comprised of the

primary air inlet, a test bay, an exhaust duct (also called

an augmentor tube) , secondary air inlets, and an exhaust

stack. Turning vanes, which are not shown, are located in

the exhaust duct to exhaust stack transition region. This

feature better utilizes the total exhaust stack cross

section with an attendant reduction in exhaust gas noise

(Ref 4). Baffles (not shown) are located at three places:

At the top of the exhaust stack, within the secondary air

inlets, and within the primary air inlet (test bay doors)

.

The baffles also provide noise reduction (Ref 4)

.

During a jet engine test, the engine is aligned with

the centerline of the exhaust duct. This can be

accomplished either with the engine in the aircraft or with

the engine supported in a test stand. With proper

alignment, a near uniform flow profile develops (Ref 3)

inside the augmentor tube. Primary air is drawn in through

the primary air inlet (test bay door/baffle configuration)

.

For a F-100 Engine, at full throttle and after burner on,

the primary air mass flow rate is 260 kg/sec of which

100 kg/sec is the mass flow rate through the engine

(Ref . 4) . As the exhaust gas enters the augmentor tube,

air from within the test bay is entrained into the

augmentor tube. The exhaust gas moving through the

augmentor tube also entrains air coming through the

secondary air inlets. The secondary air mass flow rate is

340 kg/sec (Ref. 4) . Both the entrained primary and

secondary air play an important role in the test facility

operation. Hot and noisy jet engine gases must be treated

prior to leaving the test facility in order to comply with

environmental standards. To treat jet engine exhaust, its

temperature, noise level, and particulate density must be

lowered.

The ratio of total "cooling" air (primary and

secondary) mass flow rate to the engine mass flow rate is

called the Augmentation Ratio. The Augmentation Ratio is a

key to successful test facility operation. With

appropriate primary air and secondary air mass flow rates,

the exhaust gas is sufficiently cooled which helps prolong

duct/stack life and the exhaust gas is sufficiently diluted

such that proper pollution levels are obtained (Ref. 2)

.

The Augmentation Ratio of the Denmark Test Facility is 5:1.

With a computer model that can accurately predict test

facility operation, design personnel will have the ability

to easily change model parameters such as engine location

or structural dimensions and to observe their effect on

8

test facility operation. For example by changing the

secondary air inlet configuration, the augmentation ratio

is changed. This in turn has an effect over exhaust gas

cooling. Additionally, design engineers may wish to

experiment with various exhaust stack heights or exhaust

duct openings. A mere changing of a few lines of computer

model source code accomplishes this. In all, a computer

model could save significant time and money in the design

of future jet engine test facilities.

III. DESCRIPTION OF PHOENICS

A. WHAT IS PHOENICS

PHOENICS is a general-purpose, computer-code system for

simulating fluid flow, heat transfer, and chemical reaction

processes in engineering equipment or the environment.

PHOENICS is an acronym for Parabolic, Hyperbolic, or

Elliptic Numerical Integration Code Series. Typical

applications of PHOENICS include: Thermal hydraulics of

nuclear reactors and other power plants; external

hydrodynamics and aerodynamics of cars, ships, buildings,

etc; air movement within an enclosed space, both under

normal conditions and in the presence of a fire; flows in

pumps and turbomachinery . PHOENICS was developed by D.

Brian Spalding of CHAM Ltd and of Imperial College of

London, England. Information regarding the history and

development of PHOENICS is contained in the user's guide

(Ref 5)

.

B. HOW PHOENICS WORKS

The PHOENICS computer code consists of two separate

computer programs: EARTH and Ql. The EARTH program

resides in the computer mainframe as an object code and

cannot be accessed by the user. The user couples his

problem (defined by the user) to the EARTH code. The EARTH

10

program contains the main flow simulating software and

various coding sequences which simulate the Laws of Physics

as applied to the conservation principles: energy, mass,

momentum. The Ql program defines the problem and differs

from one flow simulation program to the next. The Ql

program represents the user's decision as to what problem

is to be simulated. The Ql program activates the EARTH

program which solves the problem.

The PHOENICS code is capable of describing flow

simulations in terms of distributions in time and space.

The distributions involve assigning numerical values for

all dependent variables to an orderly array of cells

located in the physical domain of the problem.

Temperature, pressure, concentration, KE (Turbulence

Kinetic Energy) , and EP (Kinetic Energy Dissipation Rate)

values are located at a cell's center while velocity values

are located at the positive faces of the cells. A cell

configuration in the X-Y plane is illustrated in Figure

C.2. Temperatures, pressures, and concentrations would be

located at N, S, E, W, and G for example while velocities

would be at N', S', E', and W . A similar procedure is

utilized for the Z (low-to-high) direction. This

convention is called the "STAGGERED GRID" arrangement. If

the flow simulation is time dependent, the distributions

are obtained for each variable at a succession of times

11

instants. The Denmark test facility model flow simulation

is for steady state conditions.

In general, a PHOENICS flow simulation is four

dimensional: 1 time and three space coordinates. For ease

of reference to the user, PHOENICS measures time in the

past-to-future direction; X coordinates in the west-to-east

direction, Y coordinates in the south-to-north direction,

and Z coordinates in the low-to-high direction. This

concept is illustrated in Figure C.3. Although Figure C.3

represents a Cartesian configuration, individual cells may

vary in shape and size as determined by a user defined

code. This option, called BFC, was not utilized in this

investigation. The Denmark test facility model is a

Cartesian configuration of cells which vary in size.

PHOENICS calculates the dependant variables over the

complete set of cells, which defines the operational (e.g.,

system, physical) domain, with linear algebraic equations

that represent the conservation laws. Here the partial

differential equations are those governing the conservation

of energy, momentum, and mass and the linear algebraic

equations are obtained by the finite volume method. The

finite volume method is a method having some features from

the finite differencing method and the finite element

method. The conservation partial differential equations

will not be discussed here; except to say that the original

non linear, coupled conservation partial differential

12

equations are linearized. Interested readers are directed

to the PHOENICS User's Manual (Ref. 5) for detailed

information.

PHOENICS utilizes an iterative process involving a

multi-stage sequence of dependent variable value

adjustments. The process is repeated several times until

the left and right imbalance (called a residual) of each

equation is reduced to a negligible amount. A variety of

iterative procedures are available to the user. The

"SLAB-SWEEP" iterative process feature of PHOENICS for

equation imbalance reduction was chosen for the Denmark

test facility model. Slabs are arrays of cells having the

same Z (low-to-high) coordinate. PHOENICS conducts many

mathematical operations over a slab in an attempt to reduce

dependent variable imbalances among cells within the slab

prior to moving on to the next slab. The adjustment

operations are referred to as "SLABWISE SOLUTIONS". The

operations begin at the lowest numbered slab and continue

sequentially to the highest numbered slab. A sweep is a

completed set of slabwise operations. The equations for

dependent variable values at one slab are coupled to values

of other dependent variables at neighbor slabs. For this

reason numerous sweeps are normally required until all

dependent variable imbalances are negligible. This is a

necessary but not a sufficient condition for problem

convergence.

1 3

C. PHOENICS INPUT LANGUAGE

The source code used in a PHOENICS Ql program is

arranged in a 24 group data structure. Figure C.4 lists

the group categories of the data structure. The developers

of the PHOENICS code suggest this ordering of the groups

normally conforms to a well thought out flow simulation

problem description. However, any group ordering the user

desires will be acceptable to PHOENICS. It is the PHOENICS

defined variables and keywords plus the user defined

variables that actually trigger desired PHOENICS responses

as opposed to a particular group ordering. A detailed

description of group functions is explained in the PHOENICS

User's Manual (Ref . 5)

.

D. MODEL GEOMETRY

PHOENICS utilizes three distinct procedures for

defining a flow simulation operational domain (grid)

:

Cylindrical-polar, Body-fitted, and Cartesian coordinate

systems.

1. Cylindrical-Polar Coordinate System

The cylindrical-polar grid arrangement consists of

planes with constant Z coordinates that are perpendicular

to an axis of rotation, planes with a constant X coordinate

(usually called the Theta coordinate) that intersect with

the axis of rotation giving the X coordinate a

14

representation in radians, and concentric cylindrical

surfaces with a constant Y radial coordinate.

2

.

Body-Fitted Coordinate System

This arrangement is best thought of as starting

with an orthogonal group of cells made of clay. The cells

are then squeezed, bent, twisted, and stretched into the

desired shape for the fluid flow simulation operational

domain. Each cell although distorted in shape and size

still remains in contact with its original neighbors.

3

.

Cartesian Coordinate System

The Cartesian grid arrangement is composed of cells

in a mutually perpendicular X, Y and Z coordinate system.

As such the cell faces form planes that intersect at right

angles. The spacing between the cell faces (planes) is

user defined.

Due to the regularity of a Cartesian coordinate

system, the information required to specify the geometry is

rather modest. The PHOENICS variables NX, NY, and NZ

specify the number of cells the operational domain is to

have in the X, Y, and Z directions respectively. The

PHOENICS variables XULAST, YVLAST, and ZWLAST specify the

domain lengths in the X, Y, and Z directions. The "METHOD-

OF-PAIRS" is a PHOENICS coding sequence to specify the

number of cells per length of domain in the X, Y, and Z

directions. XFRAC, YFRAC, and ZFRAC are PHOENICS variables

for arrays used in the method-of-pairs coding sequence.

15

The odd indexed array elements, for example, XFRAC(l)

,

XFRAC(3), XFRAC(5), etc., specify the number of cells in a

particular length of operational domain while the even

indexed array elements XFRAC(2), XFRAC(4) , and XFRAC(6)

specifies the length of each cell. A negative argument for

the first element in each array tells PHOENICS that the

method-of-pairs is being utilized. For example, "XFRAC(l)

=-2.0;XFRAC(2)=0.1" tells PHOENICS the method-of-pairs is

to be used and that the first cell group in the X direction

is to have two cells and the length of each cell is 0.1

meter. "XFRAC(9) =4 . 0;XFRAC(10) =0. 15" specifies the number

of cells and lengths of each cell in the "FIFTH" X

direction cell group.

E. POROSITY AND BLOCKAGE

In any flow simulation problem there exists walls,

submerged bodies, or some form of obstruction to fluid

flow. For example, in Hagen-Poiseuille pipe flow the fluid

is confined to the interior of the pipe. Additionally, due

to wall friction the fluid's velocity at the wall is zero.

In a PHOENICS flow simulation problem, obstructions to

fluid flow must also be introduced. In a jet engine test

facility model one must be concerned with obstructions to

flow as a result of walls, floors, baffle material, turning

vanes, and the jet engine itself. To account for the

physical obstructions, PHOENICS makes use of the command

16

"CONPOR(R.R, TYPE,XF,XL,YF,YL,ZF,ZL) ". The real number

"R.R" normally has a value from 0.0 to 1.0. This value

tells PHOENICS how much obstruction to flow is to be

introduced by a surface or volume. For maximum obstruction

(blocked flow), "R.R" would be 0.0. The "TYPE" argument

specifies a surface or volume. For example a surface might

be the inside of the test bay ceiling. A volume might be

the geometric body of the jet engine. For a surface

obstruction the "TYPE" Arguments "WEST, EAST, SOUTH, NORTH,

LOW, OR HIGH" (the faces of an individual cell) are used.

For a volume obstruction the type "CELL" is used. The

arguments "XF, XL, YF, YL, ZF, and ZL" identify the first

and last cells of the obstruction domain in the X, Y, and Z

directions respectively. For example "CONPOR(0.0, HIGH,

1,3,1,1,3,3)" tells PHOENICS to introduce complete

obstruction to flow through the "HIGH" (Z direction)

surfaces of the group of cells starting at IX=1, IY=1, and

IZ=3, and ending at cells IX=3 , IY=1, and IZ=3

respectively. Each cell has an IX, IY, and IZ identity.

Figure C.5 illustrates "HIGH" surface obstruction to flow.

The cross-hatched surface blocks Z direction flow. "CONPOR

(0. 0,CELL, 1, 3 , 1, 1, 1, 3) " would introduce maximum obstruction

to flow through the surfaces of the volume defined by these

coordinates. In Figure C.5, the "CELL" volume outlined

with bold lines prevents fluid flow perpendicular to any of

its surfaces.

17

PHOENICS also has the ability to introduce wall or

surface "FRICTION" which brings about zero magnitude

velocity components on a cell's surface and calculates the

friction coefficient. For the above "HIGH" example, the

magnitude of flow in the Z direction was set to zero on the

surfaces of several cells. To also set the X and Y

velocity components to zero on the same "HIGH" surfaces,

the CONPOR command requires a slight modification.

Utilizing a "NEGATIVE" argument with the CONPOR command

accomplishes the desired action. For example

"CONPOR (0.0, HIGH, 1,3,1,1,3,-3)" causes the X, Y, and Z

velocity components on the "HIGH" surfaces of that

particular group of cells to be zeroed. Through the use of

the negative argument convention, velocity components on

the external surfaces of a volume (cell) can be zeroed, and

friction introduced into the model

.

F. SOURCE AND BOUNDARY CONDITIONS

In any PHOENICS flow simulation problem description,

the user's Ql program must introduce source and boundary

conditions to the EARTH program. Through the use of

PHOENICS keywords, source and boundary conditions may be

identified as energy, momentum, or mass flow. Energy

sources are identified with the enthalpy variable "H",

momentum by the velocity variables "U, V, or W" , and mass

flow utilizes the pressure variable "P". By using the

18

notation "HI" a fluid's first phase enthalpy would be

identified while "H2" would refer to second phase enthalpy

for a two phase flow simulation. Information about inflow

and outflow of any variable in the system domain is

conveyed to the EARTH Program by way of the PHOENICS

combination "PATCH-COVAL" statements. The PATCH command is

used to specify the location at which a source or boundary

condition is to be applied and to also specify the "TYPE"

factor or what the PATCH command is to do to the system

domain. The COVAL command is used to specify the

coefficient and value which combine to determine the

magnitude of the dependent variable over a PATCH. For

example, "PATCH (JETOUT, LOW, 1, 1, 5, 6, 8, 8, 1, 1)

;

COVAL (JETOUT, PI, FIXFLU, 100.0)

;

COVAL (JETOUT , Wl , ONLYMS ,500.0); COVAL (JETOUT , HI , ONLYMS

,

200000.0)" specifies a 100 kg/sec, steady-state, fixed-flux

mass source. The mass source, named JETOUT, begins at the

low faces of the cells IX=1, IY=5, and IZ=8 and ends at

IX=1, IY=6, and IZ=8. The mass source has a Z direction

velocity of 500 m/sec and an enthalpy of 200,000 J/kg. The

COVAL coefficient "ONLYMS" specifies that only convection

flow effects are influential in the transport of enthalpy

from the cell faces to the cell centers. That is,

diffusive effects are zero. Appendix 2 of the PHOENICS

User's Manual (Ref. 5) lists the various "TYPES",

19

"COEFFICIENTS", and "VALUES" that may be used with the

combination " PATCH-COVAL" statements.

