Regression Simulation of Turbine Engine Performance (RSTEP).

Abstract

The results of developing six alternate calculation procedures for parametric turbine engine performance computer programs is presented. The alternate procedures were evaluated separately and then collectively in a baseline parametric engine performance program. The alternate procedures dealt with thermodynamic properties, matrix coefficient prediction, regression of component characteristics, afterburner calculations and regression of the compression process. Analysis of the combined procedures resulted in a cost reduction of approximately 46 percent with average deviations in engine net thrust and fuel flow rate of less than 0.7 percent. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1979
Accession Number
ADA071400

Entities

People

  • Richard A. Sulkoske
  • Robert E. Clark

Organizations

  • General Motors

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Additives (Chemicals)
  • Air Force
  • Aircrafts
  • Algorithms
  • Central Processing Units
  • Combustion
  • Combustion Products
  • Compressors
  • Computer Programs
  • Computers
  • Cost Reductions
  • Databases
  • Gas Turbines
  • Geometry
  • Regression Analysis
  • Thermodynamic Properties
  • Turbines

Readers

  • Aerospace Engineering
  • Computational Modeling and Simulation