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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6100～33000,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.
The heat transfer characteristics of turbine blade trailing edge passage with staggered ribs and column ribs under rotating and static conditions were studied experimentally.The cross section of the passage was wedge-shaped, the upper and lower ribs of the staggered rib sections were staggered and the pitch ratio was about 7, The rib segment contains two rows of disturbing flow columns.The rotational static heat transfer characteristics of the staggered rib segment and the rib segment of the trailing edge passage are analyzed under the Reynolds number of 6100 ~ 33000 and the rotation number of 0 ~ 0.6.The results show that: In static state, there is difference of heat exchange between the front and the back edge of the staggered rib segment, and the difference decreases along the length of the segment. In the fully developed segment of the staggered rib, the rotation enhances the heat transfer of the trailing edge face and weakens the heat transfer of the front face. Both the fronts and fringe edges were enhanced under the heat transfer rotation. The transitional section of the column segment under rotation reduced in scale and the strongest point of heat transfer shifted to the low radius.