关键词: 压气机；总压畸变；整环；数值计算；气动稳定性

Abstract: In order to investigate the aerodynamic stability of transonic compressor with circumferential inlet total pressure distortion， a full annulus three-dimensional steady simulation of NASA Rotor37 with rotating circumferential total pressure distortion was carried out. The numerical results show that circumferential inlet total pressure distortion reduces the stall margin greatly. The stall margin is only 59% of uniform inlet flow at design speed. The total pressure and velocity under distortion region are lower than other area when distortion region rotates as the same speed of rotor. Tip leakage flow will spillage at leading edge and reverse at trailing edge when operation point closing to stall boundary and suction surface near tip region will come out boundary layer separation at the same time. Both tip leakage flow and suction boundary layer separation make compressor unstable. Circumferential inlet total pressure distortion will not change the position where the instability firstly takes place but the cause of instability can be affected.

Key words: Compressor；Total pressure distortion；Full annulus；Numerical simulation；Aerodynamic stability