跨、超声速吸附式压气机平面叶栅试验  

Experimental investigation of transonic and supersonic aspirated compressor cascades

作　　者：兰发祥[1,2] 周拜豪[2] 梁德旺 黄国平 

机构地区：[1]南京航卒航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司中国燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2010年第5期1123-1128,共6页Journal of Aerospace Power

摘　　要：对跨、超声速吸附式压气机平面叶栅进行了试验研究,试验针对若干抽气位置、抽气量和流动条件不同的叶栅工作状态进行,结果表明:一般在通道激波后、附面层分离前抽气对控制叶片附面层在逆压力梯度区的发展、抑制分离、降低叶栅损失、升叶栅气动性能有较明显的效果;在跨声速叶栅中,抽气量大于某个时抽气才能起到减小损失、改善性能的作用.The experimental investigation of a transonic and a supersonic aspirated compressor cascades was conducted in this paper. The aspirated compressor cascades were designed to improve the blade performance by sucking air on a slot. Various operating states were achieved by changing the slot location,the sucking air mass-flow,the sock location and the shock intensity. Generally,sucking air after the shock and before the separation had some beneficial effects in controlling the boundary separation and decreasing the loss. Then,the loading of blades was improved. The effects were especially prominent when there were strong shocks and strong boundary separations as a result of interaction between shock and boundary. There is a threshold of bleed air output for the transonic cascade,and also a threshold of sucking air mass-flow. Beyond it,suction can reduce the separation,weaken the loss and improve the performance.

关 键 词：涡轮发动机 吸附式压气机 试验 平面叶栅 抽气 

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]