Based on Moore-Greitzer model

a nonlinear multi "actuator disk" model was proposed to analyze the dynamic behavior of aerodynamic instabilities in high speed multistage axial compressors for both cases with and without rotating inlet distortion.The model described the duct flow fields using two dimensional

compressible and unsteady Euler equations

and accounted for the influences of downstream plenum and throttle in the system as well.It replaced each blade row of compressors with a disk.The main purpose of this work is to predict the mechanism of two-dimensional short wavelength rotating stall inception

the interaction between blade rows in high speed multistage compressors

and the influence of rotating speed of inlet total pressure distortion on the onset of flow instability.Some qualitative comparisons with available experimental results were made in this paper

showing that the model and results are reliable.