EXPERIMENTS OF PLASMA ACTUATION BASED COMPRESSOR CASCADE FLOW SEPARATION SUPPRESSION
Compressor cascade experiments were conducted to investigate the technical measures for plasma flow control technology based compressor passage flow control. A compressor cascade experiment system based on NACA 0065 blade profiles is developed, based on which the required compressor cascade flow control system is constructed, in combination with existing plasma flow control system. The experiment results demonstrate that at the Reynolds numbers of 34.4 K and 48.6 K respectively, with an incidence of 37.2 degree, the open large-scale separated compressor cascade passage flow can be suppressed effectively, and the separated passage flow field can also be improved greatly owing to the flow disturbances induced by the plasma actuators mounted on the suction surface of the cascade blade. Further analysis shows that the plasma flow control technique has potential prospects of being used on the next generation advanced aeroengines.
LI Ying-hong Song Hui-min WU Yun ZHANG Pu WEI Feng-ting SUN Dong SU Chang-bin
Engineering College, Air Force Engineering Univ.,Xian, China Air Force Engineering Univ., Xian, China
国际会议
昆明
英文
430-432
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）