G. INITIAL CONDITIONS

In order to obtain the solution of a steady state

problem, PHOENICS starts the iterative solution with an

initial field of the dependent variables. The default

initial fields for all dependent variables is zero over the

entire physical domain. However, convergence to the true

solution can be speeded up by the user specifying initial

field conditions via "FIINIT" (Field Initialization)

statements over the entire operational domain or

"PATCH-INIT" statements over subdomains of the system. For

example "FIINIT (HI) =AMOUNT" initialize a first phase

enthalpy field to a user-defined value "AMOUNT".

"PATCH (GASIN,INIVAL,XF, XL, YF,YL,ZF,ZL,TF,TL) ; INIT (GASIN, PI

,

COEFFICIENT, VALUE)" initializes a first phase pressure

field for the user-defined PATCH "GASIN". XF,XL, YF, YL, ZF,

and ZL define the geometric region of the PATCH called

"GASIN".

H. MAXIMUM/MINIMUM VALUES

At the beginning of a flow simulation problem iterative

process, a poorly defined dependent variable field value

may have an adverse affect on problem convergence. At

times, dependent variables "STRAY" outside of a physically

meaningful range and cause numerical divergence. To help

20

minimize divergence of the solution PHOENICS utilizes the

"VARMIN" and VARMAX" commands. These commands are used to

set upper and lower bounds on any dependent variables.

11VARMIN" (VI )=SLOW; VARMAX (W1)=FAST" sets a lower limit of

"SLOW" to VI and an upper limit of "FAST" to Wl.

I. UNDER-RELAXATION FACTORS

A feature of PHOENICS which greatly assists problem

convergence is the application of "UNDER-RELAXATION"

factors to flow simulation dependent variables. This

practice is most useful on an operational domain comprised

of ill-proportioned cells (very large cells adjacent to

very small cells) . During program execution, EARTH'S

dependent variable correction equations may develop

enormously large coefficients between adjacent cells. The

coefficient disparity often contributes to solution

divergence. With selective "UNDER-RELAXATION" applied to a

flow simulation program, PHOENICS introducers "FALSE-TIME-

STEP" values to select dependant variables thereby

preventing large dependent variable changes in magnitude

per sweep. The "FALSE-TIME-STEP" brings equation

coefficients closer together "LESS ABRUPTLY" which promotes

problem convergence. "UNDER-RELAXATION" for pressure,

velocity, and enthalpy components is frequently required

for steady state problems.

21

J. PROGRAM RUN PROCEDURES

The Denmark test facility model was analyzed on the

Naval Postgraduate School IBM-3 03 3 mainframe computer

system. Program run procedures involve interactive

terminal sessions and a batch submission. The necessary

flow simulation Ql program and Job Control Language (JCL)

programs reside in the User's mainframe storage area. All

flow simulation programs are submitted for execution by

means of "EXEC" (execute) and JCL files. The EXEC files

are activated by the keywords "C0PYQ1", "RUNSAT", and

"RUNEAR"

.

The C0PYQ1 EXEC file gueries the user as to the name

and file type of the flow simulation Ql program source

code. Afterwards the C0PYQ1 EXEC file stores the source

code and appropriate JCL in a temporary file. At this

point, the user must ensure the above transfer of data was

successful. This is accomplished through the user's

"VIRTUAL READER" file. An inspection of this file will

reveal various condition codes which indicate the status of

data transfer. Figure C.6 is an example of C0PYQ1 EXEC and

JCL files.

The "RUNSAT" EXEC file extracts from the user's

mainframe storage area JCL which enables a Ql program to

EARTH program communications link. This JCL is also stored

in a temporary file. Again a virtual reader file

inspection must be made to ensure that a successful data

22

transfer was achieved. Figures C.7 and C.8 are examples of

RUNSAT EXEC and JCL files.

Finally after successful C0PYQ1 and RUNSAT data

transfers, the flow simulation problem is ready for

execution. The "RUNEAR" EXEC file is called, Necessary

mainframe storage is allocated and the PHOENICS system is

activated. Figure C.9 is an example of RUNEAR EXEC and JCL

files. Upon program completion, PHOENICS output is sent to

the user's virtual reader file. After the PHOENICS output

is analyzed, the user may discard the information or

utilize a PHOENICS restart which allows the problem to

continue from where it last ended. Upon completion of a

PHOENICS run, output is stored on disk file "DF09" . To

access this file and to continue the problem the PHOENICS

code "RESTRT(A,B, . . ..,Z) " must be utilized in the Ql

program. "A,B,...,Z" represent the dependent variables

which are to continue from their last value when the

program ended. If the user desires all dependent variables

to restart from their last values then "RESTRT(ALL) " can be

used in the Ql program.

23

IV. MODELING THE DENMARK TEST FACILITY

A. MODEL DESCRIPTION

The Denmark test facility model utilizes a Cartesian

grid arrangement. Figure CIO is a schematic diagram of

the test facility in the Y-Z pane (side view). Figure C.ll

is the X-Z plane (top view) representation. The PHOENICS

code allows for a plane of symmetry. For the Denmark test

facility model the vertical Y-Z plane is one of symmetry.

Therefore, in Figure C.ll only half of the Denmark test

facility is represented, In this figure the jet engine is

slightly off-of-center from the Z axis for clarity only.

To facilitate the Denmark test facility model geometry

specifications, the system domain was divided into user

defined zones. Each zone comprises a particular section of

the Denmark test facility model. For example in Figure

C.12, "YLBL1" is a user defined variable which specified

the length of the first zone in the Y direction. This

particular zone represents the length in the Y direction

from the ground or floor of the Denmark test facility up

2.0 meters. "ZLEXT2" represents the length in the Z

direction of the atmosphere behind the test facility, and

so on. Figure C.12 is a schematic diagram of the system

domain zones which make up the vertical Y-Z plane while

C.13 illustrates the zones in the horizontal X-Z plane.

24

The zone concept has proven to be very flexible. The

number of cells in each zone may be specified by a user

defined variable. For example, "XNCBL1" specifies the

number of cells in the X direction for the length of

operational domain "XLBL1". "ZNCEX2" specifies the number

of cells in the Z direction for the length of operational

domain "ZLEXT2" and so on. Grid refinement for a

particular zone can be accomplished without any difficulty

by changing one variable in the Ql code. Figure C.14 is

the method-of-pairs coding sequence which specifies the

operational domain zones and numbers of cells used in the

Denmark test facility model. Figure C.15 is an example of

the EARTH output for the Ql code in Appendix A.

Program run time, program cost and EARTH output are

directly affected by the number of cells in the model of

the physical domain. By increasing the number of cells in

the X, Y, or Z direction zones, the EARTH program requires

more "SLAB-WISE" Computations thereby increasing computer

CPU requirements and costs. By increasing the number of

cells in the X or Y directions (i.e., NX or NY), the number

of cells and therefore the number of calculations is

increased. For example for a fixed NY, SAY 16, an increase

of 1 cell in the X direction will result in 7 (number of

dependent variables) times 16 = 102 additional equations

(and unknowns) . An increase of an additional cell in the Z

25

direction will result in 7 times NX times NY additional

equations. For example for NX=9 and NY=16, increasing NZ

from 28 to 29 will result in an additional 1,008 equations.

Therefore, deciding to use a "COURSE" or "FINE" model of

the physical domain is determined by the user's time and

financial constraints and the desired information from the

flow simulation program. The Denmark test facility model

has NX=9, NY=16 and NZ=28 for a grand total of 4,032 cells.

Since each cell has 7 dependent variables, 28,224 linear

algebraic equations must be solved iteratively to achieve

problem convergence. This is a big job even for an IBM

mainframe computer.

For the purpose of this research, the Denmark test

facility was modeled with a "COARSE" grid with the intent

of achieving problem convergence prior to using a "fine"

grid. Due to time constaints only one grid was used in

this research. Therefore, problem convergence could not be

identified as "GRID INDEPENDENT".

Although the Denmark test facility model grid is

considered "COARSE", many of the cells vary in size. The

number and size of cells for a particular region of the

grid was chosen based upon the expected activity in a

region. For example, at the primary air inlet, one would

expect primary cooling air to be entering at a relatively

low velocity and in a laminar and uniform flow. Then as

the primary air approaches the jet engine intake, fluid

26

velocities should be increasing in magnitude and changing

in direction. At the outlet of the jet engine there exists

a very hot and a very fast fluid flow mixing with entrained

primary cooling air. In this particular region with a lot

or activity, a less "COARSE" grid is more desirable in

order to incorporate the mixing process into the model. As

the exhaust gas enters the augmentor tube it mixes with the

cooler entrained secondary air. Again, a less "COARSE"

grid is necessary to better analyze the activity involved.

Figure C.16 is a schematic diagram of the system domain

grid for the X-Z plane while Figure C.17 represents the Y-Z

plane. The two figures illustrate a less "COARSE" grid

arrangement at the jet engine exhaust, augmentor tube

inlet, and secondary air inlet. Again, grid refinement for

any physical domain zone is accomplished by changing one

user defined variable in the Ql code.

Although the Denmark test facility was modeled as a

three-dimensional structure. The body fitted coordinate

option of PHOENICS was not utilized. As such, the

cylindrical jet engine, the augmentor tube, and the exhaust

stack turning vanes were modeled as rectangular cubes. The

jet engine was specified as a solid block with a hot mass

source at one end and a mass sink at the other end. The

jet engine was modeled with CONPOR and PATCH-COVAL

statements.

27

The Denmark test facility walls, floor, and ceilings

were modeled utilizing CONPOR and PATCH-COVAL statements.

The CONPOR statements were given a zero porosity value

thereby preventing mass transfer across any solid

structure. PATCH-COVAL statements were necessary for the

walls, floor, and ceilings in order to introduce

appropriate friction and set fluid velocity components to

zero magnitude at the structure surfaces.

B. MODEL BOUNDARY CONDITIONS AND TURBULENCE MODELS

Boundary conditions for the Denmark test facility

openings to the atmosphere were specified with PATCH-COVAL

statements. Ambient pressure was set to 101,325 Pascals

while ambient temperature was set to 295 K.

To incorporate turbulence into the flow simulation

problem, this research utilized the PHOENICS K-E turbulence

model. The K-E model introduces the KE (turbulence kinetic

energy) and EP (kinetic energy dissipation rate) dependent

variables into the problem. Turbulence modeling is not an

exact science and the choice of the K-E model for this

research was arbitrary. The PHOENICS user's manual

(Ref. 5) explains in detail the K-E turbulence model and

three other turbulence models available to the PHOENICS

user.

Readers may refer to Appendix A, the annotated Ql code,

which explains in detail the user defined variables for the

28

Denmark test facility model. Columns 1 and 2 are reserved

for the beginning of executable statements, while non-

executable statements (comments) begin in column 3 or

beyond.

29

V. ANALYSIS OF RESULTS

A. OBTAINING A FINAL SOLUTION

The original purpose of this research was to computer

model the Royal Danish Air Force Gas Turbine Test Facility

using the PHOENICS code. The computer model would then be

used to compare field data obtained from the test facility

with computer generated pressures, temperatures, and

velocities. If the computer generated output compared well

with the field data, one might suggest that the computer

model was successful. However, if field data from a test

facility was non-existent or perhaps very limited how then

could the success of a computer model be measured?

The field data from the Denmark test facility was

limited in scope. Besides the mass flow described in

Chapter II, the only other field data available are the

test bay pressure and the velocity and temperature of the

engine exhaust at one point in the augmentor tube and at

one point in the exhaust stack. Since the field data from

the Denmark test facility was limited, a comprehensive

comparison of field data with numerical results was not

possible. To investigate the EARTH output (numerical

results) and conclude that the numerical results were

representative of the test facility, this study examined

the EARTH output from three viewpoints: common sense

30

approach, conservation equation balances, and problem

convergence.

B. COMMON SENSE APPROACH

The Denmark test facility was modeled with five major

regions or zones. Within each zone a common sense approach

to what one would expect the gas pressure, temperature, and

velocity conditions to be was taken. The five major model

zones are: primary air inlet, test bay, secondary air

inlet, augmentor tube, and exhaust stack. The EARTH output

presented in Appendix B is the numerical results of only 5

slabs in the major model zones.

1. Primary Air Inlet

The primary air inlet is comprised of the following

cells: IX=1 to IX=8, IY=1 to IY=12 , and IZ=2. Cool ambient

air (295 K) is drawn into the test facility through the

primary air inlet (test facility doors) . Pressure drops at

the test facility doors were very small with a maximum drop

of about 12 Pascals. Air flow through the primary air

inlet was predominantly in the Z-direction (W) . Velocities

ranged from 1 to 2 m/sec with an average of about 1.7

m/sec. The horizontal X-direction velocity (U) and the

vertical Y-direction velocity (V) components were

negligible.

With an average gas density of about 1.2 kg/m3 at

the test facility doors, a primary air mass flow rate of

31

about 13 5 kg/sec was calculated. Recall from chapter IV

that the Ql program modeled only one half of the test

facility due to the Y-Z plane of symmetry. Therefore, the

135 kg/sec primary air mass flow rate is for one half of

the structure. The calculated primary air mass flow rate

for the entire structure would be about 270 kg/sec. Of

this amount, about 170 kg/sec would be primary cooling air

and the remaining 100 kg/sec flows through the engine.

From this point on, references to mass flow rates will be

for the entire test facility. The temperature at the test

facility doors remained at about 295 K. At the test

facility doors, one would not expect much activity and a

laminar flow. The KE and EP turbulence dependant variables

were negligible which indicated laminar flow.

2 . Test Bay

The test bay comprises cells IX=1 to IX=8, IY=1 to

IY=12, and IZ=2 to IZ=9. The jet engine which was modeled

as a 2000 K, 100 kg/sec sink-source is located at cells

IX=1, IY=5 to IY=6, and IZ=6 to IZ=7. At 2000 K, the

density of the engine exhaust gas was 0.18 kg/m . The jet

engine provides the excitation which draws ambient air in

through the primary air inlet, entrains primary cooling air

into the augmentor tube from the test bay and entrains

secondary cooling air into the augmentor tube from the

secondary air inlets. As primary air moved through the

test bay from the primary air inlet to the sink side of the

32

jet engine, its pressure and velocity changed. At the two

cells (IX=1, IY=5 to IY=6, and IZ=5) before the engine

inlet, about 1.5 meters upstream of the inlet, primary air

pressure dropped about 4 Pascals. The primary air W-

velocity component was about 3 m/sec at IZ=4, about 3

meters upstream of the engine inlet. The horizontal U-

velocity component was about -4.5 m/sec which indicated

that air was being drawn into the engine from the side

walls of the test bay. The vertical V-velocity component

was about -4 m/sec above the engine and about 4 m/sec below

the engine. This indicated that air was being drawn down

from the test bay ceiling into the engine and at the same

time being drawn up from the test bay floor. The turbulent

parameters KE and EP were very small indicating laminar

behavior at the engine inlet. The temperature at the

engine inlet remained at about 295 K.

At the discharge side of the engine (cells IX=1,

IY=5 to IY=6, and IZ=8) , significant activity was observed.

