A three-dimensional model called compressor stability analysis code (CSAC) was preliminarily developed to assess the effect of inlet distortion on aerodynamic performance of compressor.By solving the three-dimensional compressible Euler equations with the source item

the annular flow field of compressor interior could be simulated.The blade force and power source item were calculated with the aerodynamic parameters extracted from the three-dimensional steady-state Navier-Stokes (N-S) solutions.The way for correlating the source item with inlet aerodynamic parameters was also given. The aerodynamic performances of NASA Rotor 37 under clean inlet condition were calculated and analyzed with this model

the result under clean inlet was also compared with three-dimensional steady-state N-S solutions under the same inlet conditions. The accuracy of this model was verified.Finally

the performance of Rotor 37 under steady circumferential total pressure distortion was simulated.Results show that

total pressure distortion not only reduces the performance and the stability

but also induces total temperature distortion at the exit of compressor rotor.The research shows this model can correctly reflect the effect of distortion on compressor with much less compute resources

proving that this model is a suitable tool for compressor distortion analysis in current period.