变稠度条件下仿生学前缘结状突起对压气机叶栅性能的影响

Influence of Bionic Leading-Edge Tubercles on Cascade Performance in a Compressor With Different Solidities

本文以某压气机平面叶栅为研究对象,采用数值计算的方法,在不同稠度条件下,分别研究仿生学前缘结状突起在零攻角和正攻角时对叶栅性能的影响。结果表明,零攻角工况时,各稠度条件下的仿生学叶栅总压损失系数都有一定的增大,性能恶化;8°正攻角工况时,波长等于9.6%c的前缘结状突起在各稠度条件下都能有效降低总压损失系数,改善叶栅性能,在设计稠度下(S=2)效果最显著,损失系数降低了约18.8%;仿生学前缘的作用机理:结状突起诱导产生的成对流向涡与通道中的分离流动相互作用,包括涡系结构之间的抵消作用和动量的输运,从而延缓分离,提高叶栅性能。

In this paper,a linear compressor cascade is selected as the baseline.Numerical simulations for different solidities are carried out to investigate the influence of the bionic leading-edge tubercles on the aerodynamic performance at incidence angles of 0° and 8°.Results indicate that bionic cascades for different solidities show an increase in total pressure loss coefficient at the incidence angle of 0°,which leads to the deterioration of cascade performance.The leading edge tubercle with the wavelength of 9.6%c effectively decrease the loss coefficient and enhance the cascade performance for different solidities at the incidence angle of 8°.Among these solidities,a remarkable decrease in the loss coefficient of 18.8% is achieved at the design solidity（S=2）.The mechanism of bionic leading edge is concluded as followed：the interaction between tubercle-induced streamwise vortex pairs and separation flow in the passage,including the vortex interaction and momentum transportation,delays flow separation and enhances cascade performance.