端壁采用孔式抽吸对扩压叶栅气动性能的影响  

Effects of End-Wall Taking Hole-Suction on Aerodynamic Performance of a Compressor Cascade

作　　者：张龙新[1] 陈绍文[1] 郭昊雁[2] 杜鑫[1] 王松涛[1] 

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心,黑龙江哈尔滨150001 [2]中国航天科工集团三十一研究所,北京100074

出　　处：《推进技术》2013年第9期1204-1208,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(51206035);国家自然科学基金创新研究群体项目(51121004)

摘　　要：为明晰孔式附面层抽吸技术对压气机叶栅气动性能的作用效果,实验研究了在端壁不同位置设置抽吸孔时对大折转角扩压叶栅壁面流谱、出口二次流及损失的影响。研究结果表明,端壁抽吸改变了原型叶栅内部流场结构,角区分离起始点前进行附面层吸除可有效延缓通道涡的形成,降低叶栅损失;分离起始点之后角区分离已经充分发展的位置不宜布置抽吸孔;相比较抽吸槽,采用抽吸孔可以通过更少的抽吸量达到相同程度地对叶栅流动性能的改善。In order to uncover the effects of hole-suction on the aerodynamic performance of a compres- sor cascade, detail experimental research was carried out. The effects of taking hole-suction at different lo- cation in the endwall on the flow pattern, outlet loss contour and distribution of secondary flow vectors of the large turning cascade were obtained. As a result, flow filed of original cascade is changed while applying boundary layer suction. Suction before corner separation delays passage vortex happening and reduces the loss of original cascade. Suction after corner separation which is fully developed is not advised. As the total suction massflow is given, taking hole-suction may pronounce a better aerodynamic performance than taking slot-suction.

关 键 词：扩压叶栅 附面层抽吸 抽吸孔 抽吸位置 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]