Abstract: An important component of the gas turbine engine is its axial flow compressor system.With the advent of high maneuvering aircraft with weapon release in the vicinity of the engine inlets,there will always exist inlet total pressure distortions.So,in today’s military turbine engines,their axial compressors must be capable of stable operation despite of severe inlet total pressure distortion.Many experimental and analytical investigations have been conducted in the past four decades to quantify the effects of distorted inlet flow on axial compression system stability.A transfer matrix model was used to predict the response of a transonic two-stage axial flow compressor to steady circumferential total pressure distortions.The effects of multistage environment on the response of an axial flow compressor to steady circumferential total pressure distortion were found.Comparison with those of the two-stage compressor,great attenuation of the total pressure distortion,static pressure distortion and the weakening of the incidence angle changes were produced by isolated single stage.A good agreement was obtained by comparing the numerical results with experimental data.Suggestions were also made to utilize this method for the design of distortion-tolerant multistage axial compressors.