Turbojet and Turbofan Engine Performance Increases Through Turbine Burners

Abstract

In a conventional turbojet and turbofan engine, fuel is burned in the main combustor before the heated highpressure gas expands through the turbine. A turbine-burner concept was proposed in a previous paper in which combustion is continued inside the turbine to increase the efe ciency and speciec thrust of the turbojet engine. This concept is extended to include not only continuous burning in the turbine but also “discrete” interstage turbine burners as an intermediate option. A thermodynamic cycle analysis is performed to compare the relative performances of the conventional engineand theturbine-burner engine with differentcombustion options for both turbojet and turbofan conegurations. Turbine-burner engines are shown to provide signie cantly higher specie c thrust with no or only small increases in thrust specie c fuel consumption compared to conventional engines. Turbine-burner engines also widen the operational range of e ight Mach number and compressor pressure ratio. The performance gain of turbine-burner engines over conventional engines increases with compressor pressure ratio, fan bypass ratio, and eight Mach number.