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首页> 外文期刊>Journal of aerospace engineering >Experimental Investigation of Effects of Tip Cavity on Tip Clearance Flow in a Variable-Geometry Turbine Cascade
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Experimental Investigation of Effects of Tip Cavity on Tip Clearance Flow in a Variable-Geometry Turbine Cascade

机译：可变几何涡轮叶栅中叶尖腔对叶尖间隙流动影响的实验研究

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摘要

The variable-geometry turbine is often used to improve the gas turbine part-load performances; however, there are performance penalties associated with the vane-end part clearance that is required for the smooth movement of variable-geometry vanes. To determine the effects of tip cavity on tip clearance flows in a variable-geometry vane, experimental investigations with a variable-geometry turbine linear cascade have been conducted. The tip-cavity effects on the overtip-leakage flow and losses, and the effects of turning angle on the total pressure losses and the yaw angle are considered. The measurement results show that the variation of vane-turning angles completely changes the vane-loading distribution. As the vane-turning angle varies from design to closed, the vane loading increases and tends to be more aft loaded, thus increasing the tip-leakage loss, and vice versa. At all turning angles, the tip-leakage vortex is weakened by the tip cavity, and the cavity tip plays a significant role in reducing aerodynamic losses. The results can provide guidelines for the vane-end clearance control of variable-geometry turbines. (C) 2016 American Society of Civil Engineers.
机译：可变几何涡轮机通常用于改善燃气涡轮机的部分负荷性能。但是，可变几何形状叶片的平滑运动需要与叶片端部间隙相关的性能损失。为了确定尖端腔对可变几何叶片中尖端间隙流动的影响，已经进行了可变几何涡轮线性级联的实验研究。考虑了顶腔对顶漏流和损失的影响，以及转角对总压力损失和偏航角的影响。测量结果表明，叶片转向角的变化完全改变了叶片载荷分布。随着叶片转向角度从设计到关闭的变化，叶片载荷增加并且趋向于向后载荷，从而增加了叶尖泄漏损失，反之亦然。在所有转弯角度，尖端泄漏腔都会削弱尖端泄漏涡，而尖端在减少空气动力损失方面起着重要作用。该结果可为可变几何涡轮机的叶片端间隙控制提供指导。 （C）2016年美国土木工程师学会。

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