旋流畸变对压气机失速发展过程影响的试验研究  

Experimental Investigation of Compressor Stall Development Induced by Inlet Swirl Distortion

作　　者：刘华 屠宝锋 胡骏 谢金哲 

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,江苏南京210016 [2]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2017年第10期2306-2313,共8页Journal of Propulsion Technology

基　　金：航空科学基金(2015ZB52018)

摘　　要：为研究进气旋流畸变对轴流压气机失速发展过程的影响,设计了一种叶片式旋流畸变发生器。通过改变叶片式旋流畸变发生器的叶片安装方式来改变进口气流流向,产生对涡或整体涡,研究均匀进气、对涡和整体涡进气条件下低速轴流压气机失速发展的特点。试验结果表明:旋流畸变发生器达到了预期的设计要求,在压气机进口前产生了对涡和整体涡。压气机转子对进口旋流畸变有很大的影响,对正向旋流有一定加强作用,使正向旋流强度增大;对反向旋流有一定抑制作用。旋流畸变减小了压气机的稳定裕度,切向气流角越大效果越明显,使其更快进入失速,其中以对涡进气和正向涡进气条件下最为明显。旋流畸变进气条件下压气机中失速团的产生机理不发生改变,失速团传播频率不发生改变。In order to investigate the effect mechanism of swirl distortion inlet flow on stall development of axial compressor,a blade swirl distortion generator was designed. The angle of blades of swirl distortion generator was changed to influence the inflow conditions,which were to develop into twin swirl or bulk swirl,researching the twin swirl or the bulk swirl inflow on the rotating stall development of a low speed axial compressor. The results show that the generator realizes the prospective goal,which produce twin swirl and bulk swirl. The rotor has a great influence on the inlet swirl distortion flow,which has a certain effect on the forward flow,increasing the strength of the forward swirl and having a certain inhibition effect on the reverse flow. Swirl distortion decreases the stability margin of a compressor,the big angle of incidence expands its influence to the inflow which shorten the time from stall inception to full stall,which means stronger intensity of the swirl distortion will decrease the stability of the compressor,making it easy fall into stall,especially for the twin swirl and positive swirl conditions. Under the condition of swirl distortion,the compressor stall cell mechanism is not changed,so as to the propagation frequency of the rotating stall.

关 键 词：叶片式旋流畸变发生器 对涡 整体涡 失速起始 

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]