Abstract Non-axisymmetric endwall contouring of gas turbines has been widely employed as an effective way to improve the aerodynamic performance or heat transfer features. Though efforts have been exerted by previous investigators to generate improved contoured endwall designs, better understandings of the physics behind the phenomenon that non-axisymmetric contoured endwall configurations change the aerodynamic or heat transfer performances are still in demand. In this study, a global sensitivity analysis (GSA) methodology is used to determine shape changes at which locations on the endwall have the most significant impact on the aerodynamic or endwall heat transfer performances. Then, typical non-axisymmetric contoured endwall cases found by a multi-objective optimization approach are studied to understand further why shape changes in such locations impact the passage aero-thermal aspects so much. The results show that the most prominent areas for the passage aerodynamic performance are at the passage mid-pitch from the passage forepart to the aft part by impacting the stream-wise acceleration features. The locations at the passage's aft part influence the heat transfer features most due to high velocity, thus large heat transfer coefficient values there.

中文翻译：

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不同的涡轮端壁非轴对称轮廓对空气动力学和传热方面的影响：敏感性分析研究

摘要 燃气轮机的非轴对称端壁轮廓作为改善气动性能或传热特性的有效方法已被广泛采用。尽管以前的研究人员已经努力产生改进的轮廓端壁设计，但仍然需要更好地理解非轴对称轮廓端壁配置改变空气动力学或传热性能这一现象背后的物理原理。在这项研究中，使用全局灵敏度分析 (GSA) 方法来确定端壁上哪些位置对空气动力学或端壁传热性能影响最大的形状变化。然后，对通过多目标优化方法发现的典型非轴对称轮廓端壁情况进行了研究，以进一步了解为什么这些位置的形状变化会如此大地影响通道气动热方面。结果表明，通过影响流向加速度特征，通道气动性能最突出的区域是从通道前部到后部的通道中距。由于高速，通道尾部的位置对传热特性的影响最大，因此那里的传热系数值很大。