轴流压气机掠形前缘激波动力学效应的模型分析

借助三维激波曲面的一种分析模型,对于高负荷轴流压气机掠形转子叶片所能造就的前缘空间激波曲面,进行了构造特点和近波前波后流动参数分布的计算。着重讨论了前缘曲线的相对前掠和后掠对前缘激波后流动的影响,对于掠形叶片到底产生什么功效这个问题的一个方面,给出了一种模型化的细致分析。其中定量显示了存在着展向与周向掺混的激波掺混源这个设想的合理性。

ANALYSIS ON THE AERODYNAMIC BEHAVIORS OF THE SWEPT LEADING EDGE SHOCKS IN HIGH LOAD AXIAL COMPRESSORS

For the curved leading edge shock surfaces generated by the high load swept axial rotors, using an analytical structure model of 3 D shock surface, this paper investigated the characteristics of the shock surface structure and calculated the distribution of the flow variables in front of and behind the shock. It focused on the influences of relatively forward or backward sweep rotors on the flow field behind but near the leading edge shock surface. By this analytical model, the paper answered one aspect of the question of the swept rotors' functions. For the first time, it quantitatively showed the existence of the phenomenon of 3 D shock induced spanwise and circumferential mixing.