The pressure increased about 2100 Pascals. In adjacent

cells above/below and longside the engine at IZ=8, the

pressure dropped about 410 Pascals. The pressure

difference among the cells caused an expanding or

diverging effect if the jet engine exhaust gas. The U-

velocity component of the gas was about 3 m/sec while the

V-velocity component was about 50 m/sec. The jet engine

exhaust gas expanded out towards the rear wall of the test

33

facility as opposed to going directly into the augmentor

tube. However, due to the large magnitude of the W-

velocity component, about 43 m/sec, the resultant

direction of the engine exhaust was primarily into the

augmentor tube. Hot, fast moving gas at the engine outlet

mixed with the cool, slow moving entrained primary cooling

air. Due to this mixing, small turbulence resulted. this

premise is supported by the magnitude of the KE and EP

parameters in the region. KE had a maximum value of about

110 J/kg, while EP had a maximum value of about 5400

J/kg/sec. Due to this mixing of engine exhaust and primary

cooling air, over a distance of about 1.5 meters, the

exhaust gas was cooled from 2000 K to about 1830 K prior to

entering the augmentor tube (IZ=10) . Over the same 1.5

meter distance, the exhaust gas W-velocity component

decreased from about 430 m/sec to about 400 m/sec.

The investigation of the test bay was localized to

a small region around the jet engine. For the most part

the activity in the rest of the test bay was uneventful

(i.e. no turbulence and insignificant pressure,

temperature, or velocity changes)

.

The above observations in the test bay and at the

inlet and outlet ends of the jet engine are realistic. One

would expect primary air velocity components and pressure

to change somewhat prior to going into the engine and more

significantly at the engine outlet. Additionally, due to

34

the primary air being drawn into the engine a low pressure

area at the inlet makes good sense. While at the outlet

side of the engine a high pressure is expected. At the

engine outlet one would expect that the hot, fast engine

exhaust colliding and mixing with the cool, slow entrained

primary cooling air would result in some turbulence.

3 . Secondary Air Inlet

As was mentioned earlier in chapter II, the

secondary cooling air plays a significant role in the

operation of a jet engine test facility. The secondary

cooling air serves the purpose of providing additional cool

(ambient) air for mixing with the hot engine exhaust. For

the Denmark test facility the largest mass flow rate occurs

through the secondary air inlets. The test facility data

indicated a mass flow rate of about 340 kg/sec. In the

structure model, secondary cooling air enters the augmentor

tube at cells IX=5, IY=1 to IY=10, and IZ=10 to IZ=12. The

secondary cooling air had an average U-velocity component

of about -14 m/sec, which indicated that secondary cooling

air was being drawn into the augmentor tube from outside

the structure.

A maximum pressure drop of about 480 Pascals at the

secondary air inlet was in consonance with the relatively

high U-velocity component. With an average air density of

about 1.0 kg/m at the secondary air inlet, a mass flow

rate of about 420 kg/sec was calculated. Although the

35

secondary air inlet had a significant pressure drop and a

relatively large U-velocity component (about -14 m/sec) it

did not demonstrate turbulent behavior based upon the

relatively low KE and EP parameters. The temperature at

the secondary air inlet indicated a temperature rise of

about 15 K. The results showed that warm air from the

exhaust stack was flowing into the secondary air inlet

region.

With a primary cooling air mass flow rate of about

170 kg/sec and a secondary cooling air mass flow rate of

about 420 kg/sec, an Augmentation Ratio of about 5.9:1 was

calculated.

4 . Aucrmentor Tube

Three regions of the augmentor tube were chosen for

investigation: The region IZ=10 to IZ=16, the slab IZ=20,

and the slab IZ=22. At the beginning of the augmentor

tube, IZ=10 to IZ=16, a large mass of primary and secondary

cooling air collided and mixed with the hot, fast exhaust

gas. As a result, significant turbulence occurred. A

maximum KE value of about 7,100 J/kg was observed while

maximum EP was about 500,000 J/kg/sec. In the 8.5 meters

that the engine exhaust traveled, it cooled from 2 000 K to

about 920 K. The engine exhaust W-velocity component

decreased from about 43 m/sec to about 12 5 m/sec. The U

and V-velocity components were considered negligible.

Figures C.18 and C.19 are PHOENICS enthalpy (HI) and

36

velocity (Wl) profiles for the cells IX=1, IY=1 to IY=10,

and IZ=16. The reader is reminded at this point that an

enthalpy value divided by a specific heat value of about

1000 J/ (kg K) will give a good temperature approximation

within a cell. The profiles indicated minimum temperature

and W-velocity values at the bottom (IY=1) and top (IY=10)

of the augmentor tube and maximum temperature and W-

velocity values at the centerline of the augmentor tube.

These temperature and W-velocity distributions make good

sense. Since the location IY=5 is at the height of the

engine outlet, one would expect the engine exhaust to be

hotter and to be moving faster here than at the top/bottom

of the augmentor tube. Figures C.2 and C.21 are

temperature and W-velocity profiles for the cells at IX=1

to IX=5, IY=5, and IZ=16. Although these profiles are at

the same slab location (IZ=16) as figures C.18 and C.19,

the examination of the variables is from the center of the

augmentor tube to the side wall. These distributions

indicated maximum values of the variables occurred at the

center of the augmentor tube and minimum values at the side

walls. These profiles also make good sense. In the cells

at the augmentor wall (IX=5, IY=1 to IY=10, and IZ=16) , the

secondary cooling air entering the augmentor tube has only

mixed with the engine exhaust for about a 3 meter distance

down the augmentor tube.

37

At augmentor tube location IZ=20 (about 22 meters

downstream of the engine outlet) , the total mass flow was

examined. The W-velocity component ranged from about 2 5

m/sec to 75 m/sec with an average of about 45 m/sec. The U

and V-velocity components were considered to be negligible.

With an average gas density of about 0.6 kg/m3, the total

mass flow rate was about 7 00 kg/sec. At augmentor tube

location IZ=20, there was still some turbulence, which

indicated continued mixing of the primary/secondary cooling

air and the engine exhaust. The maximum KE value was about

740 J/kg while EP maximum was about 10,400 J/kg/sec. The

temperature ranged from about 52 K to about 63 5 K with an

average of about 550 K. Figures C.22 and C.23 are

temperature and W-velocity profiles for the cells at IX=1,

IY=1 to IY=10, and IZ=20. Figures C.24 and C.25 are

temperature and W-velocity profiles for the cells at IX=1

to IX=5, IY=5, and IZ=20. A more uniform distribution of

temperature and W-velocity was observed across the slab at

IZ=20 than at slab IZ=16. This is reasonable since the

total mass of primary and secondary cooling air and engine

exhaust has mixed for a distance of about 22 meters

downstream of the engine outlet.

In the augmentor tube/exhaust stack transition

region (IZ=22) , the test facility field data indicated the

W-velocity component on a centerline with the jet engine

was about 60 m/sec and the average temperature was about

38

650 to 675 K. The numerical results indicated a W-velocity

component of about 63 m/sec and a temperature of about

615 K. In a distance of about 4 meters from IZ=20 to

IZ=2 2, turbulence decreased by about 50 percent. KE was

about 4 00 J/kg while EP was about 4,500 J/kg/sec.

5. Exhaust Stack

Field data from the Denmark test facility indicated

a temperature rise of about 20 K from the bottom of the

exhaust stack to the area under the exhaust stack baffle

material. In the numerical model a temperature drop of

about 50 K was observed. The Denmark test facility was

modeled without baffle material at the top of the stack.

Gas velocities at the top of the computer model stack were

for the most part in the V-direction. The V-velocity

ranged from about 10 to 4 5 m/sec with an average of about

2 m/sec. Turbulence at the top of the exhaust stack was

considered to be negligible. Average temperature at the

top of the exhaust stack was about 550 K. Figures C.26,

C.27, C.28, and C.29 are temperature and V-velocity

profiles for the top (IY=13) of the exhaust stack. Figures

C.26 and C.27 are for the cells IX=1, IY=13, and IZ=21 to

IZ=26 (along the Z axis). Figure C.26 indicated highest

temperature values towards the rear (IZ=2 5) of the exhaust

stack. Additionally, Figure C.27 indicated that the

V-velocity fluctuated (low to high to low ...) from IZ=21

to IZ=2 6. It is suggested that the manner in which the

39

turning vanes were computer modeled caused a lack of

uniformity in the temperature and V-velocity distribution

for this stack region.

Figures C.28 and C.29 are the temperature and V-

velocity distributions for the cells at IX=1 to IX=5,

IY=13, and IZ=2 3 (from the center of the exhaust stack out

to the side wall) . These figures indicated fairly uniform

temperature and V-velocity profiles throughout the cells in

this region.

C. COMPUTER DATA AND FIELD DATA COMPARISON

The difference between field data results and numerical

results can be attributed to several things: baffle

material (not included in the numerical model) , turning

vanes (crudely modeled as rectangular cubes) , turbulence

model (modeling is not an exact science) , and model grid

(grid independence not verified)

.

The computer model total mass flow rate of about 700

kg/sec is about 15 percent larger than the 600 kg/sec total

mass flow rate of the Denmark test facility. It is

suggested that not including the baffle material, in the

computer model primary and secondary air inlets and the

exhaust stack, resulted in larger numerical mass flow rates

than the test facility mass flow rates. Test facility

baffle information was not available for this research.

40

Field data indicated a maximum pressure drop in the

test bay of about 500 Pascals. The computer model

calculated a maximum pressure drop of about 410 Pascals in

the cells adjacent to the jet engine outlet.

As was mentioned earlier, the exhaust gas temperature

and W-velocity component in the augmentor tube/exhaust

stack transition region compared very well with the field

data.

D. CONSERVATION EQUATION BALANCES

The PHOENICS output code enables the investigator to

determine the degree conservation of mass has been

achieved. The PHOENICS output symbol for a mass flow

source is "Rl". By an algebraic summing of the mass flow

sources, a conservation of mass flow calculation can be

made. For a total accounting of all the mass flow sources

in a computer model, the algebraic sum of the sources

should be zero. For the Denmark test facility this sum was

equal to 0.02 kg/sec. If this amount is compared to the

100 kg/sec mass flow through the jet engine there is a 0.02

percent error. Compared to the 700 kg/sec mass flow

calculated for the augmentor tube the percent of error is

reduced to 0.003. Based on this analysis, a mass balance

or a continuity of flow exists in the Denmark test facility

41

model. A mass balance or a continuity of flow is a

necessary but not sufficient condition for problem

convergence.

E . CONVERGENCE

Chapter III described the iterative process which

adjusts the values of the dependent variables during the

solution process. During the process, imbalances occurred

between the left and right hand side of the dependent

variable discretized algebraic equations. These imbalances

are called residuals. Problem convergence would be

obtained when all residuals were zero (i.e. the dependent

variable discretized algebraic equations were in balance)

.

The residual goes to zero as the number of sweeps goes to

infinity. With numerical solutions, users must employ a

variety of methods to determine problem convergence since

residuals can not decrease to zero, as a practical matter.

With the PHOENICS output (Appendix B) , this research

utilized a local and a global analysis of the dependent

variables to determine problem convergence. A local or

"spot value" analysis can be accomplished with the PHOENICS

output by designating cells to be monitored. Since the

test facility field data referenced the exhaust gas

temperature and velocity for a location in the augmentor

tube/exhaust stack transition region, the computer model

spot checked the dependent variable values at the same

42

location (the cell at IX=1, IY=5, and IX=22) . From the

initial program run to the final sweep (about 10,000), the

spot values were closely monitored and compared. Local

convergence at this cell occurred when little or no change

in the dependent variable values was observed from sweep to

sweep. Local or spot value convergence of dependent

variables for one cell is a necessary but not sufficient

condition for problem convergence. For this reason, the

results at "ALL" cells were spot checked during the

solution process.

During the problem solution process, the PHOENICS code

sums the dependent variable whole-field residuals. An

examination of the whole-field sums provides a means of

global investigation to determine problem convergence. If

whole-field residuals decrease towards zero, with

increasing iterations, problem convergence is suggested.

However, if the residuals increase, with increasing

iterations, problem divergence is occurring and some

adjustment of the PHOENICS relaxation parameters is

required. Global analysis is also accomplished by

examination of the energy balance of the system. The

dependent energy variable enthalpy (HI) residual is first

divided by 1,000,000. This result is then divided by the

absolute value of the sum of the enthalpy (HI) net sources.

If the quotient decreases to less than about 0.05 (5

percent error) , problem convergence is suggested. If the

43

quotient continues to increase, problem divergence is

occuring and PHOENICS relaxation adjustment is again

required.

F. SUMMARY

Although there was limited test facility field data to

compare with numerical results, it is suggested that the

computer modeling of the Denmark gas turbine test facility

with PHOENICS code was successful. The field test data

compared well with the numerical results. During the

common sense examination, the conditions that existed in

the five major regions of investigation made good sense and

were indicative of what one might expect in a gas turbine

test facility. The total mass flow continuity check

indicated less than 0.003 percent error. Finally, local

and global convergence was indicated. A system energy

balance was within a 5 percent error.

44

VI. RECOMMENDATIONS

A. INTRODUCTION

It is believed the PHOENICS code is a useful tool for

the solution of gas turbine flow simulation problems.

However, since the Denmark test facility has not "FINELY"

modeled the following computer model enhancements are

suggested: BFC, PHOTON, alternate turbulence models, grid

refinement, and baffle modeling.

B. BFC

Body fitted coordinates (BFC) are necessary to

incorporate the cylindrical and curved surfaces of the jet

engine, augmentor tube, and turning vanes. With the proper

geometric shapes in the test facility model, mass flow in

the augmentor tube inlet, the secondary air inlets, and the

exhaust stack will be more representative of the actual

test facility.

C

.

PHOTON

The implementation of the PHOENICS PHOTON option will

greatly enhance numerical results investigation. A two or

three dimensional representation of a dependent variable

field is much more useful than a cell by cell examination

of numbers.

45

D. ALTERNATE TURBULENCE MODELS

One or more of the alternate PHOENICS turbulence models

should be implemented and investigated. Since it was

suggested that turbulence modeling is not an exact science,

verifying the effect of the turbulence model on the

solution is crucial. It may be that the turbulence model

selected does not greatly effect the solution.

E. GRID REFINEMENT

Increasing the number of cells (grid refinement) in the

system will enhance the problem solution process. During

the slab-sweep iterative process, the dependent variable

discretized algebraic equations will be solved in a "LESS

ABRUPT 11 manner which will promote problem convergence.

Grid refinement is also necessary to verify the solution is

grid independent.

F. BAFFLE MODELING

Finally, by utilizing additional PHOENICS CONPOR

commands, baffle material could be modeled into the

primary/secondary air inlets and the exhaust stack. By

experimenting with different values of porosity, the total

mass flow rate of the computer model could more closely

represent the total mass flow rate of the actual test

facility.

