An Investigation of Gas Turbine Combustors with High Inlet Air Temperatures. Part I: Combustor Modelling

Abstract

An analytical model has been developed which will predict the performance and pollutant emissions of gas turbine combustors. The entire gas turbine combustor is approximated as a collection of perfectly stirred zones. Within each zone a general hydrocarbon combustion mechanism is used to predict the gas composition and temperature. The zone volumes and sizes are assigned from consideration of the theoretically predicted gas flows thereby approximating the mixing behavior of the system. Selected predictions of the overall model for a 'typical' aircraft combustor are presented. These results are seen to be qualitatively accurate and fall in the range of values typically observed in practical systems.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1971
Accession Number
AD0884446

Entities

People

  • Arthur M. Mellor
  • Dean C. Hammond Jr.

Organizations

  • Purdue University

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Aircrafts
  • Burning Rate
  • Chemical Reaction Properties
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Combustors
  • Computer Programs
  • Dielectric Gases
  • Equations
  • Gas Turbines
  • Heat Transfer
  • Hydrocarbons
  • Ignition Lag
  • Pressure Distribution
  • Test And Evaluation
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion science or combustion engineering.
  • Computational Modeling and Simulation