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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Experimental investigation of the influence on compressor cascade characteristics at high subsonic speed with pressure surface tip winglets
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Experimental investigation of the influence on compressor cascade characteristics at high subsonic speed with pressure surface tip winglets

机译：高亚音速压力表面尖翼尖翼对压缩机级联特性影响的实验研究

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摘要

To investigate the influence of tip winglets on the tip leakage flow in a compressor cascade with different incidences, the experimental measurement combined with numerical simulation are used to study the conventional cascade and cascades with three different pressure surface tip winglets at five incidences of −6°, −3°, 0°, +3° and +6°. The results indicate that three different tip winglets at five incidences all restrain the occurrence of leakage flow, delay the mixing of leakage flow and the mainstream, change the formation path of leakage vortex and weaken its intensity, reduce the flow loss and improve the uniformity of flow field. The sensitivity of the flow field to variable incidences is reduced. The optimization degree of the flow field is proportional to the width of the blade tip winglet. The improvements are more obvious at positive angles. When the incidence reaches +6°, the flow loss is reduced by 12.4%.
机译：为了调查尖翼翼在具有不同公告的压缩机级联中的尖端泄漏流量的影响，与数值模拟结合的实验测量用于研究传统的级联和级联，三个不同的压力表面尖翼尖翼，在5°的速度下进行-6° ，-3°，0°，+ 3°和+ 6°。 结果表明，五个不同的尖翼翼翅目所有限制泄漏流动的发生，延迟泄漏流量的混合和主流，改变泄漏涡流的形成路径并削弱其强度，降低流量损失，提高均匀性 流场。 流场对可变发夹的敏感性降低。 流场的优化度与叶片尖端小翼的宽度成比例。 在正角度的改善更明显。 当发病率达到+ 6°时，流量损失减少12.4％。

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