Higher the turbine inlet temperature of a gas turbine, higher will be the efficiency, however the increase in the turbine inlet temperature is limited to the materials and the cooling strategies employed. This article presents a study on the effect of blowing ratio on film cooling effectiveness for a cylindrical hole and a diffused hole at different angles. The analysis was done for blowing ratios of 0.5, 1.0, 1.5 and 2.0 while the angle in the diffused hole was varied as 5°, 10° and 15°. A grid independence study was performed and the simulation was validated. The results of cylindrical and different angles of diffused holes were compared. For a cylindrical hole as well as diffused hole, a blowing ratio of 1.0 was found to have an optimal effectiveness. The diffused hole was found to improve the near hole and downstream effectiveness at higher blowing ratios.

中文翻译：

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不同吹气比下扩散孔薄膜冷却效果的角度影响研究

燃气涡轮机的涡轮机入口温度越高，效率越高，但是涡轮机入口温度的增加受限于所采用的材料和冷却策略。本文研究了不同角度吹气比对圆柱孔和扩散孔膜冷却效率的影响。对吹塑比为0.5、1.0、1.5和2.0进行了分析，而扩散孔中的角度变化为5°，10°和15°。进行了网格独立性研究并验证了仿真。比较了圆柱孔和不同角度的扩散孔的结果。对于圆柱形孔以及扩散孔，发现1.0的吹塑比具有最佳效果。