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.