吸力面小翼对扩压叶栅间隙泄漏的影响

The Influence of Suction-Side Winglet on Tip Leakage of Compressor Cascade

采用数值模拟方法对利用吸力面小翼方式控制压气机叶栅间隙流动进行研究。结果表明,附加吸力面小翼可以降低叶顶泄漏流速,削弱泄漏涡强度,使得泄漏涡区损失降低。不同宽度吸力面小翼在不同间隙下部可以较好地减少叶尖泄漏,在叶顶间隙为3.3%叶高时,附加相对宽度为0.5的吸力面小翼可使损失降低4.7%。叶顶压差的降低及对泄漏涡结构的改变是吸力面小翼降低泄漏掺混损失的主要原因。

A numerical study has been conducted to explore the effect of a suction-side winglet on tip leakage flow field of compressor cascade.The current results show that a significant tip leakage velocity and associated aerodynamic loss reduction is possible by using suction-side winglet.All of the winglet with different widths produce reduced tip leakage mass flow rate across the blade tip clearance with the variation of tip gap.The most effective tip geometry to reduce the tip leakage is SW0.5, which provides the most significant aerodynamic loss reduction about 4.7 percent at the large tip gap height.The reduction of pressure difference between pressure and suction sides of the blade and the compact tip leakage vortex structure are the main mixing losses reduction mechanisms of suction-side winglet.