Accession Number:

AD0884446

Title:

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

Descriptive Note:

Annual rept. no. 2, Mar 1970-Mar 1971

Corporate Author:

PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER

Report Date:

1971-03-01

Pagination or Media Count:

119.0

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.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines
  • Air Pollution and Control

Distribution Statement:

APPROVED FOR PUBLIC RELEASE