沈阳航空航天大学学报2016，Vol.33Issue(3)：11-17,7.DOI:10.3969/j.issn.2095-1248.2016.03.002
过失速点的带间隙叶栅流动结构
Flow structure with clearance in a Post-stall condition
摘要
Abstract
Unsteady condition of aero-engine compressor depends on the blade stall. Stall can lead to the sharp decrease in compressor performance. Investigation of flow field structure under the stall condition has important value in predicting the unstable phenomena of rotating stall. This article established a moving end-wall model based on NACA64-A905. The flow structure,in which clearance sizes were 2% c(c is the blade chord)and the stall incidences varied from -2° to 30°,was simulated numerically and further investigated by analyzing the velocities,the streamline and the static pressure at the post-stall condition. The results show that separation state of boundary layer is different,when the blade is in a post-stall condition. The leakage vortex can resist the boundary layer separation in blade tip region,whereas the passage vortex can promote the boundary layer separation in blade root region,hence the separation decreases gradually along the blade height. The blade root separation is more obvious as the incidence increases.关键词
压气机叶栅/移动端壁/过失速点/流动结构Key words
compressor cascade/moving end wall/post-stall/flow structure分类
航空航天引用本文复制引用
王建明,桂琳,马驰,王涵,陈超..过失速点的带间隙叶栅流动结构[J].沈阳航空航天大学学报,2016,33(3):11-17,7.基金项目
航空科学基金 （）
