This study investigates the film cooling characteristics of four cooling schemes of a gas turbine vane at various mass flux ratios (8.0%, 8.5% and 9.0%) using the Pressure Sensitive Paint (PSP) technology. The improved cooling scheme involves the alteration from cylindrical holes to laid-back fan-shaped holes and laid-back holes on the pressure surface and the leading edge. Considering the complex fluctuations of the real engine operating environment, the one engine inoperative (OEI) situation is numerically simulated to explore the turbine vane's cooling performance at varying operating conditions. Experimental and numerical results indicate significantly enhanced film cooling effectiveness of vane with shaped holes (improved cooling schemes) compared to the cylindrical hole (baseline), particularly at higher mass flux ratio ( = 9.0%). At three OEI conditions, the film coverage of improved cooling schemes is significant compared to the baseline on the pressure side. When the OEI condition is increased from 100% to 120%, the area-averaged cooling effectiveness of the shaped hole vane decreases by 4.3%, due to the interaction between the freestream and lift-off cooling jet.

中文翻译：

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某发动机非工作状态下涡轮叶片气膜冷却特性及孔形改进的实验与数值研究

本研究使用压敏涂料 (PSP) 技术研究了燃气轮机叶片的四种冷却方案在不同质量通量比（8.0%、8.5% 和 9.0%）下的气膜冷却特性。改进的冷却方案包括由圆柱形孔改为后退式扇形孔以及压力面和前缘上的后退式孔。考虑到实际发动机运行环境的复杂波动，对单发动机不工作（OEI）情况进行数值模拟，以探讨涡轮叶片在不同工况下的冷却性能。实验和数值结果表明，与圆柱形孔（基线）相比，异形孔叶片（改进的冷却方案）的气膜冷却效果显着增强，特别是在较高的质量通量比（= 9.0%）下。在三种 OEI 条件下，改进的冷却方案的薄膜覆盖范围与压力侧的基线相比显着。当OEI条件从100%增加到120%时，由于自由流和升离冷却射流之间的相互作用，异形孔叶片的面积平均冷却效率降低了4.3%。