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EXPERIMENTS AND COMPUTATIONS ON LARGE TIP CLEARANCE EFFECTS IN A LINEAR CASCADE

机译：线性级联大尖端间隙效应的实验与计算

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摘要

Large tip clearances typically in the region of six percent exist in the high pressure stages of compressors of industrial gas turbines. Due to the relatively short annulus height and significant blockage, the tip clearance flow accounts for the largest proportion of loss in the HP. Therefore increasing the understanding of such flows will allow for improvements in design of such compressors, increasing efficiency, stability and the operating range. Experimental and computational techniques have been used to increase the physical understanding of the tip clearance flows through varying clearances in a linear cascade of controlled-diffusion blades. This paper shows two unexpected results. Firstly the loss does not increase with clearances greater than 4% and secondly there is an increase of blade loading towards the tip above 2% clearance. It appears that the loss production mechanisms of the pressure driven tip clearance jet do not increase as the clearance is increased to large values. The increase in blade force is attributed to the effect of the strong tip clearance vortex which does not move across the blade passage to the pressure surface, as is often observed for high stagger blading. These results may be significant for the design of HP compressors for industrial gas turbines.
机译：通常在工业燃气轮机压缩机的高压阶段中的大尖端间隙存在于六个百分点。由于环形高度相对较短，堵塞了很大，尖端间隙流量占HP中最大比例的损失比例。因此，增加对这种流动的理解将允许改进这种压缩机的设计，提高效率，稳定性和操作范围。已经使用实验和计算技术来增加通过控制扩散叶片的线性级联的变化间隙的尖端间隙流动的物理理解。本文显示了两个意外结果。首先，损失不会随着大于4％的间隙而增加，其次是朝向尖端的叶片载荷增加，以上的间隙高于2％。看来，随着间隙增加到大值，压力驱动的尖端间隙射流的损耗生产机制不会增加。叶片力的增加归因于强尖端间隙涡流的效果，该效果不会在叶片通道上移动到压力表面，正如经常观察到的高错叶片。这些结果对于工业燃气轮机的HP压缩机的设计可能很大。

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