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ENDWALL PERFORMANCE OF OUTLET GUIDE VANE CASCADES WITH DIFFERENT BLADE LOADING DISTRIBUTIONS

机译：出口导向叶片级联具有不同刀片装载分布的端口导向叶片的端口性能

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摘要

As a part of an innovative aerodynamic design concept for a single stage low pressure turbine, a high turning outlet guide vane is required to remove the swirl from the hot gas. The airfoil of the vane is a highly loaded compressor airfoil that has to operate at very low Reynolds numbers (Re～120,000). Recently published numerical design studies and experimental analysis on alternatively designed airfoils showed that blade profiles with an extreme front loaded pressure distribution are advantageous for low Reynolds number conditions. This paper experimentally and numerically discusses about the three-dimensional performance near the end-wall of two alternatively designed cascades, the end-wall performance of a baseline cascade with controlled diffusion airfoils (CDA) and a cascade with extreme front loaded airfoils. The results showed that although the end-wall pressure gradients are different, the characteristics of the secondary flow are very similar for both of the cascades. Both, experiment and numerical analysis showed that the losses close to the end-wall of the extreme front loaded airfoils are even lower in relation to those of the CDA airfoils. The flow mechanism on the superiority of the extreme front loaded airfoils around the end-wall region is discussed.
机译：作为单级低压涡轮机的创新空气动力学设计概念的一部分，需要高转动出口导向叶片以从热气体中除去涡流。叶片的翼型是高负荷的压缩机翼型，其必须在非常低的雷诺数（RE〜120,000）上运行。最近公布的数值设计研究和对可替代设计的翼型的实验分析表明，具有极端前部负载压力分布的叶片轮廓对于低雷诺数条件是有利的。本文在实验上进行了数值和数值讨论了两个可替代设计的级联端壁附近的三维性能，基线级联的端壁性能具有受控扩散翼型（CDA）和具有极端前部装载翼型的级联。结果表明，尽管末端壁压梯度是不同的，但次要流动的特性对于两种级联非常相似。实验和数值分析表明，与CDA翼型的那些相对于CDA的翼型相对于那些，靠近极端载荷翼型的端壁的损失甚至更低。讨论了围绕末端壁区域周围的极端负载翼型的优越性的流动机制。

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