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为更准确地预测压气机静叶角区失速以及为角区流场优化提供理论支持,在压气机平面叶栅环境下,利用数值模拟和实验验证方法,研究来流边界层厚度变化对角区流场及角区失速特性的影响。在角区失速前后的典型工况,利用总压损失系数和折转角的展向分布显示不同流场结构引起的性能变化;利用表面极限流线、总压损失云图和Q判据等手段显示角区涡结构特点。结果表明,当来流边界层厚度从1%展长增加到25%展长时,角区失速提前3°攻角发生,叶栅低损失工作范围缩减近30%。而在角区失速发生后,来流边界层厚度变化对角区失速结构没有明显影响,但仍会增强叶栅内其他区域的二次流效应。
In order to more accurately predict the stall in the static angular region of the compressor and to provide theoretical support for the optimization of the flow field in the corner region, the numerical simulation and experimental verification methods are used to study the variation of the boundary layer thickness in the diagonal region Influence of flow field and corner stall characteristics. The typical working conditions before and after the stall in the corner zone show the change of performance caused by different flow field structures by using the total pressure loss coefficient and the spread distribution of the turning angle. By using the surface limit flow lines, the total pressure loss cloud and the Q criterion, Region vortex structure characteristics. The results show that when the thickness of the boundary layer increases from 1% to 25%, the angle of attack stalls by 3 ° in advance, and the work area of low loss of blades decreases by nearly 30%. However, after the stall in the corner zone, the thickness of the boundary layer changed little to the stall structure in the corner zone, but still increased the secondary flow in other regions of the cascade.