Heat-Transfer Processes in Gas-Turbine Combustion Chambers

Abstract

The authors of this paper have analysed the relevant heat-transfer processes occurring in gas-turbine combustion chambers and have derived a general equation for flame-tube temperatures. This equation is used to determine the effect on flame-tube temperature of changes in the operating conditions of pressure, inlet temperature, and air mass flow. Changes in aircraft flight conditions, involving simultaneous changes in all these operating variables are also considered. Experimental evidence confirming the predictions of the general equation is provided. The paper concludes with a discussion on the influence on flame-tube temperatures of combustion-chamber design.