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首页> 外文期刊>Journal of turbomachinery >The Influence Of Shroud And Cavity Geometry On Turbine Performance: An Experimental And Computational Study-part Ⅱ: Exit Cavity Geometry
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The Influence Of Shroud And Cavity Geometry On Turbine Performance: An Experimental And Computational Study-part Ⅱ: Exit Cavity Geometry

机译：护罩和腔体几何形状对涡轮性能的影响：实验和计算研究-第二部分：出口腔体几何形状

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The geometry of the exit shroud cavity where the rotor shroud leakage flow reenters the main passage flow is very important due to the dominant influence of the leakage flow on the aerodynamics of low aspect ratio turbines. The work presented in this paper investigates, both experimentally and numerically, possibilities for the control of shroud leakage flow by modifications to the exit shroud cavity. The processes through which the leakage flow affects the mainstream aerodynamics identified in the first part of this study were used to develop promising strategies for reducing the influence of shroud leakage flow. The experimental program of this study was conducted on a three-stage model air turbine, which was extensively supported by CFD analysis. Three different concepts for shroud leakage flow control in the exit cavity were analyzed and tested: (a) profiled exit cavity downstream end wall, (b) axial deflector, and (c) radial deflector concepts. Reductions in aerodynamic losses associated with shroud leakage were achieved by controlling the position and direction at which the leakage jet reenters the mainstream when it leaves the exit shroud cavity. Suggestions are made for an optimum shroud and cavity geometry.
机译：转子护罩泄漏流重新进入主通道流的出口护罩腔的几何形状非常重要，这是因为泄漏流对低深宽比涡轮机的空气动力学的主要影响。本文介绍的工作在实验和数值上都研究了通过修改出口导流腔来控制导流漏流的可能性。在本研究的第一部分中确定了泄漏流影响主流空气动力学的过程，这些过程被用于开发有希望的策略来减少导流罩泄漏流的影响。这项研究的实验程序是在三阶段模型的空气涡轮机上进行的，并得到了CFD分析的广泛支持。分析和测试了三种不同的用于控制出口腔中护罩泄漏流的概念：（a）型腔出口下游端壁；（b）轴向偏转器；（c）径向偏转器概念。通过控制泄漏射流离开主流出口腔时重新进入主流的位置和方向，可以减少与上游罩泄漏相关的空气动力学损失。提出了最佳护罩和型腔几何形状的建议。

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