Unsteady Analysis of Hot Streak Migration in a Turbine Stage

Abstract

Experimental data taken from gas turbine engines has shown that hot streaks exiting combustors can have a significant impact upon the secondary flow and wall temperature of the first stage turbine rotor. Understanding the secondary flow and heat transfer effects due to combustor hot streaks is essential to turbine designers attempting to optimize turbine cooling systems. A numerical investigation is presented which addresses the issues of multi-blade count ratio and three-dimensionality effects on the prediction of combustor hot streak migration in a turbine stage. Keywords: Gas generator engines, Gas turbine rotors, Unsteady flow.

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Document Details

Document Type
Technical Report
Publication Date
Jul 18, 1990
Accession Number
ADA225213

Entities

People

  • Daniel J. Dorney
  • David E. Edwards
  • Nateri K. Madavan
  • Roger L. Davis

Organizations

  • American Institute of Aeronautics and Astronautics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Free Stream
  • Gas Turbines
  • Heat Transfer
  • Isotherms
  • Pressure Distribution
  • Surface Temperature
  • Temperature Coefficients
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Combustion Dynamics and Shock Wave Physics.
  • Internal Combustion Engine (ICE) Technology.