Compressor and Turbine Models - Numerical Stability and Other Aspects

Abstract

This report deals with the mathematical-numerical models used at AEDC for the simulation of aircraft engine compressors and turbines. Numerical stability problems encountered in a one-dimensional compressor model (COMP2SP) have been eliminated with appropriate changes in the algorithm. A multi- dimensional finite volume code (ATAC), which simulates the operation of a turbine, has been analyzed, and the source of numerical oscillations in that code has been isolated. Subsequently, proper changes to the ATAC code have been made at AEDC and numerical oscillations have been eliminated. Stage characteristics based on the total pressure loss coefficient and the deviation angle as functions of incidence angle have been found to be less sensitive to errors in interpolation for intermediate speeds than the pressure and temperature co-efficients as functions of the flow coefficient. Multi- dimensional compressor model equations suitable for simulating the circumferentially distorted flows have been developed. Characteristics and compatibility equations are derived for the imposition of inflow and outflow boundary condition.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1985
Accession Number
ADA153811

Entities

People

  • K. C. Reddy
  • S. N. Nayani

Organizations

  • University of Tennessee Space Institute

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Angle Of Incidence
  • Classification
  • Coefficients
  • Compression
  • Compressors
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Mach Number
  • Pressure Distribution
  • Simulations
  • Static Pressure
  • Turbines
  • Two Dimensional

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Fluid Dynamics.