Investigation of Endwall Flow Behavior with Plasma Flow Control on a Highly Loaded Compressor Cascade  

作　　者：Xiaohu ZHAO Yinghong LI Yun WU Jun LI 

机构地区：[1]Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi' an 710038, China

出　　处：《Journal of Thermal Science》2012年第4期295-301,共7页热科学学报（英文版）

基　　金：provided by National Natural Science Foundation of China (No. 50906100 and 10972236);Foundation for the Author of National Excellent Doctoral Dissertation of PR China (No. 201172);Postgraduate Technology Innovation Foundation of Air Force Engineering University (No. DX2010103)

摘　　要：To discover the flow behavior in the endwall region and mechanism of plasma flow control on a highly loaded compressor cascade, distributions of static pressure coefficient, total pressure loss coefficient and streamline pat- tern were investigated. Results show that cross flow from the pressure surface to neighboring suction surface ex- ists under pitch-wise pressure gradient. The deflected endwall boundary layer flow interacts with the incoming flow, and then both of them leave off the endwall in tile form of a span-wise vortex. Effect of angle of attack on static pressure is greater than that of free stream velocity. The distinct variations of total pressure loss with end- wall actuations are mainly located within the outer verge of a triangular area with high total pressure loss. Effect of pitch-vAse actuation on separated flows is much better than that of stream-wise actuation, and both enhance with the increase of angle of attack and actuation strength. An efficient method for plasma flow control in the endwall region is the increase of actuation strength, such as adjusting discharge voltage or changing plasma power supply.

关 键 词：plasma flow control COMPRESSOR CASCADE endwall region VORTEX 

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] TF777[冶金工程—钢铁冶金]