Heat transfer in rotating trailing edge channels
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摘要: 用实验的方法研究了旋转和静止状态下带交错肋和柱肋的涡轮叶片尾缘通道的换热特性.通道截面为楔形,交错肋段上下表面肋错开布置,节距比约为7,柱肋段包含大小两排扰流柱.在实验雷诺数为6 100~33 000,旋转数0~0.6的工况下对比分析了尾缘通道交错肋段和柱肋段的旋转静止换热特性.研究结果表明:静态下,交错肋段前后缘面存在换热差异,且该差异沿程减小;在交错肋充分发展段,旋转增强了后缘面的换热,削弱了前缘面的换热;交错肋段前后缘面叶间处换热旋转下均得到增强;旋转下柱肋段的过渡段尺度减小,换热最强点向低半径处偏移.Abstract: The heat transfer characteristics of static and rotating turbine blade trailing edge channels with staggered-ribs and pin-fins was experimentally. The model was a wedge shaped channel. Ribs were staggered on trailing and leading walls (p/e=7), pins of two different sizes were placed in the pin-fin region. Reynolds number ranged from 6 100 to 33 000, while the Rotation number was up to 0.6 in the experiments. The results indicates that the difference of heat transfer decreases along the radial direction. Heat transfer in rotating condition increases on the trailing side, while on the leading side it decreases overall. Heat transfer near the blade tip increases on both trailing and leading walls. The scale of transition section in pin-fin region decreases under rotating condition, the max Nusselt number tends to appear in the low radius area.
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Key words:
- turbine blade cooling /
- trailing edge channel /
- pin-fin /
- staggered ribs /
- rotating
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