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为了研究燃气透平叶片前缘气膜冷却的传热特性,建立了叶片可视化测试试验台,对叶片前缘区域的冷却效率进行了试验研究,分析了不同吹风比、不同主流雷诺数对叶片前缘区域冷却效率的影响.结果表明:气膜孔附近的冷却效率随吹风比的增大而提高,气膜孔下游的冷却效率随吹风比的增大而降低;冷却效率最高的区域在吸力面上,最低的气膜冷却效率在压力面上产生;低吹风比时主流雷诺数对叶片冷却效率的影响较小;但在高吹风比时,主流雷诺数对叶片前缘气膜孔附近的冷却效率影响较大.
In order to study the heat transfer characteristics of film cooling on gas turbine blade leading edge, a visual test bench for the blade was set up and the cooling efficiency in the leading edge of the blade was tested. The effects of different blowing ratios, The results show that the cooling efficiency near the film hole increases with the increase of the blowing ratio, and the cooling efficiency decreases with the increase of the blowing ratio in the downstream of the film hole. In the suction surface , The lowest film cooling efficiency is produced on the pressure surface; the main Reynolds number has less influence on the cooling efficiency of the blade at low blow ratio; however, at high blow ratio, the mainstream Reynolds number Greater impact on efficiency.