Technology Benefit Estimator

214 Pages·09.19 MB·English

https://ntrs.nasa.gov/search.jsp?R=19950013085 2019-01-04T01:21:27+00:00Z
Technology Benefit Estimator
(TIBEST)
USER'S MANUAL
WNE1994
Edward R. Generazio
NASA Lewis Research Center
Mail Stop 49-8
21000 Brookpark Rd.
Cleveland, Ohio 44135
OFFICE [phone]
FAJ«216)433-8011
E-MAIL [email protected]

TABLE OF CONTENTS
Section
Welcome To T /BESI' ........................................................................................•....... .i
..
S' Um.Ula.ry- .•....................•...••.•.••...•...••.•...••.......•....•....................•..........•.•..•....•..•••.•••..•
.11
1.0 WIRODUCTION ....................................................................................................... 1.1
1.1 Lea.nUng About T /B'EST ...................................................................................... 1.1
nus
1.2 How to Use Man.ual. ..................................................................................... 1.3
2.0 SETJ:'m'G UP T /BEST ................................................................................................ 2.1
21 Preparing to Use T/BEST. ................................................................................... .21
2.2 Restoring T /BEST tar file and Directories ....................................................... 22
3.0 DEMONS1RATION OF T/BESI' ............................................................................ 3.1
3.1 Executing T /BEST ................................................................................................. 3.1
3.2 Interactive Sessions for Supersonic Engine Example .................................... 3.2
3.3 Changing Default Parameters ............... ~ ........................................................... .3.10
4.0 DESCRlPTION OF T /BEST EXECUTIVE SYSTEM: ..............................................4 .1
4.1 T /BEST Modules Interaction ..............................................................................4 .1
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4.2 Format and Content of the T /BEST Neutral File ............................................. 4.7
4.3 T /BEST Shell Script .............................................................................................. 4.8
4.4 Compilation and linking of T /BEST Modules ................................................4 .9
5.0 DESCRIPTION OF DEFAULT T /BEST ANALYSES MODULES ....................... 5.1
5.1 Thermodynamic and Flow Path Analysis (NNEPWATE Module) .............. 5.1
5.1.1 Thermodynamic Engine Cycle Analysis (NNEP89) ....................................... 5.1
5.1.2 Initial Engine Sizing (VV A'fE89) ......................................................................... 5.2
5.2 Blade Assessment for Ice Impact (BLASIM) .................................................... 5.2
..
5.3 Meridional-Transonic Boundary Layer Fluid Analysis (MTSB Module) .... 5.3
5.4 Noise Analysis (NOISE Module) ........................................................................ 5.3
/
5.5 Statistical Prediction (PREDICT Module) ..........................................................5 .4
TABLE OF CONTENfS (Continued)
5.6 Range Analysis (R.ANGE Module) ..................................................................... 5.4
5.7 O'ty' Pai.rs (cnY Mod.ule) ................................................................................... .5.4
5.8 Maintenance Between Repair (REPAIR Module) ........................................... .5.4
5.9 Direct Operating Cost (DOC Module) .............................................................. .5.5
5.10 Life Cycle Maintenance (LCC Module) ........................................................... .5.5
5.11 Flight Mission Summary (FLOPS Mod.ule) ...................................................... .5.5
6 .. 0 P ARAME'IRIC snJ'DI ES ............................................................................................................... 6.1
6.1 Blade Structural Response ................................................................................... 6.1
6.2 Efficiencies for the High Pressure Compressor ............................................... 6.1
6.3 Mission S'llmmary ................................................................................................ 6.2
7.0 REFER.mCES .............................................................................................................. 7.1
APPENDIX A: DESCR1PTION OF DEMONSTRATION EXAMPLE ............................. A.1
A.1 Description of the Supersonic Engine ............................................................... A.1
A.2 Construction of Fan, Compressor and Turbine Blades ................................... A.3
A.3 Listing of supersonic. input ................................................................................... A.4
A.4 Listing of supersonic.maps .................................................................................... A.27
A.5 Listing of neutral.file ............................................................................................ A.48
APPENDIX B: DESCRIPTION OF AIRFOIL DATA BANK ............................................. B.l
B.l Airfoil Data Bank ....................... .......................................................................... B.1
~
B.2 Fonnat of the Airfoil Data Bank .......................................................................... B.4
B.2.1 AIRFOIL DEFWmON Format ........................................................................... B.4
B.2.2 Fl1LL BI.ADE D:EF'ThJl110N Fonnat .................................................................. B.I0
B.3 Listing of "airfoil.bank" file ................................................................................... B.16
TABLE OF CONTENTS (Continued)
