Effects of Boundary Layer Suction on Aerodynamic Performance in a High-load Compressor Cascade  

附面层抽吸对高负荷扩压叶栅气动性能影响的实验研究(英文)

作　　者：郭爽[1] 陈绍文[1] 宋彦萍[1] 宋宇飞[1] 陈浮[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院

出　　处：《Chinese Journal of Aeronautics》2010年第2期179-186,共8页中国航空学报（英文版）

基　　金：National Basic Research Program of China (2007CB210100);National Natural Science Foundation of China (50876023);Chinese Specialized Research Fund for the Doctoral Program of Higher Education (20060213007)

摘　　要：This article is aimed to experimentally validate the beneficial effects of boundary layer suction on improving the aerodynamic performance of a compressor cascade with a large camber angle. The flow field of the cascade is measured and the ink-trace flow visualization is also presented. The experimental results show that the boundary layer suction reduces losses near the area of rnidspan in the cascade most effectively for all suction cases under test. Losses of the endwall could remarkably decrease only when the suction is at the position where the boundary layer has separated but still not departed far away from the blade surface. It is evidenced that the higher suction flow rate and the suction position closer to the trailing edge result in greater reduction in losses and the maximum reduction in the total pressure loss accounts to 16.5% for all cases. The suction position plays a greater role in affecting the total pressure loss than the suction flow rate does.This article is aimed to experimentally validate the beneficial effects of boundary layer suction on improving the aerodynamic performance of a compressor cascade with a large camber angle. The flow field of the cascade is measured and the ink-trace flow visualization is also presented. The experimental results show that the boundary layer suction reduces losses near the area of rnidspan in the cascade most effectively for all suction cases under test. Losses of the endwall could remarkably decrease only when the suction is at the position where the boundary layer has separated but still not departed far away from the blade surface. It is evidenced that the higher suction flow rate and the suction position closer to the trailing edge result in greater reduction in losses and the maximum reduction in the total pressure loss accounts to 16.5% for all cases. The suction position plays a greater role in affecting the total pressure loss than the suction flow rate does.

关 键 词：TURBOMACHINERY boundary layer suction high-load diffusion cascade experimental investigation 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]