By means of computational fluid dynamics commercial software NUMECA

the effects of inlet distortion of different range on the performance

stability and flow-field in a subsonic axial-flow compressor were investigated with ten-annulus unsteady numerical method. The research object was the single-stage subsonic axial-flow compressor rotor of Northwestern Polytechnical University. The inlet distortion of different range was generated by setting some barriers on the inlet ring surface. Results showed that inlet distortion didnt only degrade the performance of the compressor rotor

but also decreased the stability of the rotor. And the larger distortion range indicated the more obvious phenomenon mentioned above. The fundamental flow mechanism was obtained by detailed analysis of the flow-field in rotor passage. Inlet distortion led to serious blockage in tip blade passage and further induced rotor stall because of the influence of the tip clearance leakage flow and the separation of boundary layer in some tip blade suction. Like above

the larger distortion range meant the more serious influence.