人字形微沟槽控制低雷诺数下高亚声速压气机叶型损失研究

Effects of Herringbone Microgrooves on Profile Loss of a High Subsonic Compressor under Low Reynolds Number

关键词:  压气机  扩压叶栅  人字形微沟槽  低雷诺数  叶型损失

Key words:  Compressor  Compressor cascades  Herringbone microgrooves  Low Reynolds number  Profile loss

摘要:

为研究人字形微沟槽对高亚声速压气机叶型损失的影响，以高负荷扩压叶栅为研究对象，在低雷诺数（Re）条件下对具有不同几何参数的微沟槽方案进行数值研究。计算结果表明，人字形微沟槽可以在一定范围的低雷诺数下有效降低叶片的叶型损失，提高叶片的扩压能力。人字形微沟槽深度和间距对叶型性能的影响主要体现在Re≥2.5×10⁵时，特定几何的微沟槽方案在增加气流折转角的同时可使叶型损失最大降低8.73%。变进气角特性表明在不大于设计进气角工况下微沟槽具有较为明显的降低叶型损失的效果。人字形微沟槽降低叶型损失的机理在于其使得叶片近壁面湍流掺混程度增加，有效延缓了吸力面边界层的层流分离。

Abstract:

To study the effects of herringbone microgrooves on the profile loss of a high subsonic compressor， a numerical study of microgroove schemes with different geometric parameters is conducted at low Reynolds number （Re） conditions with a high-loaded compressor cascade as the research object. The calculation results show that the herringbone microgroove can effectively reduce the blade profile loss and improve the blade pressure expansion capacity at a certain range of low Reynolds number. The influence of herringbone microgroove depth and spacing on the blade performance is mainly reflected at Re≥2.5×10⁵ ， geometry-specific microgroove solution increases the flow turning angle while reducing the profile loss by up to 8.73%. The variable inlet angle characteristics show that microgrooves have the effect of reducing the profile loss under conditions less than or equal to the design inlet angle. The mechanism of profile loss reduction is that microgrooves increase the turbulent mixing at the near-wall surface of the blade， which effectively delays the laminar flow separation at the suction surface boundary layer.