变马赫数下压力面小翼对扩压叶栅气动特性的影响

Experiment on effect of pressure side winglet on aerodynamic performance of compressor cascade at different inlet mach number

为探究变来流马赫数下压力面叶尖小翼对扩压叶栅气动特性的影响,对Ma=0.5、Ma=0.6和Ma=0.7来流马赫数下的原型叶栅和加装不同宽度的压力面叶尖小翼的扩压叶栅流场特性进行了实验研究.结果表明:在高亚声速的来流条件下,压力面叶尖小翼可以有效减小叶顶两侧压力梯度,阻碍流体流入叶顶间隙,控制叶顶泄漏流动,减小流场损失,改善流场流动状况.随着小翼宽度的增加,改善程度增大,同时马赫数的变化与控制效果成正比.当Ma=0.7时,与原型叶栅相比,PW2.0方案的流场改善程度最大,总压损失系数降低了6.53%.

To investigate the effects of pressure side winglet on aerodynamic performance of high subsonic compressor cascade at different Inlet Mach Number, the experimental study has been carried out to explore the original cascade and cascades with different pressure side winglets at different Inlet Mach Number(Ma=0.5,Ma=0.6 and Ma=0.7). The results show that the pressure side winglet not only weakens the pressure gradient on both sides of the blade, but also obstructs flow into the tip clearance. At the same time the pressure side winglet can inhibit the tip leakage flow and reduce the flow loss under the condition of high subsonic, thus the tip clearance flow is improved. With the increase of pressure side winglet width, the improvement degree is increased, and the change of Mach number is proportional to the control effect. The most effective pressure side winglet is PW2.0 at inlet Mach number of 0.7, which provides the most significant aerodynamic loss reduction by 6.53% compared to the original cascade at the same inlet Mach number.