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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, the plane cascade of a compressor is taken as the research object. The numerical calculation method is used to study the influence of the bionic front knot protuberances on the blade cascade performance at zero angle of attack and positive angle of attack under different consistencies. The results show that under zero angle of attack conditions, the total pressure loss coefficient of bionics cascade under certain consistency conditions increases to a certain degree and the performance deteriorates. In the condition of 8 ° positive attack angle, the front edge with wavelength equal to 9.6% c The knot-like protrusions can effectively reduce the total pressure loss coefficient and improve the performance of the cascade under various consistency conditions. The effect is most significant under the designed consistency (S = 2), and the loss coefficient is reduced by about 18.8%. The mechanism of the bionics front: Knot-like flow induced vortical flow and the separation flow in the channel interaction, including the vortex structure of the interaction between the momentum and the transport, thus delaying the separation and improve cascade performance.