叶尖小翼调控压气机叶栅间隙流场结构的试验研究

Experimental Study of Blade Tip Winglet on Tip Clearance Flow in Compressor Cascade

在低速条件下,对叶尖不同位置安装小翼的压气机叶栅流场进行试验研究。通过端壁静压孔对上端壁流场进行测量,叶栅出口流场利用五孔气动探针测量,细致分析不同安装方式叶尖小翼对压气机叶栅叶尖端区流场结构、气动损失和通流能力的影响。结果表明,不同安装方式的叶尖小翼对压气机叶栅间隙流场影响不同。与无叶尖小翼的常规叶栅相比,吸力面小翼使得叶栅损失降低的同时带来了流动堵塞的降低,压力面小翼使得叶栅损失和流动堵塞同时增加,组合小翼在降低叶栅损失的同时有效降低了叶栅的流动堵塞,改善了叶栅的通流能力。通过与常规叶栅叶尖区域流场结构的详细对比分析,对不同安装方式的叶尖小翼的影响机理做出解释。

The detailed experimental study on compressor cascade with three kinds of blade tip winglets has been carried out in low speed condition. The endwall flow fields are measured by static pressure taps. And the outlet flow fields of the cascade are obtained by five-hole aerodynamic probe. The effect of the blade tip winglet on the flow filed, total pressure loss and the flow capacity of the cascade are analyzed in detail. The results show that the blade tip geometry significantly affects the tip clearance flow field. Compared to the conventional cascade without blade tip winglet, the total loss can be reduced by the suction-side winglet, and the outflow blockage is reduced. The pressure-side winglet has little advantages over the baseline tip in reducing the overall losses and improving the flow capacity of the cascade. The combined winglet tip can positively affect the aerodynamic filed of the cascade by reducing the overall losses and improving the flow capacity. The flow physics are explored in detail to explain the results.