46

APPENDIX A

Ql CODE

47

TALK=F>RUN<1,1)

V •J \* \S \, \J \J \S U \J •/ W \J -J \J W \J \J \1 -^ y H LI y, W .J -. _, ^ y 'J -^ M y -^- '"* "~ " if 11 w W •- \f If J .J -I -W -J ! U W ! J LI y tfl/ -. ^J .J <J 11 ^J -_f l. ...

* ** DENMARK JET-ENGINE TEST FACILITY COMPUTER MODEL *X. •^ V^ VV VW V V .'j: ,'^ ' f M *"" M •"" " M .X. V V tf V M W UVV V W ; if n- •< -j xj 1.1 •>< ^ y ^ y y ^ y y y i^-j-if-ûwwuwwij v u- vf v> vi w ^ w yJtAAAAÂAAAAA AÂJTAAAAAAAAAAAAAAAAAAAAÂAAAAAAAAAAAAAAAAAAAAA A W A A A W A A ^

*

*

THE *if

**

*

** XLBL1* XLMID1* XLMID2* XLMID3# XLBL2* XLBL3* XLEXT1* XLEXT2* XNCBL1* XNCMD1* XNCMD2* XNCMD3* XNCBL2* XNCBL3* XNCEX1* XNCEX2* YLMID* YLBL1* YLBL2* YLEXT1# YLEXT2* YLBL3* YLEXT3# YLBL<+* YNCMID* YNCBL1* YNCBL2* YNCEX1* YNCEX2* YNCBL3* YNCEX3# YNCBL4* ZLEXT1* ZLINT1* ZLIMT2* ZLINT3* ZLINT4* ZLINT5* ZLINT6* ZLEXT2* ZNCEX1* ZNCIN1* ZNCIN2* ZNCIN3* ZNCIN4

NON-PHOENICS USER-DEFINED VARIABLES

THE FOLLOWING VARIABLES ARE USED TO DESCRIBEPHYSICAL CHARACTERISTICS OF THE DENMARK TESTFACILITY. THE FIRST LETTER OF THE VARIABLESPECIFIES THE DIRECTION IN THE COORDINATESYSTEM.THE FOLLOWING CONVENTIONS ARE USED TO DESCRIBEA PARTICULAR ZONE OF THE MODEL:

L LENGTH IN A COORDINATE DIRECTIONMID MIDDLE OF SAY THE AUGMENTOR TUBEBL BOUNDARY LAYEREXT EXTERIOR ZONE OF STRUCTURENC NUMBER OF CELLS IN A DIRECTIONINT INTERNAL ZONE OF STRUCTURE

EXAMPLE: XLBL1

YNCEX2

ZLINTS

THE LENGTH OF THE FIRSTZONE IN THE X DIRECTION.

THE NUMBER OF CELLS FOR THESECOND EXTERNAL ZONE IN THEDIRECTION.

THE LENGTH OF THE FIFTHINTERNAL ZONE IN THE ZDIRECTION.

*

****

*

*

****

*

**

*

**

*

A 8

* ZNCINS ** ZNCIN6 ** ZNCEX2 ** ** ** TMPJET TEMPERATURE OF JET EXHAUST (K) ** CPJET SPECIFIC HEAT OF JET EXHAUST ( J/KG*K ) ** PRSJET PRESSURE OF JET EXHAUST ( N/M**2 ) ** GASCON GAS CONSTANT OF JET EXHAUST I N*M/KG*K ) ** MASJET MASS FLOW RATE OF JET EXHAUST (KG/SEC) ** VELJET VELOCITY OF JET EXHAUST (M/SEC) ** RHOJET DENSITY OF JET EXHAUST ( KG/M**3 ) ** ** TMPAMB AMBIENT AIR TEMPERATURE (K) ** PRSAMB AMBIENT AIR PRESSURE ( N/M**2 ) ** CPAMB SPECIFIC HEAT AMBIENT AIR ( J/KG*K ) ** *

"K A A^ A A A A A A K K A AW A^ K AW A A A A A W WW A*W AW A A A A A A A A A A A A A A A A A A A A A? A A A A. A A A A A A A A A A A

* ** ** ************************************************************************ÂAWAW*W*^ÂA*AAÂA^*^RAAffWA^^ÂAAAAAA"A^ÂAAAÂAAAWAAWK*A*AAAAWWAAA* ** VARIABLE DECLARATIONS *

* *7tAW^ÂAÂ^W^^TT^WÂ'WÂ^WAÂ^WAAAAA^*AAAAWW^^WA«!WÂWWW^WW^^WAKW^rAAAAWAWWW

* *

* PHOENICS ALLOWS <+5 USER DEFINED REAL-NUMBER VARIABLES ** *

REAL! XLBL1 ,XLMID1 ,XLMID2 ,XLMID3 ,XLBL2 ,XLBL3 ,XLEXT1 ,XLEXT2

)

REAL(YLMID,YLBL1,YLBL2,YLEXT1,YLEXT2,YLBL3,YLEXT3,YLBL<+)REAL! ZLEXT1 ,2LINT1 ,ZLINT2 ,ZLINT3 ,ZLINT4 ,ZLINT5 ,ZLINT6 ,ZLEXT2

)

REAL! TMPJET, CPJET, PRSJET, GASCON, MASJET, VELJET, RHOJET)REAL! TMPAMB, PRSAMB, CPAM3,DELT, FACT)REAL(KEINJ,EPINJ,KEINA,EPINA)

* ** PHOENICS ALLOWS 45 USER DEFINED INTEGER VARIABLES *

* *

INTEGER! XNCBL1 ,XNCMD1 ,XNCMD2 ,XNCMD3 ,XNCBL2 ,XNCBL3 ,XNCEX1 ,XNCEX2 )

INTEGER! YNCMID ,YNCBL1 , YNCBL2 , YNCEX1 , YNCEX2 , YNCBL3 , YNCEX3 , YNCBL<+ )

INTEGER! ZNCEX1 ,ZNCIN1 ,ZNCIN2 ,ZNCIN3 ,ZNCIN4 , ZNCINS ,ZNCIN6 ,ZNCEX2

)

* *

* *

* ********************************* X X X X X* X X X X X X X* X X X X x*********************************** X X X X X****xxxxxxxxxxxxxxxx************************** *

* INITIALIZATION OF USER-DEFINED VARIABLES ** *\j -.- -j * -w -j u w w -a w -; ,^, v y -, jj j a .y, y, .y, „y ,y. ^ ,y y, ,m. ,A y. y y y y y y y y w y -• y y i m V ' V '1 M Ml j. a W 'ml U M' ¥ '! V- J. .fc * ^ y * M «

* *

49

X DIRECTION LENGTHS (METERS)

XLBL1=0.5XLMID1=0.5XLMID2=0.5XLMID3=0.5XLBL2=0.5XLBL3=5.4XLEXT1=2.0

*

XNCBL1=1XNCMD1=1XNCMD2=1XNCMD3=1XNCBL2=1XNCBL3=3XNCEX1=1

*

*

*

YLBL1=2.0YLMID=1.0YLBL2=2.0YLEXT1=3.8SYLEXT2=2.1SYLBL3=6.0

*

YNCBL1=4YNCNIO=2YNCBL2=4YNCEX1=2YNCEX2=1YNCBL3=3

*

ZLEXT1=2.0ZLINT1=23.5ZLINT2=3.2ZLINT3=1.5ZLINT4=6.0ZLINT5=16.3ZLINT6=8.<+ZLEXT2=4.0

*

#

ZNCEX1=1ZNCIN1=5ZNCIN2=1ZNCIN3=2

NUMBER OF CELLS IN X DIRECTION

Y DIRECTION LENGTHS (METERS)

NUMBER OF CELLS IN THE Y DIRECTION

Z DIRECTION LENGTHS (METERS)

NUMBER OF CELLS IN THE Z DIRECTION

50

ZNCIN4=6ZNCIN5=5ZMCIN6=6ZNCEX2=2

N***. W U M y. K Mi k V ;i ^ ,W .'J

- "^ ^ ^- M "tf M ^ V V M M M, M , ^ a ~U d "W ^ '* U a' V ^ ^ 'tt a" fr '*." ~M ^ fc ^ U J ^ M, kl ' "» " \f V V ^' " B. M J M M M M M i

**-***-*** X X X X********tt********* X X X X X**"X-*"X-******* X X X X***** XX K XX******** ** GROUP 1. RUN TITLE AND OTHER PRELIMINARIES ** *

TEXTl DENMARK JET-ENGINE TEST FACILITY MODEL)

* *., .a y ^ M s w .. -^ -.. ,,- -^ -^ „ u- ^ ^ ., ^ a

- -., w , -^ M ^ M , M w ^ -^ .. M -^ ,, w j . -^ M , a < W tf fc . m ,a ,•* '' ^ m. 'A '» y' ¥ m V V a ¥ V tt'

**H******jH******"*^******-**-**-**tt-»r*X X X X X X *"X-****"******"X-* X XXX tt*-******-****

GROUP 2. TRANSCIENCE* TIME -STEP SPECIFICATION

DEFAULT TAKEN: STEADY STATE

tt***tt**********-X-**-»*-X-X"»******** X X X X»»*»*»»**»»<»*» » X X X********-»***-**

* *

* GROUP 3. X-DIRECTION GRID SPECIFICATION *

x- *

* *

* NX = THE NUMBER OF CELLS IN THE X DIRECTION (INTEGER) *x- XULAST = DISTANCE IN THE X DIRECTION (METERS) ** *

NX=XNCBLlrXNCMDl+XNCMD2+XNCMD3+XNCBL2+XNCBL3+XNCEXl

XULAST=XL3L1+XLMID1+XLMID2+XLMID3+XLBL2+XLBL3+XLEXT1

THE METHOD-OF-PAIRS HAS BEEN USED TO DEFINE THE NUMBER *

AND SIZE OF CELLS. THE XFRACYFRAC, AND ZFRAC SPECIFY THE X,Y>*AND Z COORDINATES RESPECTIVELY. THE ODD INDEX SPECIFIES THE *

NUMBER OF CELLS IN A DIRECTION AND THE EVEN INDEX SPECIFIES THE*SIZE OF EACH CELL. THE NEGATIVE QUANTITY FOR THE FIRST ODD *

INDEX IN EACH GROUP IS THE RESERVED WORD WHICH SPECIFIES *

"METHOD-OF-PAIRS" **

XFRACI 2 )=XLBLl/( XNCBL1*XULAST )

XFRACt <t )=XLMIDl/( XNCMD1*XULAST

)

XFRACI 6 )=XLMID2/( XNCMD2*XULAST

)

XFRACt 8 )=XLMID3/( XNCMD3*XULAST

)

XFRAC( 10 )=XLBL2/( XNC3L2*XULAST )

XFRACI 12 )=XLBL3/( XNCBL3*XULAST

)

*

**

*

*

*

XFRACI 1)=-XNCBL1>XFRACI 3 )=XNCMD1>XFRACI 5 )=XNCMD2vXFRACI 7)=XNCMD3;XFRACI 9 )=XNCBL2>XFRACI ll)=XNCBL3j

51

XFRAC ( 13 ) =XNCEX1 > XFRAC ( 14 ) =XLEXTl/< XNCEX1*XULAST

)

M

A A A A .^ A A A A^ R ^ J17T^^TT^^ WR W.TH H71RR7TW W A K WTTWWAAA^^AAAA^^ A A H JI^K^I

#* GROUP 4. Y-DIRECTION GRID SPECIFICATION*A A A * ^^ T^ A A A A A A A ^ A 7TWAAAAAAAA 7T^7TAAAAAAAAAAAAAAA^^^^ AAA*

* NY = THE NUMBER OF CELLS IN THE Y DIRECTION (INTEGER)* YVLAST = DISTANCE IN THE Y DIRECTION (METERS)#

NY=YNCMID+YNCBL1+YNCBL2+YNCEX1+YNCEX2+YNCBL3YVLAST=YLMID+YLBL1+YLBL2+YLEXT1+YLEXT2+YLBL3

* METHOD OF PAIRS

YFRACl 2 )=YLBLl/( YNCBL1*YVLAST

)

YFRACl < )=YLMID/( YNCMID*YVLAST )

YFRACl 6 )=YLBL2/1 YNCBL2*YVLAST

)

YFRACl 8 )=YLEXTl/( YNCEX1*YVLAST

)

YFRACl 10 )=YLEXT2/(YNCEX2*YVLAST)YFRACl 12 )=YLBL3/( YNCBL3*YVLAST

)

YFRACl 1)=-YNCBL1>YFRACl 3 )=YNCMID;YFRACl 5 )=YNCBL2iYFRACl 7)=YNCEX1;YFRACl 9)=YNCEX2jYFRACl 11 )=YNCBL3>

* ** GROUP S. Z-DIRECTION GRID SPECIFICATION *

* NZ = THE NUMBER OF CELLS IN THE Z DIRECTION (INTEGER) ** ZWLAST = DISTANCE IN THE Z DIRECTION (METERS) *

NZ=ZNCEX1+ZNCIN1+ZNCIN2+ZNCIN3+ZNCIN<++ZNCIN5+ZNCIN6+ZNCEX2ZWLAST=ZLEXT1+ZLINT1+ZLINT2+ZLINT3+ZLINT4+ZLINT5+ZLINT6+ZLEXT2ZFRACI 1)=-ZNCEX1>ZFRACI 3 )=ZNCINljZFRACI 5 ) =ZNCIN2,ZFRACI 7)=ZNCIN3vZFRACI 9)=ZNCIN<t;ZFRACI 11)=ZNCIN5ZFRACI 13 )=ZNCIN6ZFRACI IS )=ZNCEX2

ZFRACI 2)=ZLEXT1/(ZNCEX1*ZHLAST)ZFRACI <+ )=ZLINTl/( ZNCIN1*ZWLAST )

ZFRAC I 6 ) =ZLINT2/( ZNCIN2*ZWLAST

)

ZFRACI 8 )=ZLINT3/( ZNCIN3*ZWLAST

)

ZFRACI 10)=ZLINT4/(ZNCIN<t*ZWLAST)ZFRACI 12 )=ZLINTS/( ZNCIN5*ZWLAST

)

ZFRACI 1<+)=ZLINT6/(ZNCIN6*ZWLAST)ZFRACI 16 )=ZLEXT2/( ZNCEX2*ZWLAST

)

*

*

* #* GROUP 6. BODY-FITTED COORDINATES OR GRID DIRECTION *

52

* ( NOT IN USE )

TXXXXX «^^7TR AHH H^ A^ W 7*^^^^ 7T^ "^^ ^"^ A A ^^ A A A ^^

*m (inAHAÂAAAAT^nww^ a r jiw^^ a a^^ fnnv>vinnnntmnv?CHinvivii a a ^ a a a 7HrT7nfX7TT

AAAAWAAjvnWAAÂAWWA"WW^WA WA1WWWWÂAA^W*AKA^WWAI AÂ;W.*A'A'W^^WWWRAÂ1 WA' *. R *. A AAA A A

* #* GROUP 7. VARIABLES STORED, SOLVED AND NAMED *

tf ¥ * tt Mi ¥ "¥ tt * ¥ ¥ M W ¥ 'k M 'If'< M * k' ^ ¥ V V V V *" W M V M UV'M, ^ -J'tJ-wvJ'>J^^'v '" ,^ ,<V^ ^^''-fvvfi-i'-i-f^-w\J' M i- ^ ^. V ~M U ^7T7TW^nnAAAAAAAAAAAÂAAAAAAAAAA 7TAA/\AAAAAAAAAA^/%«ÂAWAAAAAAAAAAAAAAAAA.W

SOLVE! P1,H1, Ul, VI, Wl)S0LUTN(P1,Y,Y,Y,N>N,N)STORE! RH01.TMP1)

* *AAAAAAW^^WAAAAAAAAWA^ÂWAAA A^ÂÂAÂ A A A W A A A A A 9ÂAAAAA.TAWAAHWW^^^ A A A A A?

