叶尖小翼结合凹槽对压气机叶栅间隙流场的影响

Influence of Tip Winglet Combined With Tip Groove on the Leakage Flow of Compressor Cascade

为了揭示叶尖小翼结合叶顶凹槽对压气机叶栅性能及其间隙流场的影响,采用数值模拟方法对一低速压气机叶栅进行了研究。结果表明,不同宽度吸力面小翼均能控制叶顶泄漏流,减少叶尖泄漏损失。吸力面小翼与叶顶凹槽相结合,可以进一步削弱叶顶泄漏涡强度及降低叶栅损失。不同叶顶间隙尺寸的数值计算结果表明吸力面小翼结合叶顶凹槽降低了叶栅损失的间隙敏感性,具有较好的变间隙特性。

In order to reveal the effect of blade tip winglet combined with tip groove on the performance of compressor cascade and the clearance flow field, a low-speed compressor cascade was studied by numerical simulation method. The results show that the tip leakage flow can be controlled and the tip leakage loss can be reduced by suction-side winglet with different widths. The combination of suction wing and tip groove can further weaken tip leakage vortices and reduce cascade losses. The numerical results of different tip clearance size cases show that the suction-side winglet combined with tip groove reduces the clearance sensitivity of cascade loss and has better variable clearance characteristics.