Turbojet and turbofan engine performance increases through turbine burners

In a conventional turbojet and turbofan engine, fuel is burned in the main combustor before the heated high-pressure gas expands through the turbine, A turbine-burner concept was proposed in a previous paper in which combusti on is continued inside the turbine to increase the efficiency acid specific thrust of the turbojet engine, This concept is extended to include not onl y continuous burning in the turbine but also "discrete" interstage turbine burners as an intermediate option, A thermodynamic cycle analysis is perfor med to compare the relative performances of the conventional engine and the turbine-burner engine with different combustion options For both turbojet and turbofan configurations, Turbine-burner engines are shown to provide si gnificantly higher specific thrust with no or only small increases in thrus t specific Fuel consumption compared to conventional engines, Turbine-burne r engines also widen the operational range of Right Mach number and compres sor pressure ratio, The performance gain of turbine-burner engines over con ventional engines increases with compressor pressure ratio, fan bypass rati o, and Right Mach number.