Numerical investigation of the response of axial flow compressor to circumferential total pressure distortion

Based on the given circumferential total pressure distortion of steady inlet flow,the response of an axial flow compressor rotor to the circumferential total pressure distortion of steady inlet flow was investigated numerically using 3-Dtime-accurate unsteady algorithm with the help of NWPU-1 axial flow compressor rig.The results show that,at 84 percent of design speed,the overall performance of compressor rotor is reduced due to distortion,with inlet flow circumferential distortion,the efficiency of ompressor rotor is decreased by 0.5 percent and the equivalent weight flow increases by 4.1 percent at near-stall condition if compared with clean inlet flow.Circumferential flow redistribution due to distortion tends to make the load of several blades too high,the blockage zone caused by tip leakage vortex is full of the whole passage,leading to the occurrence of stall.