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首页> 外文期刊>Experiments in Fluids: Experimental Methods and Their Applications to Fluid Flow >Experimental analysis and modeling of the losses in the tip leakage flow of an isolated, non-rotating blade setup
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Experimental analysis and modeling of the losses in the tip leakage flow of an isolated, non-rotating blade setup

机译：隔离，非旋转刀片设置的尖端泄漏流动损失的实验分析与建模

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摘要

Improving pressure rise capabilities of axial compressors requires an in-depth understanding of the losses produced in the tip leakage region. Here, a generic setup that magnifies the tip region of an isolated, non-rotating blade is used with the objectives of describing the main flow components and evaluating the related sources of loss. The flow at the tip is structured by the jet flow out of the gap which, under the effect of the main stream, rolls-up into a tip-leakage vortex. The current setup is characterized by the tip gap height and the thickness of the incoming boundary layer at the casing, here a flat plate, for a given incidence of the blade. Measurements are performed using LDV and a multi-port pressure probe. Variations in the tip-leakage flow are found to be mainly driven by gap height. A small, intermediate and large gap regimes are more specifically found, with threshold around 4% and 8% of gap to chord ratio for the present setting. The incoming boundary layer thickness is shown to provoke a notable effect on the vortex lateral position and total pressure losses. The local entropy creation rate is computed from LDV data and used to identify the sources of loss in the flow. A decomposition into wake and vortex losses is further proposed, allowing to relate the contributions of the various flow components to the overall losses. An empirical model of the formation of the tip vortex is developed to account for the increased losses as a function of gap height. The model provides a useful mean for the practical approximation of the gap sensitivity of pressure losses.
机译：提高轴向压缩机的压力升高能力需要深入地理解尖端泄漏区域中产生的损失。这里，将隔离的非旋转刀片的尖端区域放大的通用设置与描述主流组件的目标并评估相关源的目标。尖端处的流动由喷射流出的间隙构成，该间隙在主流的效果下卷成尖端泄漏涡流。当前设定的特征在于壳体在壳体上的尖端间隙高度和壳体的厚度，这是一个平板，用于给定的叶片的发生率。使用LDV和多端口压力探头进行测量。发现尖端泄漏流动的变化主要由间隙高度驱动。更具体地发现小，中间和大的差距制度，阈值约为本发明的间隙的4％和8％的间隙。示出了进入的边界层厚度，从而引起涡流横向位置和总压力损失的显着影响。从LDV数据计算本地熵创建速率，并用于识别流程中的损耗源。进一步提出了一种分解和涡流损耗，允许将各种流量组分的贡献与整体损失相关联。开发了尖端涡旋形成的经验模型，以考虑因隙高度的函数增加的损失。该模型为压力损失的间隙敏感性的实际近似提供了一种有用的平均值。

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