进口总压畸变对压气机性能及流场影响的机理研究  

A Study of the Mechanism of the Influence of Inlet Total Pressure Distortion on Compressor Performance and Its Flow Field

作　　者：张皓光[1] 楚武利[1] 吴艳辉[1] 苏中亮[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《机械科学与技术》2010年第7期880-885,共6页Mechanical Science and Technology for Aerospace Engineering

基　　金：中国博士后科学基金项目(20090451395);航空基金项目(2007ZB53021);航空科技创新基金项目(08B53004)资助

摘　　要：采用全三维非定常数值方法研究进口周向总压畸变对轴流压气机转子性能及内部流场的影响,数值结果表明进口周向总压畸变后不仅降低压气机的稳定裕度,也使压气机等熵效率减少。通过详细地分析压气机内部流场,揭示了进口周向总压畸变对该压气机转子性能及流场影响的机理,即进口周向总压畸变后,明显降低50%～100%叶展内的气流进气角。同时增强产生叶尖泄漏运动的驱动力,提前使叶顶间隙泄漏涡涡核破碎,造成高的堵塞,最终触发压气机失速。Effect of inlet circumferential total pressure distortion on the performance and flow field of an axial-flow rotor is studied with the help of 3D unsteady numerical method.The numerical results show that inlet circumferential total pressure distortion not only debases the steady operating range of compressor but also considerably decreases the compressor efficiency.The flow mechanisms of the numerical simulation obtained by detailed analysis of the flow-filed in the compressor indicates that：（1） The magnitudes of flow inlet angle between 50% to 100% blade span is decreased obviously with inlet circumferential total pressure distortion;（2） inlet circumferential total pressure distortion makes the blade tip load increase and consequently improves the driving power of tip leakage flow,thus making the eddy of tip leakage vortex break down ahead of schedule,which induces the blockage in blade passage and the springing of the stall of the compressor.

关 键 词：总压畸变 轴流压气机 性能 流场 机理 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]