Stall prediction of in-flight compressor due to flamming of refueling leakage near inlet

摘要

The propagation of strong distortion at inlet of an axial compressor is investigated by applying the critical distortion line and the integral method. The practical applications, such as the inlet conditions of flaming of leakage fuel during mid-air refueling process, are implemented to show the details of the numerical methodology used in analysis of the axial flow compressor behavior and the propagation of inlet distortion. From the viewpoint of compressor efficiency, the propagation of inlet flow distortion is further described by a compressor critical performance and its critical characteristic. The simulated results present a useful physical insight to the significant effects of inlet parameters on the distortion extension, velocity, and compressor characteristics. The distortion level, incidence angle and the size of distortion area at compressor inlet, and the rotor blade speed are found being the major parameters affecting the mass flow rate of engine.