APPENDIX C: T /BEST NEUTRAL FILE INPur & OUTPtIT ......................................... C.l
CI Module ............................................................................................... C.2
NEIITG~
C.2 NNEPWA1 'E Module ........................................................................................... C.l1
C3 NNEPPOST Module ..............................................................................•.............. C.12
C.4 Module ........................................................................................... C.14
B~Gm
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CS BLASW Module .................................................................................................... C.lS
C.6 BI..ASTh1J?OS1' Module ......................................................................................... C.16
C7 M1'SBGEl'J' Module ............................................................................................... C.17
C.S M1'SB Module ............................ ~ ........................................................................... C.IS
C.9 M'I'SBPOST Module .............................................................................................. C.19
C.l 0 NOISE Module ...................................................................................................... C.20
C.II PREDICl' Module. ................................................................................................. C.2l
C.12 RANGE Module ..................................................................................................... C.22
C.13 crrY Module ......................................................................................................... C.23
C.14 REPAIR. Module .................................................................................................... C.24
C.lS DOC Module ......................................................................................................... C.25
C.16 LCe Module .......................................................................................................... C.2B
C.17 FI..OPSGEN' Module ............................................................................................. C.30
C.IS FI..OPS Module ..................................................................................................... C.32
C.19 FI..OPSPOST Module ........................................................................................... C.33
APPENDIX D: T /BEST EXECUTIVE SYSTEM MISCELLANEOUS DATA ................. D.l
D.I Listing of the T /BEST UNIX Shell tbest.exe ....................................................... D.I
D.2 Listing of list.exefile .............................................................................................. D.IO
D.3 Database for predict Module ............................................................................... D.Il
DA Listing of the T /BEST Material Data Bank ........................................................ D.17
UST OF FIGURES
Figure Page
1.1 Default Computational Simulation Modules of
t:ll.e T/ BEST Executive System ................................................................................... 1.2
2.1 T /B~ Directory Tree ............................................................................................... 2.1
3.1 Engine Direct Operating Costs Pie Charts ............................................................ .3.9
4.1 Inter-Modular Olart for the T /BEST Executive System .......................................4 .1
6.1 Blade Structural Response: Static Root Stress Level
and MDE Failure Function ........................................................................................ 6.2
6.2 Blade Structural Response: Untwist and Uncamber ............. :. ............................... 6.3
6.3 Blade Modal Response: Natural Frequencies of the first Five Modes ................. 6.3
6.4 Compressor Efficiency Change Due to Loss ........................................................... 6.4
6.5 High Pressure Compressor Stages Overall Efficiency ........................................... 6.4
6.6 Mission Performance: Mach Number at Climb, Cruise, and Descent ................. 6.5
6.7 Missipn Performance: Aircraft Gross Weight at Climb,
Cruise, and Descent .................................................................................................... 6.5
A.1 Block Diagram of a Supersonic Research Engine ................................................... A.1
A2 Default Airfoil for Fan,. Compressor and Turbine Blades ... ____ .... __ .. _. .•.......... A.3
B.1 T /B~ Airfoil Data Bank for Fan, Compressor and Turbine Blades ................. B.2
B. . 2 Input Blade Details of an Unswept SR-2 Blade ....................................................... B.3
B. . 3 lx2y Airfoil Section Coordinate Input .................................................................... B.15
WELCOME TO TIBEST
1bis is the documentation on the T /BEST (Technology Benefit ESTimator) Users
and Programmers Manual. T /BEST which is operational on IRIS SGI
workstation is a computer software developed at NASA Lewis Research Center
for the benefit analysis of aerospace propulsion systems.
In T /BEST, the following capabilities are integrated:
- engine cycle analysis, engine sizing and weight estimation
- fan, compressor, and turbine blade structural analyses
- transonic fluid flow solution and efficiencies for each rotor
- noise estimation
- range estimation
- aircraft weight analysis
- city pairs determination
- direct operating cost
- aircraft repair requirements cost
- engine maintenance cost
- mission performance
TjBEST User's Manual i Welcome to TjBEST
SUMMARY
The Technology Benefit Estimator (T/ BES'D system is a formal method to assess
advanced technologies and quantify the benefit contributions for prioritization.
