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转子叶片叶尖增加翼梢小翼是控制涡轮间隙泄漏流减小泄漏损失的有效手段之一,为研究翼梢小翼位置对高压涡轮间隙泄漏流动的影响,利用数值模拟方法求解雷诺平均纳维-斯托克斯方程获得涡轮通道内的三维流场,并详细分析叶片压力边和吸力边增加翼梢小翼对间隙泄漏流及涡轮气动损失的影响。研究发现:压力边翼梢小翼可以降低间隙泄漏流量,但基本不改变间隙泄漏涡结构,对涡轮效率影响较小;吸力边翼梢小翼虽然对降低间隙泄漏流量作用不明显,但可以有效地抑制泄漏涡的生成和发展并削弱叶片吸力面壁面潜流,降低泄漏流动损失。结果表明:在控制间隙泄漏流动减小泄漏损失方面,吸力边翼梢小翼明显优于压力边翼梢小翼。
In order to study the influence of the position of wingtip on the leakage of high-pressure turbine clearance, numerical simulation is used to solve the Reynolds-averaged Navier-Stokes problem - Stokes equation to obtain the three-dimensional flow field in the turbine passageway. The influence of blade tip pressure on the leakage flow and the aerodynamic loss of turbine was analyzed in detail. It is found that the pressure wing tip winglet can reduce the leakage of clearance but basically does not change the gap leakage vortex structure and has little effect on the turbine efficiency. Although the suction wing tip winglet has no obvious effect on reducing the leakage leakage, it can be effective To suppress the formation and development of leakage vortices and weaken the surface subsidence of the suction surface of the blade to reduce the leakage flow loss. The results show that the suction wing tip winglet is obviously superior to the pressure wing tip winglet in controlling the leakage flow and decreasing the leakage loss.