首页|期刊导航|哈尔滨工业大学学报（英文版）|Aerodynamic performance of high-turning curved compressor cascade with boundary layer suction
哈尔滨工业大学学报（英文版）2007，Vol.14Issue(3)：341-348,8.
Aerodynamic performance of high-turning curved compressor cascade with boundary layer suction
Aerodynamic performance of high-turning curved compressor cascade with boundary layer suction
摘要
Abstract
The impact of boundary layer suction on the aerodynamic performance of a high-turning compressor cascade was numerically simulated and discussed. The aerodynamic performance of a curved and a straight cascade with and without boundary layer suction were comparatively studied at several suction flow rates. The results showed that boundary layer suction dramatically improved the flow behavior within the flow passage. Moreover, higher loading over the whole blade height, lower total pressure loss, and higher passage throughflow were achieved with a relatively small amount of boundary layer removal. The integration of curved blade and boundary layer suction contributed to better aerodynamic performance than the cascades with only curved blade or boundary layer suction used, and the more favorable effect resulted from the weakening of the three dimensional effects of the boundary layer close to the endwalls.关键词
high-turning compressor cascade curved blade boundary layer suctionKey words
high-turning compressor cascade curved blade boundary layer suction分类
航空航天引用本文复制引用
CHEN Fu,CHEN Huan-long,SONG Yan-ping,WANG Zhong-qi..Aerodynamic performance of high-turning curved compressor cascade with boundary layer suction[J].哈尔滨工业大学学报（英文版）,2007,14(3):341-348,8.基金项目
Sponsored by the National Natural Science Foundation of China( Grant No. 50646021 ). （ Grant No. 50646021 ）
