DI-MISC-80672.pdf

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DI-MISC-80672 HI 7777787 0002373 7

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!.. TITLE

as Turbine nigine Steady State and Transient Performance resentations for Digital Computer Programs

DATA ITEM DESCRIPTION

i. IDENTIFICATION NUMBER

DI-MISC-80672

l. APPROVAL DATE 5 OFFICE OF PRIMARY RESPONSIEILITY (OPR) 6r . OTIC REQUIRED

F/AFSC-ASD (WMMDD)

880811

1. APPROVAL LIMITATION 9r. APPLICABLE FORMS 9b. AMSC NUMBER

6b. GIDEP REQUIRED

I F4520

IO. PREPARATION INSTRUCTIONS

10.1 Reference documents. The applicable issue of the docunents cited herein, including :heir approval dates and dates of any applicable amendwnts, notices, and revisions, shall be 3s specified in the contract.

19.2 General requirements.

L0.2.1 htanotive Engineers Standard AS 6811)-82, "Gas Turbine kigine Steady State Performance Presentation for Digital Computer Programs," for steady state Models or the Society of 4utcmotive kigineers Recomnended Practice ARP 1257-72, "Gas Turbine Engine Transient Ferformance Presentation for Digital Computers," for transient Models.

Except as modified herein, the Models shall conform to either the Society of

10.2.2 zapable of being compiled and executed on the canputer system identified by the Using Service.

zomputer upon which the Models will be installed to obtain the official engine performance iata.

The Models shall be written and provided in FORTRAN 77 source language, and shall be

The Using Service shall specify the manufacturer, model, and location of the

10.2.3 designation, manufacturer's name, engine specification number, revision date, and Model identification number.

The Models shall carry suitable identification including the engine model

(Continued on Page 2) i i, DISTRIBUT~~ONITATEMENT

DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.

bD Form 1664, JUN 86 Previous editions are obsdete. PAGE 1 OF 2 PAGES

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DI-MISC-80672

B l o c k 10, Preparation Instructions (Continued)

10.2.4 maintained (i .e., the fan, axial compressor, centrifugal compressor, each turbine, combustor, augmentor, fan duct, ard each exhaust nozzle must be identified as entities in the Model logic) as required to obtain and maintain an accurate simulation.

The Models shall be thermodynamic cycle simulations in which cmpnent identity is

10.2.5 state Models and within the precision requirements of ARP 1257-72 for transient Models.

The Models shall agree within the precision requirements of AS 681D-82 for steady

1i8,2.6 Input test cases shall be provided with the Models to adequately verify the capabilities and opration of the Models prior to acceptance by the Using Service.

The Models shall be capable of operating throughout the engine operating envelope.

10.2.7 Engineers Recmended Practice ARP 755A-74, "Gas Turbine Engine Performance Station Identification and Nomenclature".

Internal program nomenclature shall be in accordance with Society of Automotive

18.3 Documentation requirements.

10.3.1 internal documentation (i.e., detailed cment statements) within the program code to identify the subroutines and their logic.

program shall be magnetic tape, and a source program listing shall k provided.

The source program shall include all program subroutines, and shall have sufficient

The physical medium us& to store the source

B@,3.2 ïnputs/ûutguts,

10.3.2.1 the output data.

made in the output for declassification and authority information.

NAMELIST.

The Model shall be so organized that the input data shall print out separately from Output shall include engine and Model designations. Provision shall be

Model input shall be via

10.3.2.2 In addition to the inputs listed in AS 681û-82 for steady state Models and in ARP 1254-72 for transient Models, provisions shall be made for the input of fuel lower heating value, and either net thrust for turbojet/turbofan engines or output shaft speed with shaft horsepower fer turboprop/turboshaft engines.

10.3.2.3 used to niodify the major parameters for each of the engine canponents.

available on all cmpnent efficiencies, burner pressure loss, duct pressure losses, intermediate case pressure loss, nozzle discharge coefficient, and all leakages and cooling flows.

The Model shall also be capable of providing expanded input for adders and scalars Adders shall be made

Scalars shall be made available on turbine flow parameters.

10.3.2.4 evaluation and calculations must be available as output without reprogramning.

10.3.2.5 foot system.

Control and aerothermcdynamic cycle parameters used in component performance

The units used on the input and output parameter values shall be based on the poma, Page - 2 of - 2 Pages

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