¥ v ¥ v *• ¥ ¥ ¥. ¥ ¥ ¥ ¥ ¥ ¥ ¥ ¥ y y v ¥ ** ^ ¥ v v v * a ¥ w my i ' .m m ,^. j, ^ Hi ^ ,m > a ,a . j j ki - * y~ v : .. ,«. - -. - - ». — -- ------ -^ .j.

* *

* GROUP 8. TERMS (IN DIFFERENTIAL EQUATION) AND DEVICES ** *

WA'A^^^WWA^^WWWWWÂ'AA'A^Â A^^^^W*A A ^ A A A A A A A A A 'W A A A A W R K A A A A^^ W A A A A A A*WW^* ** DEFAULT TAKEN *

* *

* GROUP 9. PROPERTIES OF THE MEDIUM (OR MEDIA) ** *

TMP1A=TINYTMPAMB=29S.PR3AMB=0.CPAMB=1004.TMP1B=1.0/CPAMBTMP1=GRND2TMPJET=2000.CPJET=100^.PRSJET=0.GASC0N=287.RH01B=1. /GASCONMASJET=100.PRESS0=10132S.RHOJET=( PRESSO+PRSJET )/( GASCON^TMPJET )

VELJET=MASJET/RHOJETRH01=GRNDSENUL=1.0E-0SDRH1DP=GRN0STURMCD(KEMODL)

STORE (VIST)KEINJ=0 .5*1 . 005*VELJET )**2

EPINJ=0 . 09*KEINJ**1 .5/1 . 05*0 .5

)

KEINA=0.5*< 0.005*1.0 )**2

EPINA=0 . 09*KEINA**1 .5/(0.1)

* *li v Y 'j u j y v -^ j v y v, j v w ¥ ;J ¥ ¥ '« V ¥ ¥ ¥ ¥ ¥ ¥ tf ^t ^ ¥ ¥ " '-^ ""• ~^ ^ ¥ -^ ~-J "-J ^ ^ -.< w ! \J '^ / -i -u w ^ ;g m .^ -^ ^ -j, m M ¥ ¥ j m j JA A RltHinTH Jl~ « A . A A W^ AAAAAAAAWW A A A W A 5AJ(7r)l)()(^JfJlXHH)l)IH)f KtT^ W 9f A A A A A 7T A * W A A A WW

A A W A 7T A A A A STTKXX WHHHRH RJI 7T^^ ^^ÂARHXfXHXHHJ()(?(AHA)l)t^HnJlRJ?JlHAH A A A A A A A W A A W

* ** GROUP 10. INTERPHASE -TRANSFER PROCESSES AND PROPERTIES ** *asasasasxas asmuucatacjtasas as asasasasasiuucasasasjSiAsas asasasm assuutasvmasasmas^mm asasasasiuuucjcm.hluuuuuuutAAAtTAAWA A A^7TAAAAWW.WWAAA7TÂ A A AAAAAAWWAWWA<A;ATWWWA.AAWWA A A W^VWrWrTtW^^ A A A A inCITK

* DEFAULT TAKEN ** *k- w u u t ¥¥*¥¥¥¥'¥¥¥ ;4 ¥ "tt MM" ¥ ¥ ¥ ¥ ¥ MM ¥ ¥ V ¥ ¥ ¥ ¥ .Mi * M ¥ V ¥ .M ¥ ¥ ¥ J ^ i M k W k.'A J. k '^ Jt a ^ ^ 'i ¥ ^ k M «- ^ » MWW WWWWW*WA WWWWWWWWW K WWWWWWWWW KffXStKRjtXXXX RAWW.WWWWWWA A1 W WW W * WW WW * * WW A* A W

W A Itini W AAWAAÂ AAA7TAA W/ AÂWÂÂ AAAA AAtTtTW/WWAWAAWA AAAAW^WÂ A^WAAAAAAAAAWW ~~~A A^* *

* GROUP 11. INITIALIZATION OF VARIABLE OR POROSITY FIELDS ** *y -j w --f \j \t y u ~" ''^ ,U M k M jt ,'^ ^ ^ ^ ^ k V, M t t ¥ k 'I ^ ¥ ¥ V ¥ ^ ^ ^ ^. ^ V 'f '¥ ¥ ^ ¥ ¥ ¥ ¥. ^ ^ M M ¥ -L a A ^. .'A ^ ¥: ~^ ^. '* .¥ ¥ < y ' *WWWWWWWWWAP"TAAAAAAAAAWWWWAAWWWWAWAWWWWWWWWWWWWWWWWWAAWAÂWAWAWAWWWWWA^

FIINITI HI )=CPAMB*TMPAMBFIINIT(TMP1)=TMPAMBFIINIT(DEN1)=1.0FIINIT(P1)=0.0FIINIT(U1)=0.0FIINIT(V1)=0.0FIINIT(H1)=0.0FIINITI KE )=KEINAFIINITI EP)=EPINA

* *

* BLOCKING OUT THE MASS OF THE JET ENGINE *

CONPOR(0.0,CELL,1>1>5,6,6,7)* *

* WALL, FLOOR, AND CEILING BOUNDARY CONDITIONS. RESTRICTING FLOW** ACROSS A BOUNDARY BY USING CONPOR VALUES FROM 0.0 I NO FLOW) TO** 1.0 (MAX FLOW). BOUNDARY FRICTION TO FLOW IS ALSO IMPLEMENTED** USING A NEGATIVE BOUNDARY COORDINATE. THIS CONVENTION CAUSES ** FLOW PARALLEL TO THAT BOUNDARY FACE TO HAVE FRICTION. BOUNDARY** CONDITIONS WILL BE DESCRIBED BY COMMENT AND PLANE. *

* ** *

* TEST FACILITY FOUNDATION AND GROUND OUTSIDE STRUCTURE ** *

CCNPORI . , SOUTH , 1 ,NX , 1 , 1 , 1 ,NZ

)

PATCH! FL0R,SWALL,1, NX, 1,1,1,NZ, 1,1)COVAL(FLOR,U1,GRND2,0.0

)

COVALI FLOR ,N1 ,GRND2 ,0 . )

COVALl FLOR,KE,GRND2,GRND2)COVALI FLOR, EP ,GRND2 ,GRND2

)

* *

* JET-ENGINE TEST BAY ** ** BAY SIDE WALL (Y-Z) *

CONPOR! 0.0, WEST, 9, 9, 1,12, 2, 9)

* BAY CEILING (X-Z) ** *

CONPOR! 0.0, SOUTH, 1,8, 13, 13, 2, 9)* #* BAY WALL REAR (X-Y) 2 SECTIONS ** *

CONPOR (0.0, LOW, 6, 8, 1,12, -10, 10)CONPOR(0.0,LOW,1,5,11,12,-10,10)

* EXHAUST DUCT INLET TUBE ** *

CONPOR! 0.0, NORTH, 1,2, 3, 3, 10, 14)PATCH(TUB1,NWALL,1,2,3,3,10,14,1,1)COVAL ( TUB1 ,U1 ,GRND2 ,0 . )

COVAL! TUB1,W1,GRND2, 0.0)COVAL! TUB1 ,KE ,GRND2 ,GRND2

)

COVAL! TUB1,EP,GRND2,GRND2)CCNPOR 10.0 , SOUTH , 1 , 2 , 8 ,8 , 10 , 14

)

PATCH! TUB2, SHALL, 1,2, 8, 8, 10, 14, 1,1)COVALI TUB 2 ,U1 ,GRND2 ,0 . )

COVALI TUB2 ,W1 ,GRND2 ,0 . )

COVALI TUB2 ,KE ,GRND2 ,GRND2

)

COVALI TUB2 ,EP ,GRND2 ,GRND2

)

CONPOR! 0.0, WEST, 3, 3, 4, 7, 10, 14)PATCH(TUB3,WWALL,3,3,4,7,10,14,1,1)COVALI TUB3, VI, GRND2, 0.0)COVAL(TUS3,W1,GRND2,0.0

)

COVALI TUB3 ,KE ,GRND2 ,GRND2

)

COVALI TUB3 ,EP ,GRND2 ,GRND2

)

CONPOR! 0.0, LOW, 1,5, 1,3, 10, 10)CONPOR I . , LOW , 1 ,5 ,8 , 10 , 10 , 10

)

CCNPOR! 0.0, LOW, 3, 5, 4, 7, 10, 10)* ** SECONDARY-AIR INLET WALL (X-Y) *

CONPOR (0.0, LCW ,6,7,1,10,12,12)PATCH(SAIW,LWALL,6,7,1,10,12,12,1,1)COVALI SAIW,U1,GRND 2, 0.0)COVAL (SAIW, VI, GRND2, 0.0)COVALI SAIW,KE ,GRND2,GRND2

)

COVALI SAIW, EP,GRND2,GRND2)* *

* SECONDARY-AIR INLET AND PARTIAL EXHAUST DUCT CEILING (X-Z) ** *

CONPOR(0.0,SOUTH,1,7,11,11,10,12)PATCH(SAIWPE,SWALL,1,7,11,11,10,12,1,1)COVALI SAIWPE ,U1 ,GRND2 ,0 . )

COVALI SAIWPE ,W1 ,GRND2 ,0 . I

COVALI SAIWPE ,KE ,GRND2 ,GRND2

)

55

COVALl SAIWPE ,EP ,GRND2 ,GRND2

)

* ** EXHAUST DUCT CEILING (X-Z) ** *

CONPORI . , SOUTH , 1 ,5 , 11

,

11 , 13 , 20

)

PATCH! EDC,SHALL, 1,5, 11, 11, 13, 20, 1,1

)

C0VAL(EDC,U1,GRND2,0.0)COVALl EDC ,W1 ,GRND2 ,0 . )

COVAL(EDC,KE,GRND2,GRND2)COVALl EDC ,EP ,GRND2 ,GRND2 )

* ** EXHAUST-DUCT WALL (Y-2) ** *

CONPORI 0.0, WEST, 6, 6, 1,10, 13, 20)PATCH! EDWXZ, WWALL, 6, 6, 1,10, 13, 20, 1,1)COVALl EDWXZ, VI, GRND2, 0.0)COVALl EDWXZ, W1,GRND2, 0.0

)

COVAL! EDWXZ, KE,GRND2,GRND2)COVALl EDWXZ, EP,GRND2,GRND2)

* ** EXHAUST-STACK WALLS (X-Y) TWO SECTIONS ** *

CONPORI 0.0, HIGH, 1,5, 11, 13, 20, 20 )

PATCH(ESWXY1,HWALL,1,5,11,13,20,20,1,1)COVAL I ESWXY1 ,U1 ,GRND2 ,0 . )

COVALl ESWXY1, VI, GRND2, 0.0 )

COVALl ESWXY1 ,KE ,GRND2 ,GRND2 )

C0VAL(ESWXY1,EP,GRND2,GRND2)CONPOR (0.0, LOW ,1,5,1,13,27,27)PATCH! ESWXY2,LWALL, 1,5, 1,13, 27, 27, 1,1)COVALl ESWXY2,U1,GRND2,0.0 )

COVALl ESWXY2 ,V1 ,GRND2 ,0 . )

COVALl ESWXY2 ,KE ,GRND2 ,GRND2 )

COVALl ESWXY2,EP,GRND2,GRND2)* ** EXHAUST-STACK WALL (Y-Z) ** *

CONPORI 0.0, WEST, 6, 6, 1,13, 21, 26)PATCH! ESWXZ, WWALL, 6, 6, 1,13, 21, 26, 1,1)CCVALI ESWXZ ,V1 ,GRND2 ,0 . )

COVALl ESWXZ,W1,GRND2, 0.0 )

COVALl ESWXZ,KE,GRND2,GRND2 )

COVALl ESWXZ,EP,GRND2,GRND2 )

* TURNING VANES ** #

CONPOR I 0.0, SOUTH, 1,5, -7, 7, 21, 22)CONPORI 0.0, SOUTH, 1,5, -3, 3, 23, 2<+

)

CONPORI 0.0, LOW , 1 ,5 , 7 , 10 , -23 , 23 )

CONPOR I . , LOW , 1 ,5 , 3 , 6 , -25 , 25

)

********************************}H****************************^******************************************* XXKX>X)i X***** XXX ********** ** GROUP 12. CONVECTION AND DIFFUSION ADJUSTMENTS ** *

56

W .T ^^^ A W WA^WW^W^W^^^W^Â A KWWKHWWKW A" A A^WA'AWAHR^^WWWWWÂW^^WWA A A A WW^WWW^WW* *

* DEFAULT TAKEN ** *¥ rf ¥ V ¥ d V V V ¥ M M U ^ ^.' ^ .A .^ ,•*: M ^ î .a. i* a y ^^^yy^^^M'tf'Mi'M'VrfVVVM^'^M'^^ M M M ^ " . u "•""*: ^ ^, ,y iA ^ B~ ¥ kA A A JT A 7T A A A A A A^^^W A A A A AAAAAAAAWAAAAA A 7t7T^HR)m*AH7! HWirTfUATrwir)!^ H HT7T7T^ A H WTTtT

V V/ tj -W \j / \f W Yf V W W WW \#\*^^WWV\^w*f*#WVW\JM\*\^WWW\JXf'«WM\^V\#WWWY*Y»'\^Y#SrVWWWVWWl#VYfWV.-\^W-VfW 'LfW A A 7T A ^ A W A" W A A ^^ A JIWa AAAAAAÂAAAA AAAAAAAAAÂAWRAAA tTTTxAAAAAAAAAAAAAAA A A A ^

* ** GROUP 13. BOUNDARY CONDITIONS AND SPECIAL SOURCES ** *

ÂAAAHWAAWJ?A!RAWAA^ÂAAA^ÂA^ÂAAAWAAA^WAAAÂAAAA AAAAAAAAAAJtAAAAAAJW A

* ** JET-ENGINE MASS SOURCE ** *

PATCH! JETIN, HIGH, 1,1,5,6,5,5, 1,1)COVAL! JETIN , PI , FIXFLU , -MASJET*1 .

)

COVAL! JETIN, HI, ONLYMS, SAME

)

PATCH! JETOUT, LOW, 1,1, 5, 6, 8, 8, 1,1)COVALI JETOUT, PI, FIXFLU, MASJET*1.

