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Effects of Winglet Geometry on the Aerodynamic Performance of Tip Leakage Flow in a Turbine Cascade

机译：小翼几何形状对涡轮叶栅尖端泄漏流空气动力学性能的影响

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Experimental and numerical methods were used to investigate the aerodynamic performance of a winglet tip in a linear cascade. A flat tip and a cavity tip are studied as baseline cases. The flow patterns over the three tips are studied. The flow separates over the pressure side edge. For the cavity tip and the winglet tip, vortices appear in the cavity. These vortices reduce the discharge coefficient of the tip. The purpose of using a winglet tip is to reduce the driving pressure difference. The pressure side winglet of the winglet geometry studied in this paper has little effect in reducing the driving pressure difference. It is found that the suction side winglet reduces the driving pressure difference of the tip leakage flow near the leading edge, but increases the driving pressure difference from midchord to the trailing edge. This is also used to explain the findings and discrepancies in other studies. Compared with the flat tip, the cavity tip and the winglet tip achieve a reduction of the loss to the size of the tip gap- The effects of the rounding of the pressure side edge of the tips were studied to simulate the effects of deterioration. As the size of the pressure side edge radius increase, the tip leakage mass flow rate and the loss increase. The improvement of the aerodynamic performance by using a winglet remains similar when comparing with a flat tip or a cavity tip with the same pressure side radius.
机译：实验和数值方法用于研究线性叶栅中小翼尖端的空气动力学性能。将平头和腔头作为基线案例进行研究。研究了三个尖端的流动模式。流量在压力侧边缘上分开。对于空腔尖端和小翼尖端，在空腔中会出现涡旋。这些涡流降低了尖端的放电系数。使用小翼尖的目的是减小驱动压力差。本文研究的小翼几何体的压力侧小翼对减小驱动压力差的影响很小。发现吸力侧小翼减小了前缘附近的尖端泄漏流的驱动压力差，但是增大了从中弦到后缘的驱动压力差。这也可以用来解释其他研究中的发现和差异。与平头相比，腔尖和小翼尖减少了尖端间隙尺寸的损失。研究了尖顶压力侧边缘的倒圆效果，以模拟变质的效果。随着压力侧边缘半径的大小增加，尖端泄漏质量流率和损失增加。当与具有相同压力侧半径的平顶或腔顶相比时，通过使用小翼改善空气动力学性能仍然相似。

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