Abstract
Inlet performance with the back pressure in the TBCC(Turbine-Based Combined Cycle) is analyzed in order to study a stable start of the turbojet engine. A reliable back-pressure boundary condition using total pressure extrapolation method is proposed to investigate the inlet performance and to obtain the turbojet compressor effect in high accuracy. Numerical results show that the location of flow separation of subsonic diffuser can be decided by the subsonic diffuser angle and the bleed effect. In low back-pressure, the total pressure recovery of the turbojet is very low because the terminal shock has relatively strong strength. In high back-pressure, the mass capture ratio is low because of the large amount of the bleed flow rate. Considering the stable flight of TBCC, a range of back pressure may exist even in the critical condition depending on the performance of the engine itself.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
