跨声速双级轴流压气机对周向进气总压畸变的响应特性分析

基于所建立的总压畸变矩阵传递模型,对周向总压畸变下某型跨声速双级轴流压气机容畸变特性进行了详细的数值分析,揭示出了多级环境下轴流压气机对进气畸变的衰减/增益变化规律,这对理解增强多级轴流压气机抗压力畸变能力机理,提高多级轴流压气机性能和扩大其稳定工作范围意义明显.

Response of an Transonic Two-Stage Compressor to Steady Circumferential Total Pressure Distortions

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.