Tip leakage flow directly affects the aerodynamic performance in the turbine stages. In this research, wind tunnel experiments and numerical calculations are performed for the Original Cavity Tip (OCT), the modified Stepped Cavity Tip (SCT) and Cavity Winglet Tip (CWT) with different pressure squealers under seven incidence angles in a range of ±15°. The shape control effects on the aerodynamic performance are obtained by comparing the loss structure of the exit flow field, the pressure distribution of the casing wall and the surface load of the blades. Experimental results show that SCT structure reduces the total pressure loss by 6.8% and the CWT by 4.1% relative to OCT at 0° incidence angle with an outlet Mach Number 0.92. The variation of the incoming flow angles significantly affects the scale and loss values of the passage vortex, which further affects the leakage flow. Numerical calculations are performed as supplementary detail analysis, specify the interrelationship between leakage and passage vortices.

尖端泄漏流量直接影响涡轮级中的空气动力学性能。在本研究中，对原始腔尖端（OCT），改进的阶梯腔尖端（SCT）和腔翼尖端（CWT）进行了风洞实验和数值计算，其中具有不同的压力扬声器，在±15范围内的七个入射角下°。通过比较出口流场的损失结构、机壳壁的压力分布和叶片的表面载荷，得出形状控制对气动性能的影响。实验结果表明，在0°入射角和出口马赫数为0.92的情况下，SCT结构相对于OCT减少了6.8%的总压力损失和4.1%的CWT。来流角度的变化显着影响通道涡流的规模和损失值，这进一步影响了泄漏流量。数值计算作为补充细节分析进行，指定泄漏和通道涡流之间的相互关系。