涡流发生器对高负荷扩压叶栅性能影响的机理分析  

Mechanism Analysis of Effects of Vortex Generator on High-Load Compressor Cascade

作　　者：吴培根[1] 王如根[1] 郭飞飞[1] 胡加国[1] 李坤[1] 

机构地区：[1]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《推进技术》2016年第1期49-56,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(50906100)

摘　　要：为探明涡流发生器流动控制技术对高负荷扩压叶栅性能影响及作用机理,根据高负荷扩压叶栅的流动特点,提出了在叶栅入口端壁处加涡流发生器的流动控制方案,通过计算研究了采用涡流发生器前后叶栅气动性能、附面层及主要旋涡结构的变化。研究结果表明:采用涡流发生器后,叶栅正攻角下的气动性能显著提升,总压损失减小,静压升增大,稳定工作最大正攻角从3°增加至5°,其中在3°攻角下总压损失系数下降0.028,静压系数提升0.033;涡流发生器生成的尾涡阻挡端壁附面层由压力面向吸力面的横向迁移,使吸力面/端壁区域聚集的低能流体减少,改善了角区流动;采用涡流发生器后,通道涡、集中脱落涡和壁角涡减弱,角区分离得到抑制。Based on the flow characteristics of high load compressor cascade, the flow control scheme of using vortex generator applied in front of the end wall of cascade was proposed. Numerical simulations were carried out to explore the effects of vortex generator on performance of high load compressor cascade and the action mechanism of flow control. The alterations were analyzed on the cascade aerodynamic performance,the boundary layer and the principal vortices. The results show that the aerodynamic performance under the positive attack angle of cascade improves by means of vortex generators. Furthermore it decreases the total pressure loss,raises the static pressure ratio and increases the stable maximum positive incidence from 3° to 5°. In the incidence of3°,the total pressure loss coefficient decreases 0.028 and the static pressure coefficient increases by 0.033. Vortex generator obstructs the migration of boundary layer at the end wall from pressure to suction side, which makes the low energy fluid accumulated in the suction surface and the end wall region decreases,and then improves corner flow. After using the vortex generator,the development of the passage vortex,concentrated shed vortex and corner vortex is most effectively controlled,and then the corner stall is restrained.

关 键 词：高负荷扩压叶栅 涡流发生器 二次流动 旋涡结构 角区分离 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]