燃气透平叶片前缘气膜冷却效率的试验研究

An Experimental Study on Film Cooling Effectiveness over the Leading Edge of Gas Turbine Blades

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-cooled turbine blade at the leading edge,a visualized test apparatus was established,with which an experimental study on film cooling effectiveness over the leading edge was conducted,so as to analyze the influence of flowing ratio and main flow Reynolds number on the cooling effectiveness.Results show that with the rise of blowing ratio,the cooling effectiveness reduces over the areas in the downstream of film holes,but increases in the vicinity of the holes.The maximum cooling efficiency occurs on the suction surface while the minimum on the pressure surface.Cooling effectiveness over the blade is little affected by the main flow Reynolds number at low blowing ratio,however,the number plays a role in influencing the cooling effectiveness over the leading edge of turbine blade in case of a high blowing ratio.