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  

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

作　　者：吴虎[1] 贾海军[1] 黄健[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安7100072

出　　处：《航空动力学报》2006年第3期437-441,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助(10377013);航空科学基金资助(02C53022)

摘　　要：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。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 stabil- ity. 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.

关 键 词：航空 航天推进系统 轴流压气机 总压畸变 传递特性 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]