摘要
为了进一步揭示吸力面叶尖小翼控制压气机叶栅间隙泄漏流动的作用机制,实验研究了三种不同宽度吸力面小翼在3%弦长间隙下对压气机叶栅气动性能的影响,并建立了带吸力面小翼的压气机叶栅旋涡结构模型。研究结果表明,吸力面小翼使得泄漏流在翼顶通道内发生掺混,延缓了泄漏涡的形成并降低了泄漏涡强度,三种宽度吸力面小翼分别使叶栅损失降低6.9%,7.7%和8.2%。吸力面小翼对叶栅损失值的降低量并不与其自身宽度增加量成线性关系。较大宽度的吸力面小翼会导致近端壁区气流欠偏转程度增加及泄漏流掺混损失等附加损失增大。
In order to further reveal the action mechanism of suction-side winglet controlling tip leakage flow in compressor cascade,detailed experimental investigations have been carried out. For a fixed tip gap of 3%chord,three kinds of suction-side winglets with different width were tested,and the vortex model of the compressor cascade with suction-side winglet was established. The results show that the tip leakage flow mixing occurs inside the tip gap above the winglet and the formation of tip leakage vortex is delayed. Meanwhile, the strength of tip leakage vortex is reduced. The loss coefficient is reduced by about 6.9%,7.7% and 8.2%,respectively,for the three kinds of suction-side winglet cases. The aerodynamic loss reduction by the suction-side winglet is not linear with the increase amount of winglet width. The suction-side winglet with a larger width increases the flow underturning degree near the casing and the additional losses made by leakage flow mixing process etc.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2016年第3期471-478,共8页
Journal of Propulsion Technology
基金
国家自然科学基金(51436002
51406021)
辽宁省教育厅科学研究一般项目资助(L2014197)
辽宁省高校创新团队支持计划资助(LT2015004)
中央高校基本科研业务费专项资金资助(3132015208
3132014319)
关键词
吸力面小翼
压气机叶栅
间隙流动
实验研究
Suction-side winglet
Compressor cascade
Tip leakage flow
Experimental investigation
