Some Aspects on Increasing Gas Turbine Combustor Exit Temperature

A high turbine inlet temperature promotes the gas turbine overall cycle efficiency. Problems arising in the combustion system when increasing the temperature are discussed. A high exit temperature aircraft gas turbine combustor was designed by deleting the dilution air in a double recirculation zone combustor. Rig test were carried out and comparisions were made with a reference combustor of conventional design. It was found that the overall fuel-air ratio could be increased from 0.0182 to 0.0315 without imparing the emission characteristics or the combustion efficiency at any power setting. The exit temperature pattern factor was improved by providing a proper fuel and air mixing.