变冲角下吸力面小翼对压气机叶栅气动性能的影响  

Effects of Suction-Side Winglet on Aerodynamic Performance of Compressor Cascade at Different Incidences

作　　者：韩少冰[1] 钟兢军[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《推进技术》2012年第3期384-390,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(51076018)

摘　　要：为了进一步揭示吸力面小翼对压气机叶栅间隙流动的影响机理,采用数值模拟方法对压气机叶栅加装吸力面小翼控制间隙流动进行研究,着重考察了吸力面小翼在不同来流冲角下(-5°、0°、+3°)对叶栅气动性能的影响。结果显示,负冲角时,吸力面小翼有效降低了叶尖泄漏损失及遏制了压力面分离。随着冲角增加,叶顶最大压差作用区向叶栅上游移动,泄漏涡与通道涡的相互作用增强,吸力面小翼对叶栅气动性能的改善逐渐降低。In order to further uncover the effects and action mechanics of the suction-side winglet on the tip leakage flow of the compressor cascade,the numerical simulation has been carried out to investigate the effects of suction-side winglet on controlling tip clearance flow in an axial compressor cascade.Emphasis is put on the analysis of effectiveness of suction-side winglet when the approaching flow is at different incidences（-5°,0°,＋3°）.The simulation results show that,at negative incidence,the suction-side winglet can reduce the cascade aerodynamic loss significantly and the boundary separation on pressure surface can be effectively controlled by using suction-side winglet.With the increase of incidence,the region under the effect of pressure difference extends towards the blade leading edge,and the interaction between leakage vortices and passage vortex is intensified.The improvement of suction-side winglet on the aerodynamic performance decreases gradually.

关 键 词：压气机叶栅 冲角 吸力面小翼 间隙流动 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]