)

COVALI JETOUT, Wl, ONLYMS, VELJET)COVALI JETOUT, HI, ONLYMS, CPJET*TMPJET)COVALI JETOUT, KE , ONLYMS ,KEINJ

)

COVALI JETOUT, EP, ONLYMS, EPINJ)* ** ATMOSPHERIC BOUNDARY CONDITIONS ** ** LAST CELL SURFACE IN X DIRECTION *

PATCH(XSKY,EAST,NX,NX,1,NY,1,NZ,1,1)COVAL(XSKY,P1,0.1,0.0 )

COVALI XSKY, HI, ONLYMS, CPAMB*TMPAMB

)

COVALI XSKY.KE, ONLYMS, KEINA)COVALI XSKY ,EP , ONLYMS, EPINA

)

* *

* LAST CELL SURFACE IN THE Y DIRECTION *

PATCH! YSKY, NORTH, 1, NX, NY, NY, 1,NZ, 1,1)COVALI YSKY, PI, 0.1, 0.0)COVALt YSKY, HI, ONLYMS, CPAMB*TMPAMB

)

COVALI YSKY ,KE , ONLYMS , KEINA

)

COVALI YSKY, EP, ONLYMS, EPINA)

* FIRST CELL SURFACE IN THE Z DIRECTION ** *

PATCH I ZSKY1 , LOW , 1 ,NX , 1 ,NY , 1 , 1 , 1 , 1

)

COVALI ZSKY1, PI, 0.1,0.0)COVALI ZSKY1 , HI , ONLYMS, CPAMB*TMPAMB

)

COVALI ZSKY1,KE , ONLYMS, KEINA

)

COVALI ZSKY1 ,EP, ONLYMS, EPINA

)

* *

* LAST CELL SURFACE IN THE Z DIRECTION ** *

PATCH! ZSKY2, HIGH, 1, NX, 1, NY, NZ,NZ, 1,1)C0VAL(ZSKY2,P1,0.1,0.0)COVALI ZSKY2, HI, ONLYMS, CPAM3*TMPAMB)COVALI ZSKY2,KE, ONLYMS, KEINA)

57

COVAL! ZSKY2 ,EP ,ONLYMS,EPINA

)

k k- » k k ¥ k ¥ ¥ k a ¥ k'k »f k k d ¥ ¥ / J ¥ "k ¥ k k k* ML M ki k k k. k. ^ .¥ kt ^ ^ ^ >£ ^ ^ ik k£ ^ w ^ " " ¥ ¥ ¥ ¥ " ^ '* ^ ^ " * '-J -l ^W W W A TT^W^ 7T A ATT^^lrWJtKK^Tf^W A A^WAWWAA A A A A A A tT A< A 7TtT A A * A A AWÂWWWAAAA A AAAAAAAR* ¥ ¥ k. k ». * -k- -J- -k. -k -k. / ¥ k k ¥ ¥ k .y" ¥ * -k. k- -k. -k- -M- -k^ -k. -k. k -k. -k. -d. k ¥ j- "k. ¥ ¥ .k- .k. J k ¥ k k -k. -M .k — 'J ¥ k J^ J » M î J J ^ ¥ U k

GROUP 14. DOWNSTREAM PRESSURE FOR PARAB=T

TW R A A A. A H7

DEFAULT TAKEN

*

**

WWWWW W W A A A A A

* GROUP 15. TERMINATION OF SWEEPS

**************

RESTRT(ALL)FSWEEP=1LSWEEP=2

*

**

^ A As A. A A A AAAAWAWAAAAAAAARA'

^t Jrf -¥ M ^ ^, M ¥ ¥ ¥ ¥ k, ^ ^ * U M tt ^ i'i .J ¥ V ¥ M M. k k. .a k. ,' M ^ k 't ^ ^ k it ^ k ,it it M ¥ '^ ^ it M k k, k. kfc ¥ ¥ ¥ Mi ¥ ^ ¥ ki k* ¥ M ¥ ¥ ¥ ¥

wwww w. -Tw w ,Twwwww a w w a .*w.*wwwwa"a' wwwwwwwwwa1 ,Twwwwwwwww Ww a w rw^ (rnirir*w)( a1 a1 .Twwww* ** GROUP 16. TERMINATION OF ITERATIONS ** *... -^ jjl ^ ^ ,

J M ^ -J j ^ .y; \J sj \J J ^ -J 'J ^ ^,y -- \j \i u lj 1/ \J \j •*. J \j <-- - ^ ^- '- u w i-t ^ ^ ;m, ^ j y, i.' -w y; >j ^ w. -^ ^ -^ -w y, w v \j- -^ ^ if w ~^-

* ** DEFAULT TAKEN ** *

W "k d" 'i ¥ 'kf ¥ U ¥ ¥ ¥ V V "X V ¥ V ^ ¥ ¥ U V At ik ^k ^ ^ ^ " " M, . . - a . a. k - ; k . a « y k a. ^ ^ » M j k n, k k k d. k ' ^ .

* ** GROUP 17. UNDERRELAXATION DEVICES *

* *. d k k a d « - k a k M k a. ¥, j . a, k ' '.k . k a

r

i a d j j- l ' m m 'i '* t . j_ j. .J. M. j_ j. :. __ M_ k ^ ' a a. » - ki *_ m < ¥ d 'd. k M k k

* *

DELT=S0 . /( NZ*0 . 2*VELJET

)

FACT=0.2SSHIFTED TO FACT=0.S AT 1SS0 SWEEPS

FACT=0.SRELAX(P1,LINRLX,0.3)RE LAX( Ul , FALSDT , FACT*DELT

)

RE LAXl VI , FALSDT , FACT*DELT

)

RE LAXl Wl , FALSDT , FACT*DELT

)

RELAX! KE, FALSDT, FACT*0ELT)RELAX! EP, FALSDT, FACT*DELT)

REMOVED THE 2.5 FROM HI RELAX AT 5000 SWEEPSRELAX! HI , FALSDT ,FACT*DELT*1 . )

* ** ** *

TAAA.AIAA AAIA"ARAÂÂAA 7TAAAAAWAAÂWAAAAAAAKAAAAAAA.»,.rtrt^v.nrt«^-»

58

J*. ^ A W H ^7T W Jl W7T7T7r^, A A ^^^tTAAAAAAWW^ ^T^^TtT A A 7r n A TT^ A W A TT A" A A A A A A A A A A A AWHRRRKKItRMW* ** GROUP 18. LIMITS ON VARIABLES OR INCREMENTS TO THEM ** */*. * ,\ f\ ^ ^^^ÂAÂAAAAATÂÂW^^^ÂAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA^TtAÂ^W™™ ^. A

* *

VARMIN( PI )=-2*PRESS0VARMINt HI )=CPAMB*TMPAMBVARMIN(U1)=-VELJETVARMINIV1 )=-VELJETVARMIN(W1)=-VELJETVARMINI TMP1 )=TMPAMBVARMIN(RH01)=0.1VARMAXt PI )=2*PRESS0VARMAXI HI )=CPJET*TMPJETVARMAX(U1)=VELJETVARMAXI VI )=VELJETVARMAXI W1)=VELJETVARMAXI TMP1 )=TMPJETVARMAXI RH01)=2.0

* *

********************************************************************

* ** GROUP 19. DATA COMMUNICATED BY SATELLITE TO GROUND ** *

* DEFAULT TAKEN ** **************************************************************************************************************************-**************** ** GROUP 20. PRELIMINARY PRINTOUT ** *

* ** ** DEFAULT TAKEN ** ******************************************************************************************************************************************

* GROUP 21. PRINTOUT OF VARIABLES**********************************************^!T*.*W^^^^.TAAAWA^?r^TA^^^^^W^W^^^:A7tAAAAAAAA^^W^^ÂAA^ÂA^^WA.AWAAAAAW^^^W

* ** GROUP 22. SPOT-VALUE PRINTOUT *

59

IXM0N=1IYMON=SIZMON=22TSTSWP=10

* *

*-**** X X X XXX X X**** * * X*JH*********»****'^»**tt**»JHHt*******»*JHt*-^*-*»*»»¥ V ¥ ¥ ¥ ¥ ¥ I ¥ "M. — Li ^ i k tf fJ 'J V V -M1 '-t 'A ¥ -M ¥ ¥ ¥ ¥ ¥ tf ¥ ¥ ¥' ¥ * ¥ ¥ ' ¥ J ¥ ¥ ¥ ¥ ¥ ¥ " " •" »* ./n, v^-^t.w v,w.,^^J--J- w'wvfAikKAAARAKRAKiT^ ttttRBw^Â^RîvwK^^ a a a a a a r jt/t w wkttt j» a a x7T7nnr7r3r7r7Wr7r7r7r1MrUlrwirir

* ** GROUP 23. FIELD PRINTOUT AND PLOT CONTROL ** #

PATCH!PL0T5,PR0FIL,1,1,5,5,1,NZ,1,1)PLOT! PLOTS , PI , -3000 . ,2500 . )

PATCH!PL0T3,PR0FIL,1,1,5,5,1,NZ,1,1)PLOT! PL0T3,U1, -20. 0,50.0)PATCH(PL0T<+,PR0FIL,1,1,5,5,1,NZ,1,1)PLOT! PL0T4 , VI ,-40. 0,60 .0 J

PATCH(PL0T2,PR0FIL,1,1,5,5,1,NZ,1,1)PLOTt PL0T2 ,W1 ,-15. ,500 . )

PATCH(PL0T1,PR0FIL,1,1,5,5,1,NZ,1,1)PLOTt PL0T1, HI, 275000. 0,2100000.0)PATCH! PL0T6,PR0FIL, 1,1, 1,10, 20, 20, 1,1)PLOTt PL0T6, HI, 300000. 0,1000000.0)PATCH! PL0T7,PR0FIL, 1,1, 1,10, 20, 20, 1,1)PLOT! PL0T7,W1, 20. 0,175.0)PATCH(PLOT8,PROFIL,1,5,5,5,20,20,1,1)PLOT! PL0T8, HI, 300000. 0,1000000.0)PATCH(PLOT9,PROFIL,1,5,5,5,20,20,1,1)PLOT! PL0T9,W1, 20. 0,175.0)PATCH! PLOT10,PROFIL, 1,1, 1,10, 16, 16, 1,1)PLOTt PLCT10, HI, 300000. 0,1000000.0)PATCH! PL0T11,PR0FIL, 1,1, 1,10, 16, 16, 1,1)PLOT (PL0T11,W1, 20. 0,175.0)PATCH!PL0T12,PR0FIL,1,5,5,5,16,16,1,1)PLOT! PL0T12, HI, 300000. 0,1000000.0)PATCH(PL0T13,PR0FIL,1,5,5,5,16,16,1,1)PLOT! PL0T13,W1, 20. 0,175.0)PATCH(PL0T14,PR0FIL,1,1,13,13,21,26,1,1)PLOT! PL0T14, HI, 500000. 0,600000.0)PATCH(PL0T1S,PR0FIL,1,1,13,13,21,26,1,1)PLOTt PL0T15, VI, 10. 0,45.0)PATCH(PL0T16,PR0FIL,1,5,13,13,23,23,1,1)PLOTt PL0T16, HI, 500000. 0,600000.0)PATCH(PL0T17,PR0FIL,1,5,13,13,23,23,1,1)PLOT! PL0T17, VI, 10. 0,45.0)NUMCLS=10*NXPRINNPLT=10ITABL=3IPR0F=3

LUPR3=6

t>^V¥M¥'^> HO^¥M^^^^^KM^k^k^Mâ^^MkM^¥^k^M^M ¥ ¥1 ¥ ¥ U ^ ^ ^ ¥ ¥ -r ¥ ¥ ¥ » ¥ M ¥ a . .» . .a a ^ a aw^ a a aw x w. AWWfl*w^)TîT^x w a. a x a w w ^ ^ ffif***f f w K a A a Kflîtw^ x x m n xmw aw^ww^^^*****##******l&***-*-**#**#:*-*-*#*r****#-*#* X X XXX X******* X XXXXXXXXX X *»»*-**

* *

¥ GROUP 24. DUMPS FOR RESTARTS ¥# *¥ . > ¥ ¥ -." i ' > ¥ ¥ ¥ m d ¥ j ¥ ¥ ^ 'a ¥ ¥ ¥ ¥ 'J ¥ » M ¥ "M li" ¥ ¥ '-' -> " J ¥ ¥ ¥ ¥. ,j ¥i ¥ ¥¥¥¥ ^- *---¥- ¥^ -^ ¥ A ¥ ¥ j* ¥ M. a', ¥ U Jww a* a a^^ a «^wwwww«^"ffw^w a /Taaaa (i a a a a w itmnvx a1 a a a aw aw"a,waawwwww^w^wa, a a a a xaa a

STOP

60

APPENDIX B

EARTH OUTPUT

61

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APPENDIX C

FIGURES

Figure C.l. Denmark Jet-Engine Test Facility

88

Figure C.2. Staggered-Grid Cell Configuration

89

Figure C.3. Cartesian Cell Configuration

9D

GROUP TITLE

1 RUN TITLE AND OTHER PRELIMINARIES2 TRANSIENCE: TIME-STEP SPECIFICATIONS3 X-DIRECTION GRID SPECIFICATION4 Y-DIRECTION GRID SPECIFICATIONS5 Z-DIRECTION GRID SPECIFICATIONS6 BODY-FITTED COORDINATES OR GRID DISTORTION7 VARIABLES STORED, SOLVED AND NAMED8 TERMS (IN DIFFERENTIAL EQUATIONS) AND DEVICES9 PROPERTIES OF THE MEDIUM (OR MEDIA)10 INTERPHASE-TRANSFER PROCESSES AND PROPERTIES11 INITIALIZATION OF VARIABLE OR POROSITY FIELDS12 CONVECTION AND DIFFUSION ADJUSTMENTS13 BOUNDARY CONDITIONS AND SPECIAL SOURCES14 DOWNSTREAM PRESSURE FOR PARAB=T15 TERMINATION OF SWEEPS16 TERMINATION OF ITERATIONS17 UNDERRELAXATION DEVICES18 LIMITS ON VARIABLES OR INCREMENTS TO THEM19 DATA COMMUNICATED BY SATELLITE TO GROUND20 PRELIMINARY PRINTOUT21 PRINTOUT OF VARIABLES22 SPOT-VALUE PRINTOUT23 FIELD PRINTOUT AND PLOT CONTROL24 DUMPS FOR RESTARTS

Figure C.4. PHOENICS Data Group Catagories

91

Figure C.5. CONPOR Porosity And Blockage

92

FILE: C0PYQ1 EXEC Al

8TRACE-STARTSTYPE WHAT ARE THE FILENAME AMD FILETYPE OF THE Ql FILE YOU WANTSTYPE TO STORE ON MVS? USE ENTER TO EXIT.SREAD VAR SQ1 &Q2

SIF /8Q1 EQ / SEXITSTATE SQ1 8Q2 A8IF SRC EQ 8G0T0 -NEXTSTYPE FILE 8Q1 8Q2 A DOES NOT EXIST. USE ENTER TO EXIT.

