来流马赫数对吸力面小翼控制间隙泄漏效果影响的研究

Control Effect of Suction Side Winglet on Tip Clearance Leakage at Different Inlet Mach Number of High Subsonic

为了探索来流马赫数的变化对吸力面叶尖小翼间隙泄漏流动控制效果的影响,采用数值模拟软件ANSYS CFX对Ma=0.5、Ma=0.6及Ma=0.7三个高亚声速下无叶尖小翼叶栅及加装了不同宽度吸力面小翼的扩压叶栅进行了数值计算。结果表明:当Ma=0.5时,不同宽度吸力面叶尖小翼都可以削弱泄漏涡的强度,改善叶顶间隙流动,降低叶栅流动损失。与原型叶栅相比,SW2.0方案总压损失降低了4.52%。而当来流马赫数逐渐变大时。吸力面叶尖小翼对叶栅顶部流场带来的有效改善作用随之减弱,对流场的消极影响增强。当Ma=0.7时,吸力面叶尖小翼结构增加了流场总压损失。

In order to investigate the effects of the suction side winglet on tip clearance leakage at different inlet Mach number,the numerical simulation has been carried out to explore the original cascade and cascades with different suction side winglets at different inlet Mach number(Ma=0.5,Ma=0.6 and Ma=0.7) by using the ANSYS CFX software.The results show that the suction side winglet can reduce the intensity of tip leakage vortex and improve the tip clearance flow when the Mach number is 0.5,thus the total pressure loss of the cascade is decreased.SW2.0 provides the most significant aerodynamic loss reduction by 4.52 percent compared to original cascade at the same inlet Mach number.And when the incoming Mach number gradually becomes larger.The effective improvement effect of the suction side winglet on the flow field at the top of the cascade is weakened,and the negative impact on the flow field is enhanced.The suction side winglet even aggravate the flow field flow when the Mach number is 0.7.