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本文实验研究了通过前置可调导叶改变来流气流方向对涡轮低压导向器环形叶栅损失的产生与分布的影响 ,以及在沿叶高不同分布的冲角下模型叶栅气动特性的变化。在不同的沿叶高分布的进气冲角下 ,详细地测量了导向器出口流场和叶栅表面静压分布 ,得出导向器总流动损失随平均冲角的变化 ,从而确定了对应最小流动损失的冲角范围 ,对导向器的变工况性能做出了评价。
In this paper, the effects of the flow direction of the flow through the front adjustable guide vanes on the generation and distribution of annular cascades in the turbocompressor are studied experimentally, and the changes of the aerodynamic characteristics of the model cascades at different angles along the blade height . Under different angles of incidence along the blade height distribution, the outlet flow field of the guide and the static pressure distribution on the surface of the cascade were measured in detail. The change of the total flow loss of the guide with the average angle of attack was obtained and the corresponding minimum The range of attack angle of flow loss makes an evaluation on the performance of the guide.