Abstract:In order to study the influence of tip clearance on the aerodynamic performance of the compressor in the stage environment, this paper takes the supersonic compressor stage with guide vanes as the research object, and the commercial software NUMECA was used to carry out three-dimensional numerical calculation of the compressor when the tip clearance of the rotor is 0.0 mm, 0.3 mm, 0.6 mm and 0.9 mm, and analyzed the aerodynamic performance and flow characteristics of the compressor stage. The results show that: with the increase of tip clearance, the shock wave at the rotor tip moves upstream; the angle of attack of the inlet flow of stator increases; finally, the compressor stability margin, the efficiency of rotor peak point and the low loss range of stator decrease. The tip clearance has little effect on the performance of the inlet guide.