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Non-axisymmetric end wall profiling in a highly loaded compressor cascade

机译:高负载压缩机叶栅中的非轴对称端壁轮廓

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摘要

Very few studies of non-axisymmetric endwall profiling in compressor have been conducted in published literatures. This study investigates the control mechanism of non-axisymmetric endwall on the flow field of a highly loaded compressor cascade and the guidelines for the design of non-axisymmetric endwall. First, CFD method was validated with existing experimental data. Then, the design method of non-axisymmetric endwall based on trigonometric function and Bezier curve was introduced. The design strategies of non-axisymmetric endwall considering axial position effect, height effect and different patterns of concave/convex were investigated in detail. Results show that non-axisymmetric endwall is an effective way to control the near endwall flow field of the compressor cascade. With the optimal non-axisymmetric endwall in this study, the loss coefficient of the cascade is reduced by 5.5%, and the cascade exhibited suppressed corner separation, reduced passage vortex and more uniformly distributed outflow angles. The optimal axial position of the concave was at 0.22 axial chord, which was near the onset of corner separation, so the best control effect was obtained. There is an optimal height for the concave of the non-axisymmetric endwall. A lower concave will not have sufficient effect on the cascade, whereas a higher concave will be detrimental on the contrary. It is indicated that the influence mechanism of non-axisymmetric endwall on the compressor cascade is basically derived from the superimposed effect of reduced cross-passage pressure gradient and increased spanwise inward pressure gradient. The cross-passage pressure gradient can be reduced by both concave on the suction side and convex on the pressure side of the endwall. However, concave can introduce spanwise inward pressure gradient, whilst convex can introduce spanwise outward pressure gradient. For better improving the performance of compressor cascades, non-axisymmetric endwall is suggested to be a concave on the entire endwall, which introduces both reduced cross-passage pressure gradient and increased spanwise inward pressure gradient.
机译:在公开的文献中,很少有关于压缩机中非轴对称端壁轮廓的研究。本研究探讨了非轴对称端壁在高负荷压缩机叶栅流场上的控制机理以及非轴对称端壁设计的指导原则。首先,利用现有实验数据验证了CFD方法。然后介绍了基于三角函数和贝塞尔曲线的非轴对称端墙的设计方法。详细研究了考虑轴位置效应,高度效应以及凹凸形状的非轴对称端壁的设计策略。结果表明,非轴对称端壁是控制压缩机叶栅近端壁流场的有效方法。使用本研究中的最佳非轴对称端壁,叶栅的损失系数降低了5.5%,并且叶栅显示出抑制的角分离,减小的通道涡流和更均匀分布的流出角。凹面的最佳轴向位置在0.22的轴向弦上,接近拐角分离的开始,因此获得了最佳的控制效果。非轴对称端壁的凹面有一个最佳高度。较低的凹面不会对级联产生足够的影响,相反,较高的凹面将是不利的。结果表明,非轴对称端壁对压气机叶栅的影响机理基本上是由减小交叉通道压力梯度和增大翼展向内压力梯度的叠加作用得出的。通过在端壁的吸力侧上的凹部和在端壁的压力侧上的凸部两者都可以减小交叉通道压力梯度。但是,凹面可以引入翼展方向向内的压力梯度,而凸面可以引入翼展方向向内的压力梯度。为了更好地改善压缩机叶栅的性能,建议将非轴对称端壁在整个端壁上设置为凹形,这样既可以减小跨通道压力梯度,又可以增大翼展向内压力梯度。

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    Northwestern Polytech Univ, Sch Power & Energy, 159 Mail Box,127 West Youyi Rd, Xian 710072, Shaanxi, Peoples R China|Shaanxi Key Lab Internal Aerodynam Aeroengine, Xian, Shaanxi, Peoples R China|Peking Univ, Coll Engn, Beijing 100871, Peoples R China;

    Northwestern Polytech Univ, Sch Power & Energy, 159 Mail Box,127 West Youyi Rd, Xian 710072, Shaanxi, Peoples R China|Shaanxi Key Lab Internal Aerodynam Aeroengine, Xian, Shaanxi, Peoples R China;

    AECC Xian Aeroengine Controls Co Ltd, Xian, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Power & Energy, 159 Mail Box,127 West Youyi Rd, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Power & Energy, 159 Mail Box,127 West Youyi Rd, Xian 710072, Shaanxi, Peoples R China;

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  • 正文语种 eng
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  • 关键词

    Non-axisymmetric endwall; axial flow compressor; compressor cascade; corner separation; passage vortex;

    机译:非轴对称端壁;轴流压缩机;压气机级联;角分离;通道涡;

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