SREAD VAR 88IF /8 EQ / SEXIT

&GOTO -START-NEXT

STATE COPYQ1 JCL ASIF SRC EQ SGOTO -COPYSTYPE TEMPLATE FILE COPYQ1 JCL A DOES NOT EXIST ;

STYPE SEE LAB MANAGER.SEXIT -2

-COPYSERROR SEXIT -1

COPYFILE COPYQ1 JCL A TEMPI JCL A (REPLS = SCONCAT OF /YOURQ1 FI L ENAME/ 8Q1 /SSTACK TOP8STACK CLOCATE/YOURQ1FILENAME/SSTACK CHANGE S 1 1

SSTACK CLOCATE/SYSUT1/SSTACK GET 8Q1 8Q2 ASSTACK TOPSSTACK FILEXEDIT TEMPI JCL AEXEC SUBMIT TEMPI JCL ACONWAITDESBUF

SEXIT

FILE: COPYQ1 JCL Al

//CXHUSH JOB (4555,9999), 'COPYTMVS ' , CLASS=A// EXEC PGM=IEBGENER//SYSPRINT DD SYSOUT=A//SYSIN DD DUMMY//SYSUT2 DD DSN=MSS.S4555.PH0ENICS. SRC (YOURQ1FIL ENAME ),DISP=SHR//SYSUT1 DD x/*//

Figure C.6 COPYQ1 EXEC And JCL Files

93

FILE: RUNSAT EXEC Al

8TRACE-START8TYPE WHAT IS THE FILENAME OF THE Ql FILE YOU WANT TO RUN (SATELITE)?STYPE USE ENTER TO EXIT.SREAD VAR 8Q1

SIF /8Q1 EQ / SEXITx STATE 8Q1 DATA Ax SIF SRC EQ SGOTO -NEXTx STYPE FILE 8Q1 DATA A DOES NOT EXIST. USE ENTER TO EXIT.* SREAD VAR Sx SIF /S EQ / SEXITX SGOTO -START-NEXT

STATE RUNSAT JCL ASIF SRC EQ SGOTO -COPYSTYPE TEMPLATE FILE RUNSAT JCL A DOES NOT EXIST ;

STYPE SEE LAB MANAGER.SEXIT -2

-COPY8ERR0R SEXIT -1COPYFILE RUNSAT JCL A TEMP2 JCL A (REPLS = 8C0NCAT OF / YOURQ1 FI L ENAME / 8Q1 /8STACK TOPSSTACK CHANGE 8X18STACK FILEXEDIT TEMP2 JCL AEXEC SUBMIT TEMP2 JCL ACONWAITDESBUF

8EXIT

Figure C.7 RUNSAT EXEC File

94

FILE: RUNSAT JCL Al

//RXHUSH JOB (4555,9999), ' XCHAM' , CLASS=A, REGION=1024K//G02 EXEC PGM=SATLITP//STEPLIB DD DSN=MSS. PHOENICS. LOAD, DISP=SHR//LIST1 DD DSN=MSS. PHOENICS. LISTl.DIR,DISP=(OLD)//LI5T2 DD DSN=MSS. PHOENICS. LIST2.DIR,DISP=(OLD)//LIST3 DD DSN=MSS. PHOENICS. LIST3.DIR,DISP=(0LD)//LIST4 DD DSN=MSS. PHOENICS. LIST4.DIR,DISP=(0LD)//Ql DD DSN=MSS.S4555. PHOENICS. SRC(Y0URQ1FILENAME),DISP=( OLD)//PHHELP DD DSN=MSS. PHOENICS. PHHELP. DATA, DISP=(OLD)//SCRL DD DSN=MSS. PHOENICS. SCRL,DISP=(NEW, PASS),// DCB=(RECFM=F,LRECL=80,BLKSIZE=80),// SPACE=(TRK, (12,3)),UNIT=SYSDA//COPY DD DSN=MSS. PHOENICS. COPY, DISP=(NEN, PASS),// DCB=(RECFM=F,LRECL=8 0,BLKSIZE=6320),// SPACE=(TRK, (12,3)),UNIT=SYSDA//FT09F001 DD SYSOUT=x//FT06F001 DD SYSOUT=*//FT14F001 DD SYSOUT=*//G512 DD DSN=MSS. PHOENICS. G51 2 , DISP=( OL D)//G513 DD DSN=MSS. PHOENICS. G513,DISP=(0LD)//G514 DD DSN=MSS. PHOENICS. G514 , DISP=( OLD)//G515 DD DSN=MSS. PHOENICS. G515, DISP=( OLD )

//G516 DD DSN=MSS. PHOENICS. G516,DISP=(OLD>//G518 DD DSN=MSS. PHOENICS. G518 , DISP=( OLD)//G526 DD DSN=MSS. PHOENICS. G526 , DISP=( OLD)//G520 DD DSN=MSS. PHOENICS. G520 , DISP= ( OL D)//G521 DD DSN=MSS. PHOENICS. G521,DISP=(0LD)//G522 DD DSN=MSS. PHOENICS. G522, DISP=( OLD)//G523 DD DSN=MSS. PHOENICS. G523, DISP=( OLD)//G524 DD DSN=MSS. PHOENICS. G524 , DISP=( OLD)//G527 DD DSN=MSS. PHOENICS. G527,DISP=(0LD)//G528 DD DSN=MSS. PHOENICS. G528 , DISP=( OLD)//G529 DD DSN=MSS. PHOENICS. G529 , DISP= ( OLD)//G530 DD DSN=MSS. PHOENICS. G530

,

DISP= ( OLD)//G531 DD DSN=MSS. PHOENICS. G531 , DISP=( OLD)//G735 DD DSN=MSS. PHOENICS. G7 35 , DI SP= ( OL D)//G736 DD DSN=MSS. PHOENICS. G736

,

DISP= ( OLD)//G737 DD DSN=MSS. PHOENICS. G7 37 , DISP= ( OLD)//DF10 DD DSN=MSS.S4555. PHOENICS. DF10,// DTSP-SHR//DF12 DD DSN=MSS.S4555. PHOENICS. DF12, DISP=SHR//

Figure C.8. RUNSAT JCL File

95

FILE: RUNEAR EXEC Al

STRACEEXEC SUBMIT RUNEAR JCL A

FILE: RUNEAR JCL Al

//EXHUSH JOB (4555,9999), 'CHAM', CLASS=G, REGION=2048K//XMAIN ORG=NPGVMl . 4555P, LINES = ( 12)//G02 EXEC PGM=EARTHP//STEPLIB DD DSN=MSS.PHOENICS.LOAD,DISP=SHR//DSTL DD DUMMY//DF09 DD DSN=MSS. 34555. PHOENICS . DF09 , DISP=SHR//DF01 DD DSN=S8DF01,DISP=(NEN,PASS),// DCB=(RECFM=VBS,LRECL=19000,BLKSIZE=19006),// SPACE=(TRK, (25,3)),UIIIT = SYSDA//DF02 DD DSN=88DF02,DI5P=(NEW,PASS),// DCB=(RECFM=VBS,LRECL=190 00,BLKSIZE=19006),// SPACE=(TRK, (25,3) ),UNIT=SYSDA//DF03 DD DSN=S8DF03,DISP=(NEH,PASS),// DCB=(RECFM=VBS,LRECL=19000,BLKSIZE=190 06),// SPACE=(TRK, (25,3) ),UNIT=SYSDA//DF04 DD DSN=SSDF04,DISP=(NEM,PASS),// DCB=(RECFM=VBS,LRECL=19000,BLKSIZE=19006),// SPACE=(TRK,(25,3)),UNIT=SYSDA//DF05 DD DSN=&&DF05,DISP=(NEW,PASS),// DCB=(RECFM=VBS,LRECL=19000,BLKSIZE=19006),// SPACE=(TRK, (25,3) ),UNIT=SYSDA//DF07 DD DSN=88DF07,DISP=(NEH,PASS),// DCB

=

(RECFM=VBS,LRECL=1 9000, BLKSIZE=1 9006),// SPACE=(TRK,(25,3)),UNIT=SY5DA//DF08 DD DSN=S8DF08,DISP=(NEW,PASS),// DCB=(RECFM=VBS,LRECL=19000,BLKSIZE=190 06),// SPACE=(TRK, (25,3)),UNIT=SYSDA//DF15 DD DSN = 88DF15, DISP = ( NEN, PASS )

,

// DCB=(RECFM=VBS,LRECL=190 0,BLKSIZE=190 06),// SPACE=(TRK, (25,3)),UNIT=SYSDA//DF16 DD D3N=MSS.S4555. PHOENICS. DF16 , DISP = SHR//DF10 DD DSN = MSS.S<+555. PHOENICS. DF1 , DISP=( OL D)//DF12 DD DSN=MSS.S4555. PHOENICS. DF12, DISP=( OLD )

//FT14F001 DD SYSOUT=*//FT06F001 DD SYSOUT=*//

Figure C.9 RUNEAR EXEC And JCL Files

96

Figure CIO. Test Facility Side View (Y-Z Plane)

97

Figure C.ll. Test Facility Top View (X-Z Plane)

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99

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x GROUP 5. X-DIRECTION GRID SPECIFICATIONx NX = THE NUMBER OF CELLS IN THE X DIRECTION (INTEGER)X XULAST = DISTANCE IN THE X DOMAIN (METERS)x

NX=XNCBL1+XNCMD1+XNCMD2+XNCMD3+XNCBL2+XNCBL3+XNCEX1XULAST=XLBL1+XLMID1+XLMID2+XLMID3+XLBL2+XLBL3+XLEXT1

xXFRAC(1)=-XNCBL1; XFRAC( 2) =XLBLl/(XNCBLlxXULAST)XFRAC(3)=XNCMD1XFRAC(5)=XNCMD2XFRAC(7)=XNCMD3XFRAC(9)=XNCBL2

XFRAC(4)=XLMID1/(XNCMD1XXULAST)XFRAC(6)=XLMID2/(XNCMD2XXULAST)XFRAC(8)=XLMID3/(XNCMD3XXULAST)XFRAC(10)=XLBL2/(XNCBL2XXULAST)

XFRAC(11)=XNCBL3; XFRAC( 12 ) =XLBL3/(XNCBL3*XULAST

)

XFRAC(13)=XNCEX1; XFRAC( 14) =XLEXT1/(XNCEX1XXULAST)xx GROUP 4. Y-DIRECTION GRID SPECIFICATIONx NY = THE NUMBER OF CELLS IN THE Y DIRECTION (INTEGER)x YVLAST = DISTANCE IN THE Y DOMAIN (METERS)x

NY=YNCMID+YNCBL1+YNCBL2+YNCEX1+YNCEX2+YNCBL3YVLA5T=YLMID+YLBL1+YLBL2+YLEXT1+YLEXT2+YLBL3

x

YFRAC(1)=-YNCBL1; YFRACC 2) =YLBLl/( YNCBLlxYVLAST)YFRAC(3)=YNCMIDYFRAC(5)=YNCBL2YFRAC(7)=YNCEX1YFRAC(9)=YNCEX2

YFRACC 4 )=YLMID/(YNCMIDXYVL AST)YFRAC(6)=YLBL2/(YNCBL2XYVLAST)YFRACC 8 )=YLEXT1/(YNCEX1XYVL AST)YFRAC(10)=YLEXT2/(YNCEX2XYVLAST)

YFRACC 11 )=YNCBL3; YFRAC( 12) =YLBL3/(YNCBL3XYVLAST)Xx GROUP 5. Z-DIRECTION GRID SPECIFICATIONx NZ = THE NUMBER OF CELLS IN THE Z DIRECTION (INTEGER)x ZWLAST = DISTANCE IN THE Z DOMAIN (METERS)x

NZ=ZNCEX1+ZNCIN1+ZNCIN2+ZNCIN3+ZNCIN4+ZNCIN5+ZNCIN6+ZNCEX2Zhi.AST = ZLEXTl+ZLINTl +ZLINT2 +ZLINT3+ZLINT4+ZLINT5 +ZLINT6 +ZLEXT2

x

ZFRAC(1)=-ZNCEX1; ZFRACC 2 ) =ZLEXTl/(ZNCEXlxZWLAST)ZFRACC 3 )=ZNCIN1; ZFRACC4)=ZLINT1/(ZNCIN1*ZWLAST)ZFRACC 5 )=ZNCIN2, ZFRACC6 ) =ZLINT2/(ZNCIN2*ZWLAST )

ZFRAC(7)=ZNCIN3; ZFRACC 8 ) =ZLINT3/ CZNCIN3XZWLAST)ZFRACC 9 )=ZNCIN4; ZFRAC( 10)=ZLINT4/CZNCIN4XZWLAST)ZFRACC 11 )=ZNCIN5; ZFRACC 12) =ZL INT5/CZNCIN5XZWL AST

)

ZFRACC 13 )=ZNCIN6; ZFRACC 14 ) =ZLINT6/ CZNCIN6XZWL AST

)

ZFRACC 15) =ZNCEX2; ZFRACC 16 ) =ZLEXT2/( ZNCEX2XZWL AST

)

Figure C.14. Ql MEthod-Of-Pairs Coding Sequence

101

XFRAC C 3) = 1 OOOE+00XFRAC ( 5) = 1 OOOE+00XFRAC ( 7) = 1 OOOE+00XFRAC ( 9) = 1 OOOE+00XFRAC ( 11) r 3 OOOE+00XFRAC ( 13) = 1 OOOE+00

GROUP 3. X-DIRECTION GRID SPACINGCARTES = TNX = 9XULAST = 9.900E+00

METHOD OF PAIRS USED FOR GRID SETTINGXFRAC ( 1) = -1. 000E+00 ;XFRAC ( 2) = 5.051E-02

:XFRAC ( 4) = 5.051E-02XFRAC ( 6) = 5.051E-02XFRAC ( 8) = 5.051E-02XFRAC ( 10) = 5.051E-02XFRAC ( 12) = 1.818E-01XFRAC ( 14) = 2.020E-01

XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXGROUP 4. Y-DIRECTION GRID SPACING

NY = 16YVLAST = 1.700E+01

METHOD OF PAIRS USED FOR GRID SETTINGYFRAC ( 1) = -4. OOOE+00 ;YFRAC ( 2) = 2.941E-02

000E+00 ;YFRAC ( 4) = 2.941E-02000E+00 ;YFRAC ( 6) = 2.941E-02000E+00 ;YFRAC ( 8) = 1.132E-01000E+00 ;YFRAC ( 10) = 1.265E-01000E+00 ;YFRAC ( 12) = 1.176E-01

XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXGROUP 5. Z-DIRECTION GRID SPACING

PARAB = FNZ = 28ZWLAST = 6.490E+01

METHOD OF PAIRS USED FOR GRID SETTINGZFRAC ( 1) = -1. OOOE+00 ;ZFRAC ( 2) = 3.082E-02

;ZFRAC ( 4) = 7.242E-Q2ZFRAC ( 6) = 4.931E-02ZFRAC ( 8) = 1.156E-02ZFRAC ( 10) = 1.541E-02ZFRAC ( 12) = 5.023E-02ZFRAC ( 14) = 2.157E-02ZFRAC ( 16) = 3.082E-02

XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXX

YFRAC ( 3) = 2YFRAC ( 5) = 4YFRAC ( 7) = 2YFRAC ( 9) = 1

YFRAC ( 11) = 3

ZFRAC ( 3) = 5 000E+00ZFRAC ( 5) = 1 000E+00ZFRAC ( 7) = 2 000E+00ZFRAC C 9) = 6 000E+00ZFRAC ( 11) = 5 OOOE+00ZFRAC ( 13) = 6 000E+00ZFRAC ( 15) = 2 OOOE+00

Figure C.15. EARTH Method-Of-Pairs Output

102

Eco

E

CMca»

i—

t

i—

t

caCO

o

"t

OCsJ

i

C°.

