Abstract In order to improve compressor performance using a new design method, which originates from the fins on a humpback whale, experimental tests and numerical simulations were undertaken to investigate the influence of the tubercle leading edge on the aerodynamic performance of a linear compressor cascade with a NACA 65–010 airfoil. The results demonstrate that the tubercle leading edge can improve the aerodynamic performance of the cascade in the post-stall region by reducing total pressure loss, with a slight increase in total pressure loss in the pre-stall region. The tubercles on the leading edge of the blades cause the flow to migrate from the peak to the valley on the blade surface around the tubercle leading edge by the butterfly flow. The tubercle leading edge generates the vortices similar to those created by vortex generators, splitting the large-scale separation region into multiple smaller regions.

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结节前缘叶片压缩机级联性能研究

摘要 为了使用源自座头鲸鳍的新设计方法提高压气机性能，通过实验测试和数值模拟研究了结节前缘对线性压气机叶栅气动性能的影响。 NACA 65-010 翼型。结果表明，结节前缘可以通过降低总压力损失来改善后失速区域叶栅的气动性能，而前失速区域的总压力损失略有增加。叶片前缘上的结节使流动通过蝶形流从结节前缘周围叶片表面上的波峰迁移到波谷。结节前缘产生的涡流类似于涡流发生器产生的涡流，