The engine with inter-stage turbine burner was computed in non-ideal cycle with F100-PW229 parameter.The differences of performance and thermal efficiency between inter-stage turbine burner and afterburner were compared;effect of component efficiency on the engine with inter-stage turbine burner was analyzed;combustion efficiency of main burner

inter-stage turbine burner

and after burner were contrasted.The result was different from the computation based on ideal cycle and it shows that thrust specific fuel consumption increases almost the same extent as the specific thrust after using inter-stage turbine burner on subsonic flight and specific thrust increases about 10% on supersonic;the economic performance is worse than base engine

and maneuverability is worse than engine with after burner.Then

the parameter of inter-stage turbine burner engine was optimized.