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首页> 外文会议>ASME turbo expo >EXPERIMENTAL INVESTIGATION OF DISC CAVITY LEAKAGE FLOW AND HUB ENDWALL CONTOURING IN A LINEAR ROTOR CASCADE
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EXPERIMENTAL INVESTIGATION OF DISC CAVITY LEAKAGE FLOW AND HUB ENDWALL CONTOURING IN A LINEAR ROTOR CASCADE

机译：线性转子叶栅中盘腔漏流和轮毂端部轮廓的实验研究

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摘要

An experimental study is carried out in a stationary linear cascade which simulates a turbine rotor to compare the thermal performance of two new axisymmetric endwall contour geometries. Measurements of endwall adiabatic film cooling effectiveness and near-endwall passage temperature fields are made for this purpose. In addition to documenting endwall contouring effects, a range of disc cavity leakage flow rates is investigated. This information is meant to quantify, over the range tested, the benefits and penalties of introducing leakage flow into the passage using the designated endwall contouring. Special attention is paid to determine whether the endwall curvature has any effect on the interaction between mainstream and secondary flows within the passage. Results indicate improved thermal performance when strong endwall curvature exists near the blade leading edge. The strong curvature causes cavity leakage flow to remain closer to the endwall, thereby increasing cooling effectiveness.
机译：在固定的线性叶栅中进行了实验研究，该线性叶栅模拟了涡轮机转子，以比较两个新的轴对称端壁轮廓几何形状的热性能。为此目的，对端壁绝热膜的冷却效率和近端壁通过温度场进行了测量。除了记录端壁轮廓影响外，还研究了一系列碟形腔泄漏流量。该信息旨在在测试的范围内量化使用指定的端壁轮廓将泄漏流引入通道的好处和损失。要特别注意确定端壁曲率是否对通道内主流和次要流之间的相互作用有任何影响。结果表明，当叶片前缘附近存在强的端壁弯曲时，热性能得到改善。强曲率导致空腔泄漏流保持更靠近端壁，从而提高了冷却效率。

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