CSJ j t

1i

#/1—

1

(&U3 -

E

CM

ro

LT)

Eo

<Sj

<J2

i

E " 1

|LD^^ ,

r

• /OEj[ 1C2> CM '

CM •

roC2j

E

*d-

C=j

ECM

2 f

Figure C.16. System Domain Grid (X-Z Plane)

103

CM

/

CM

rocaun

X

LT)

r--

//:-

O E<Sj CMcm •

oo(Si

«=3-

CE> •

LT)

CMca.,

CM

CO

E lt>

Lf) CMi—

1

cr>• •

CM i—i

C°, CO,

t—

1

CM

oC=.

O

rM

Figure C.17. System Domain Grid (Y-Z Plane)

104

PATCHCPLOT10 ,PROFIL, 1, 1, 1, 10, 16, 16,PLOTCPLOT10 ,H1 , 3.000E+05, 1.000E+06)TABULATION OF ABSCISSA AND ORDINATES...

1, 1)

Y500E-01500E-01250E+00750E+00250E+00750E+00250E+00750E+00250E+00750E+00

VARIABLEMINVAL=MAXVAL=

HI454E+05154E+05411E+05754E+05650E+05599E+05667E+05340E+05097E+05613E+05

HI000E+05000E+06

CELLAV= 6.074E+05

1.000.900.800.700.60

.1 .2 .3 .4 .5 .6 .7 .8 .9 1.0THE ABSCISSA IS Y . MIN= 2.50E-01 MAX= 4.75E+00

Figure C.18. H vs Y-Axis at IY=1 to IY=10For IX=1 And IZ=16

1D5

PATCHCPL0T11 ,PROFIL, 1, 1, 1, 10.PLOKPLOTll ,W1 , 2.000E+01, 1.750E+02)TABULATION OF ABSCISSA AND ORDINATES...

16 16 1, 1)

Y2.500E-017.500E-011.250E+001.750E+002.250E+002.750E+003.250E+003.750E+004.250E+004.750E+00VARIABLE

MINVAL=MAXVAL=CELLAV=

1.00 +....+.

Wl2.923E+014.467E+017.167E+011.226E+021.696E+021.684E+021.203E+026.873E+014.100E+012.919E+01

Wl2.000E+011.750E+028.653E+01

... + .... + ... .+>lsl<-rt-r-»W. + .... + .... + .... + ....+0.90 +0.80 +0.70 +

0.60 +

0.50 +0.40 +

0.30 +

0.20 + J*0.10 W^"^o.oo +7. . . +

.

s \ +if \ +

/ N. +

\^^ +

^^^ W... + + .... + .... + .... + .... + .... + .... +7"7~~-t+

.1 .2 .3 .4 .5 .6 .7 .8 .9 l.UTHE ABSCISSA IS Y . MIN= 2.50E-01 MAX= 4.75E+00

Figure C.19. W vs Y-Axis At IY=1 To IY=10For IX=1 And IZ=16

106

PATCHCPL0T12 ,PROFIL, 1, 5, 5, 5,PL0TCPL0T12 ,H1 , 3.000E+05, 1.000E+06)TABULATION OF ABSCISSA AND ORDINATES...

16, 16, 1, 1)

2.500E-017.500E-011.250E+001.750E+002.250E+00VARIABLE


HI650E+05746E+05784E+05848E+05530E+05

HIOOOE+05000E+06512E+05

.1 .2 .3 .4 .5 .6 .7 .8 .9 1.0THE ABSCISSA IS X . MIN= 2.50E-01 MAX= 2.25E+00

Figure C.20. H vs X-Axis At IX=1 To IX=5For IY=5 And IZ=16

1 C7

PATCHCPL0T13 ,PROFIL, 1, 5, 5, 5,PL0TCPL0T13 ,W1 , 2.000E+01, 1.750E+02)TABULATION OF ABSCISSA AND ORDINATES...

16, 16, 1, 1)

2.500E-017.500E-011.250E+001.750E+002.250E+00VARIABLE


Wl696E+02196E+02867E+01822E+01315E+01

Nl000E+01750E+02

8.384E+01

1.000.900.800.70

1 .2 .3 .<+ .5 .6 .7 .8 .9 1

ISCISSA IS X . MIN= 2.50E-01 MAX= 2.25E+0I

Figure C.21. W vs X-Axis At IX=1 To IX=5For IY=5 And IZ=16

UO

x*xxx**xxxx*xx*x*x*x*xxx*xx**xxxxx**xxx**x*xxxxxxx*xx*x*x***PATCHCPL0T6 ,PROFIL, 1, 1, 1, 10, 20, 20, 1, 1)PL0T(PL0T6 ,H1 , 3.000E+05, 1.000E+06)TABULATION OF ABSCISSA <\ND ORDINATES. .

.

Y HI2.500E-01 5.117E+057.500E-01 5.534E+051.250E+00 5.850E+051.750E+00 6.171E+052.250E+00 6.376E+052.750E+00 6.331E+053.250E+00 6.057E+053.750E+00 5.715E+054.250E+00 5.447E+054.750E+00 5.315E+05VARIABLE HI

MINVAL= 3.000E+05MAXVAL= 1.000E+06CELLAV= 5.791E+05

1.00 +....+. ...+....+.. . . + . ...+....+....+....+....+. ++0.90 +

0.80 + +0.70 + +

0.60 + +0.50 +

0.40 + R.

u_ H U +nH It-—~^__ +

0.30 H^-""^ H-

0.20 -F +

0.10 + +0.00 +....+. ...+....+.. . . +

.

...+....+....+....+....+. +..1 .2 .3 .4 .5 .6 .7 .8 .9 1

THE ABSCISSA IS Y MIN= 2.50E-01 MAX= 4.75E+00XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXX

Figure C.22. H vs Y-Axis At IY=1 To IY=10For IX=1 And IZ=20

109

PATCHCPL0T7 ,PROFIL, 1, 1, 1, 10,PL0TCPL0T7 ,W1 , 2.Q00E+01, 1.750E+02)TABULATION OF ABSCISSA AND ORDINATES...

20, 20, 1, 1)

Y2.500E-017.500E-011 .250E+001.750E+002.250E+00.750E+00250E+00750E+00250E+00750E+00

VARIABLEMINVAL=MAXVAL=CELLAV=

1 .000.900.800.700.600.500.400.300.20

+

++

+++

+++

0.10 w0.00 +

THE ABxxxxxx

HI170E+01000E+01790E+01663E+01

7.281E+017.200E+01,108E+01297E+01782E+01620E+01

Wl2.000E+011.750E+025.691E+01

•1 -2 .3 .4 .5 .6 .7 .8 .9' iSCISSA IS Y . MIN= 2.50E-01 MAX= 4.75E+0

.++++++++

+.+.0

XXXXXX

Figure C.23. W vs Y-Axis At IY=1 To IY=10For IX=1 And IZ=20

110

PATCHCPL0T8 ,PROFIL, 1, 5, 5, 5, 20, 20, 1, 1)

PL0TCPL0T8 ,H1 , 3.000E+05, 1.000E+06)TABULATION OF ABSCISSA AND ORDINATES...

X HI2.500E-01 6 .376E+057.500E-01 6 .165E+051.250E+00 5 .890E+051.750E+00 5 .679E+052.250E+00 5 .577E+05VARIABLE HI

MINVAL= 3 000E+05MAXVAL= 1 000E+06CELLAV= 5 937E+05

1.00 +....+. +....+....+.. . . + . .

0.90 + +0.80 + +0.70 + +0.60 +

0.50 H H_____++

0.40 +

0.30 +H— ^ —

H

+0.20 + +0.10 + +0.00 +. . . .+. +....+....+.. . . + . .

.1 .2 .3 .4 .5 .6 .7 .8 .9 1.0THE ABSCISSA IS X . MIN= 2.50E-01 MAX= 2.25E+00

Figure C.24. H vs X-Axis At IX=1 TO IX=5For IY=5 And IZ=20

111

PATCHCPL0T9 ,PROFIL, 1, 5, 5, 5,PL0TCPL0T9 ,W1 , 2.000E+01, 1.750E+02)TABULATION OF ABSCISSA AND ORDINATES...

20, 20, 1, 1)

500E-01500E-01250E+00750E+00.250E+00


1.000.900.800.700.600.500.400.300.200.100. 00

+++++++

+++ .

THE ABS

HI281E+01474E+01391E+01524E+01084E+01

Wl2.000E+011.750E+025.551E+01

++++++++

+ .+....+....+....+....+....+....+....+..•+.1 .2 .3 .<+ .5 .6 .7 .8 .9 1.0

CISSA IS X . MIN= 2.50E-01 MAX= 2.25E+00

Figure C.25. W vs X-Axis At IX=1 To IX=5

For IY=5 And IZ=20

11 2

PATCHCPL0T14 ,PROFIL, 1, I, 13, 13, 21, 26,PL0TCPL0T14 ,H1 , 5.000E+05, 6.000E+05)TABULATION OF ABSCISSA AND ORDINATES...

1, 1)

Z000E+00350E+00050E+00375E+01845E+01315E+01

VARIABLEMINVAL=NAXVAL=CELLAV=

HI429E+05535E+05653E+05895E+05905E+05681E+05

HIOOOE+05000E+05

5.683E+05

++

++

THE AB

0.00".I .2 .3 A .5 .6 .7 .8 .9 1

SCISSA IS Z . MIN= 1.00E+00 MAX= 2.31E+0XXXX*XXXX*XX**XXXX*XXX**XXXXX**XX***X***********

++++++.+.0

1

xxxxxx

Figure C.26. H vs Z-Axis At IZ=21 To IZ=26For IX=1 And IY=13

11

PATCHCPL0T15 ,PROFIL, 1, 1, 13, 13,PL0TCPL0T15 ,V1 , l.OOOE+01, 4.500E+01)TABULATION OF ABSCISSA AND ORDINATES...

Z VIl.OOOE+00 1.286E+01

21, 26, 1, 1)

350E+00050E+00375E+01845E+01315E+01


973E+01223E+01062E+01919E+01821E+01

VI000E+01500E+01547E+01

1.000.900.80

+....+....+....+....+....+....+.. .+

0.700.600.500.400.300.20 +0.10 V0.00 +

.1 .2 .3 .<+ .5 .6 .7 .8 .91.0THE ABSCISSA IS Z . MIN= 1.00E+00 MAX= 2.31E+01

+....+....+....+....+.,..+. .+. .+

+

++++

++++

+ . .+

Figure C.27. V vs Z-Axis At IZ=21 To IZ=26For IX=1 And IY=13

11 4

PATCH(PL0T16 ,PROFIL, 1, 5, 13, 13,PL0TCPL0T16 ,H1 , 5.000E+05, 6.000E+05)TABULATION OF ABSCISSA AND ORDINATES...

23, 23, 1, 1)

500E-01500E-01250E+00750E+00250E+00


HI653E+05647E+05638E+05628E+05620E+05

HIOOOE+05OOOE+05637E+05

00908070605040

0.300.200.100.00

+....+....+....+....+

.4.1 .2 .3 .4 .5 .6 .7 .8 .91.0THE ABSCISSA IS X . MIM= 2.50E-01 MAX= 2.25E+00

Figure C.28. H vs X-Axis At IX=1 To IX=5

For IY=13 And IZ=23

115

PATCHCPL0T17 ,PROFIL, 1, 5, 13, 13, 23, 23,PL0TCPL0T17 ,V1 , l.OOOE+01, 4.500E+01)TABULATION OF ABSCISSA AND ORDINATES...

1, 1)

500E-01500E-01250E+00750E+00250E+00


VI223E+01306E+01^4^8E+01591E+01641E+01

VI000E+01500E+01442E+01

1 .00 +

0.90 +0.80 +

0.70 +

0.60 +

0.50 +

0.40 ±-

0.30 V0.20 +

0.10 +0.00 +

THE AB******

.1 .2 .3 .4 .5 .6 .7 .8 .9 1.03CISSA IS X MIN= 2.50E-01 MAX= 2.25E+00************ ******************************************

Figure C.29. V vs X-Axis At IX=1 to IX=5For IY=13 And IZ=23

11 6

LIST OF REFERENCES

1. Brunner, D. D. , Naval Civil Engineering Laboratory,Port Hueneme, Project Master Plan for Aviation GasTurbine Engine Test Facilities . March 1984.

2. Bailey, D. L. , Tower, P. W. , and Fuhs, A. E.,Advisory Group for Aerospace Research and DevelopmentReport Number 125, Polution Control of Airport EngineTest Facilities . April 1973.

3. Walters, J. J. and Netzer, D. W. , A Validation ofMathematical Models for Turbo Jet Test Cells .

Engineer's Thesis, Naval Postgraduate School,Monterey, California, June 1978.

4. Brink-Johnsen, B. , Titech Company, OSLO, Norway LetterSerial TS/BBJ/ABV, to the Naval Civil EngineeringLaboratory, Port Hueneme, Computerized Jet Engine TestCell and Aircraft Trim Facility . 16 September 1985.

5. Rosten, H. I. and Spalding, D. B. , Cham of NorthAmerica, Incorporated, Huntville, Alabama, PHOENICSBeginner's Guide and User's Manual , October 1976.

117

INITIAL DISTRIBUTION LIST

No. Copies

Defense Technical Information Center 2

Cameron StationAlexandria, VA 22304-6145

Library, Code 0142 2

Naval Postgraduate SchoolMonterey, CA 93943-5002

Professor David Salinas 3

Code 69SaNaval Postgraduate SchoolMonterey, CA 93943

C. Kodres 3

Naval Civil Engineering LaboratoryPort Hueneme, CA 93 043

Professor Anthony J. Healey 1

Code 069Chairman, Department of Mechanical EngineeringNaval Postgraduate SchoolMonterey, CA 9 3 943

LCDR Michael J. Meaker 2

Code 800Long Beach Naval ShipyardLong Beach, CA 90822-5099

118

#-* , ti c sj Q

ThesisM399543c.l

Meaker

Computer model of anaviation gas tn-rhste<! . ~ .f

dS turbmetest facility

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Meaker

Computer model of anaviation gas turbine

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