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首页> 外文期刊>Journal of turbomachinery >Heat Transfer in Leading Edge, Triangular Shaped Cooling Channels With Angled Ribs Under High Rotation Numbers
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Heat Transfer in Leading Edge, Triangular Shaped Cooling Channels With Angled Ribs Under High Rotation Numbers

机译：在高旋转数下前缘，三角形棱形带肋肋的冷却通道中的热传递

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摘要

The gas turbine blade/vane internal cooling is achieved by circulating compressed air through the cooling channels inside the turbine blade. Cooling channel geometries vary to fit the blade profile. This paper experimentally investigated the rotational effects on heat transfer in an equilateral triangular channel (D_h = 1.83 cm). The triangular shaped channel is applicable to the leading edge of the gas turbine blade. Angled 45 deg ribs are placed on the leading and trailing surfaces of the test section to enhance heat transfer. The rib pitch-to-rib height ratio (P/e) is 8 and the rib height-to-channel hydraulic diameter ratio (e/D_h) is 0.087. Effect of the angled ribs under high rotation numbers and buoyancy parameters is also presented. Results show that due to the radially outward flow, heat transfer is enhanced with rotation on the trailing surface. By varying the Reynolds numbers (10,000-40,000) and the rotational speeds (0-400 rpm), the rotation number and buoyancy parameter reached in this study are 0-0.58 and 0-1.9, respectively. The higher rotation number and buoyancy parameter correlate very well and can be used to predict the rotational heat transfer in the equilateral triangular channel.
机译：燃气涡轮叶片/叶片内部冷却是通过使压缩空气循环通过涡轮叶片内部的冷却通道来实现的。冷却通道的几何形状会有所不同，以适合叶片轮廓。本文实验研究了旋转对等边三角形通道（D_h = 1.83 cm）中的热传递的影响。三角形通道适用于燃气轮机叶片的前缘。 45度倾斜的肋条放置在测试部分的前表面和后表面，以增强热传递。肋骨间距与肋骨的高度比（P / e）为8，肋骨高度与通道的液压直径比（e / D_h）为0.087。还介绍了斜肋在高转数和浮力参数下的影响。结果表明，由于径向向外流动，在尾随表面旋转时传热增强。通过改变雷诺数（10,000-40,000）和转速（0-400 rpm），本研究中达到的转速和浮力参数分别为0-0.58和0-1.9。较高的转数和浮力参数非常相关，可用于预测等边三角形通道中的旋转热传递。

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