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首页> 外文会议>ASME Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >Measurement and Calculation of Turbine Cascade Endwall Pressure and Shear Stress
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Measurement and Calculation of Turbine Cascade Endwall Pressure and Shear Stress

机译：涡轮叶栅端壁压力和剪应力的测量与计算

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摘要

The complex three-dimensional fluid flow on the end-wall in an axial flow turbine blade or vane passage has been extensively investigated and reported on in turboma-chinery literature. The aerodynamic loss producing mechanisms associated with the endwall flow are still not fully understood or quantitatively predictable. To better quantify wall friction contributions to endwall aerodynamic loss, low Mach number wind tunnel measurement of skin friction coefficients have been made on one endwall of a large scale cascade of high pressure turbine airfoils, at engine operating Reynolds numbers. Concurrently, predictive calculations of the endwall flow shear stress have been made using a computational fluid dynamics (CFD) code. Use of the oil film interferometry skin friction technique is described and applied to the endwall, to measure local skin friction coefficients and shear stress directions on the end-wall. These are correlated with previously reported measured local endwall pressure gradients. The experimental results are discussed and compared to the CFD calculations, to answer questions concerning endwall aerodynamic loss predictive ability.
机译：在涡轮流体技术文献中，对轴流式涡轮机叶片或叶片通道中端壁上的复杂三维流体流进行了广泛的研究并进行了报道。与端壁流动相关的空气动力学损失产生机理仍未被完全理解或不能定量预测。为了更好地量化壁摩擦对端壁空气动力损失的贡献，在发动机工作的雷诺数下，在大型高压涡轮机翼叶栅的一个端壁上进行了低马赫数风洞的表皮摩擦系数测量。同时，已经使用计算流体动力学（CFD）代码对端壁流动切应力进行了预测性计算。描述了使用油膜干涉法皮肤摩擦技术并将其应用于端壁，以测量端壁上的局部皮肤摩擦系数和切应力方向。这些与先前报告的测得的局部端壁压力梯度相关。讨论了实验结果并将其与CFD计算进行比较，以回答有关端壁空气动力学损失预测能力的问题。

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