T /BEST may be used to provide guidelines to identify and prioritize high payoff
research areas, help manage research and limited resources, show the link
between advanced concepts and the bottom line, i.e., accrued benefit and value,
and to credibly communicate the ~efits of research.
The T /BESI' software computer program is specifically designed for estimating
benefits, and benefit sensitivities, of introducing new technologies into existing
propulsion systems. Key engine cycle, structural, fluid, mission and cost analysis
modules are used to provide a framework for interfacing with advanced
technologies. An open-ended, modular approach is used to allow for
modification and addition of both key and advanced technology modules.
T /BEST has a hierarchical framework that yields varying levels of benefit
estimation accuracy that are dependent on the degree of input detail available.
This hierarchical feature permits rapid estimation of technology benefits even
when the technology is at the conceptual stage. As knowledge of the technology
details increases the accuracy of the benefit analysis increases.
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":""
Included in T /BEST's framework are correlations developed from a statistical
data base that is relied upon if there is insufficient information given in a
particular area, e.g., fuel capacity or aircraft landing weight. Statistical
predictions _ are not required if these data are specified in the mission
requirements. The engine cycle, structural, fluid, cost, noise, and emissions
analyses interact with the default or user material and component libraries to
yield estimates of specific global benefits: range, speed, thrust, capacity,
component life, noise, emissions, specific fuel consumption, component and
engine weights, 'pre-certification test, mission performance engine cost, direct
operating cost, life cycle cost, manufacturing cost, development cost, risk, and
development time.
Currently, T /BEST operates on stand-alone or networked workstations, and uses
a UNIX shell or script to control the operation of interfaced FORTRAN based
analyses. T /BEST's interface structure works equally well with non-FORTRAN
or mixed software analyses. This interface structure is designed to maintain the
integrity of the expert's analyses by interfacing with expert's existing input and
output files. Parameter input and output data (e.g., number of blades, hub
diameters, etc.) are passed via T /BEST's neutral file, while copious data (e.g.,
finite element models, profiles, etc.) are passed via file pointers that point to the
experts' analyses output files. In order to make the communications between the
T /BESTs neutral file and attached analyses codes simple, only two software
TjBEST User's Manual it Summary
commands, PUT and GET, are required. This simplicity permits easy access to
all input and output variables contained within the neutral fue. Both public
domain and proprietary analyses codes may be attached with a minimal amount
of effort, while maintaining full data and analysis integrity, and security.
T /BEST's software framework, status, beginner-to-expert operation, interface
architecture, analysis module addition, key analysis modules are discussed.
Representative examples of T/ BEST benefit analyses are shown.
T/BEST User's Manual iii Summary
SECTION 1.0
INTRODUCTION
1.1 Leaming About TIBEST
Improvements in technology have contributed to the advancement of research in
the area of aerospace propulsion systems. To efficiently take advantage of these
advances, the need arises to communicate the benefits of advanced teclmology in
this research area. As a result, an effort was undertaken at NASA Lewis Research
Center to develop a computational simulation, T/BEST (Technology Benefit
ESTimator), that successfully integrates several disciplines in the area of
aerospace propulsion systems to yield the benefits in emissions, noise, weights,
thrust, range, specific fuel consumption, cost, etc.
T /BEST is an executive system developed for the benefit analysis of aerospace
propulsion systems. Figure 1.1 depicts the default computational simulation
modules of T /BEST. The executive system controls the execution of all modules
as well as the flow of information between modules. A computational module is
defined here as a FORTRAN (other languages may be included) program with a
specified analysis capability. All modules inter-communicate via a data bank
system named neutral.file.
The first and last analysis modules executed in T/BEST are, respectively,
NNEPWATE [Ref. 1] and FLOPS [Ref. 11]. Each module requires prior to
execution the availability of its standard input file(s). These files are generated
using built-in pre-processor in T/BEST with the exception of NNEPWATE where
these files are to be provided by the user. NNEPWATE sample input files will be
available in the fll'st release of T /BEST.
The disciplines integrated in T /BEST are:
1. thermodynamics
2. structures
3. fluid flow
4. cost
5. mission
6. emissions
7. noise
The T /BEST executive system conforms wi th three levels of user's expertise:
•
1. beginner, a first time user, is advised to execute T /BEST using the sample
example included in the first release (section 3.2).
T/BEST User's Manual 1.1 Introduction