压气机端壁自适应流通延迟失速的数值分析  

Numerical investigation of the flow mechanisms of compressor stall delay through end wall self recirculation

作　　者：张皓光[1] 楚武利[1] 吴艳辉[1] 高鹏[1] 曹玉吉[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]第二炮兵工程学院,陕西西安710025

出　　处：《推进技术》2009年第2期202-208,共7页Journal of Propulsion Technology

基　　金：航空科学基金(05C53016);国家自然科学基金(50506026)

摘　　要：端壁自适应流通方式是轴流压气机主动控制失速方法的有效措施之一,即在机匣上结合喷气与引气的方式来延迟压气机的失速,其特点是自适应流通的喷气或吹气量将随压气机的工况自我调整。采用数值模拟方法研究了端壁自适应流通方式对某轴流压气机气动性能的影响,数值计算结果表明,端壁自适应流通方式能有效地延迟失速并略微提高压气机的效率,通过详细地分析端壁自适应流通方式对压气机顶部区域流场结构的影响,揭示了其改善压气机性能的机理。End wall self recirculation is known as an active method to control stall in axial compressors. It is implemented by combining injection and bleed on the compressor shroud and has the characteristic of injection or bleed quantity self adjusting with the compressor work point varying. Effect of end wall self recirculation on the performance of an axial-flow rotor was performed with the help of numerical method. The numerical results show that end wall self recirculation method can not only suspend the stall effectively but also improve the compressor efficiency appreciably. The fundamental flow mechanism of end wall self recirculation reforming the compressor performance was obtained by detailed analyzing the flow fieid at the blade tip.

关 键 词：轴流压气机 自适应流通^+ 失速 流场 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]