叶片端部孔隙结构对透平叶栅气动性能影响的试验研究

THE VALIDITY OF HOLE CONFIGURATIONS ON THE AERODYNAMIC PERFORMANCE OF TURBINE BLADE

减小叶片端部的二次流动能够显著减小叶栅的流动损失.本文通过分析叶栅二次流动的机理,提出了一种减小二次流损失的结构—叶片端部的孔隙结构.并通过试验验证了合理的孔隙结构能达到减小二次流损失的目的.本文分别研究了在透平叶片端部不同位置的孔隙结构对透平叶栅气动性能的影响.发现对于小尺寸的孔隙结构,其对流动控制的能力有限,尽管如此,其还是能够达到减小损失的目的.本文进行了五个攻角下的孔隙结构实验,结果表明,端部前缘孔隙结构与原始叶栅相比,不同攻角下的总压损失分别减小了2.4%、6.8%、6.8%、3.6%、2.7%.本文工作为提高透平叶栅气动性能提供了一种新思路.

With the reduction of secondary loss, the exit blade loss is cutting down remarkably. Some hole configurations are adopted here, wishing they can decrease the loss. The validity of this configuration is verified experimentally at five attach angles. The results showed that this hole configuration can reduce the exit blade losses by 2.4%-6.8%, which provided a new method to increase the aerodynamic performance of the turbine cascade.