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Calhoun: The NPS Institutional Archive
Theses and Dissertations Thesis Collection
1988
Computer model of an aviation gas turbine test facility.
Meaker, Michael J.
http://hdl.handle.net/10945/22974
I
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
TASKNO
WORK UNITACCESSION NO
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.24 H vs X-Axis at IX=1 to IX=5 111for IY=5 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.28 H vs X-Axis at IX=1 to IX=5 115for IY=13 and IZ=23
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-^uwwuwwij v u- vf v> vi w ^ w yJtAAAA^AAAAAA A^AJTAAAAAAAAAAAAAAAAAAAA^AAAAAAAAAAAAAAAAAAAAAA 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
* ** ** ************************************************************************^AAWAW*W*^^AA*AA^AA^*^RAAffWA^^^AAAAAAA"A^^AAAA^AAAAWAAWK*A*AAAAWWAAA* ** VARIABLE DECLARATIONS *
* *7tAW^^AA^A^W^^TT^W^A'W^A^WA^A^WAAAAA^*AAAAWW^^WA«!W^AWWW^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 (inAHA^AAAAAT^nww^ a r jiw^^ a a^^ fnnv>vinnnntmnv?CHinvivii a a ^ a a a 7HrT7nfX7TT
AAAAWAAjvnWAA^AAWWA"WW^WA WA1WWWW^AAA^W*AKA^WWAI A^A;W.*A'A'W^^WWWRA^A1 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^nnAAAAAAAAAAA^AAAAAAAAAAA 7TAA/\AAAAAAAAAA^/%«^AAWAAAAAAAAAAAAAAAAA.W
SOLVE! P1,H1, Ul, VI, Wl)S0LUTN(P1,Y,Y,Y,N>N,N)STORE! RH01.TMP1)
* *AAAAAAW^^WAAAAAAAAWA^^AWAAA A^^A^AA^A A A A W A A A A A 9^AAAAAA.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^^WWWWW^A'AA'A^^A 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^^ ^^^AARHXfXHXHHJ()(?(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.WWAAA7T^A 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 AAWAA^A AAA7TAA W/ A^AW^A^A AAAA AAtTtTW/WWAWAAWA AAAAW^W^A 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"TAAAAAAAAAWWWWAAWWWWAWAWWWWWWWWWWWWWWWWWAAWA^AWAWAWAWWWWWA^
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^^A A KWWKHWWKW A" A A^WA'AWAHR^^WWWWW^AW^^WWA A A A WW^WWW^WW* *
* DEFAULT TAKEN ** *¥ rf ¥ V ¥ d V V V ¥ M M U ^ ^.' ^ .A .^ ,•*: M ^ ^i .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 AAAAAA^AAAAA AAAAAAAAA^AAWRAAA tTTTxAAAAAAAAAAAAAAA A A A ^
* ** GROUP 13. BOUNDARY CONDITIONS AND SPECIAL SOURCES ** *
^AAAAHWAAWJ?A!RAWAA^^AAAA^^AA^^AAAAWAAA^WAAA^AAAAA 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 AW^AWWWAAAA 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 ^i 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"ARA^A^AAA 7TAAAAAWAA^AWAAAAAAAKAAAAAAA.»,.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\ ^ ^^^^AA^AAAAAAT^A^AW^^^^AAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA^TtA^A^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^^^AAA^^AA^^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^^A^R^ivwK^^ 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^M^a^^MkM^¥^k^M^M ¥ ¥1 ¥ ¥ U ^ ^ ^ ¥ ¥ -r ¥ ¥ ¥ » ¥ M ¥ a . .» . .a a ^ a aw^ a a aw x w. AWWfl*w^)T^iT^x w a. a x a w w ^ ^ ffif***f f w K a A a Kfl^itw^ 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
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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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Figure C.12. Vertical Y-Z Plane Zones
99
Z1X31Z
91NI1Z
S1NI1Z
171NI1Z
eiNiiz
Z1NI1Z
UNI1Z
T1X31Z
COCVJrHco C\J O Q Q i—
I
_J _l >-i —i —i _|co cq 2: s: s: cq__i —i —i —i i »X X X X X X
\r-vi
Figure C.13. Horizontal X-Z Plane Zones
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
MINVAL=MAXVAL=CELLAV=
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
MINVAL=MAXVAL=CELLAV=
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
VARIABLEMINVAL=MAXVAL=CELLAV=
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
VARIABLEMINVAL=MAXVAL=CELLAV=
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
VARIABLEMINVAL=MAXVAL=CELLAV=
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
VARIABLEMINVAL=MAXVAL=CELLAV=
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
Thesi?M399543
c.l
Meaker
Computer model of anaviation gas turbine
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