Turbine guide vane faces extremely high thermal load, especially on the leading edge region. In order to enhance cooling performance, the present study investigates the effects of leading-edge film cooling arrangements by adiabatic and aero-thermal coupled simulation. The three-row cooling design of the 25° inclined angle with the trenched holes is used to replace five-row showerhead holes. The $\text{SST}k-\omega \gamma -\text{R}{\text{e}}_{\theta }$ model is employed after conducting the numerical validation. The results show that at coolant mass flow of 0.00171 kg/s, three-row showerhead film cooling with trenched holes can provide higher laterally averaged adiabatic cooling effectiveness than three-row round holes. It can also improve cooling performance in most of the leading-edge regions, compared with five-row showerhead cooling arrangements. The three-row cooling design with trenched holes can still obtain the highest area-averaged effectiveness on either the suction side or the pressure side of the leading edge. Besides, the trenched holes are also beneficial to the reduction of the aerodynamic losses. In the aero-thermal coupled simulation, the improvement of the three-row cooling design with trenched holes decreases because of the internal cooling effect. It is also proved that the transverse trench would not lead to a local high temperature region on the metal surface. The trenched configuration above can be used on the first-stage turbine vane to increase turbine inlet temperature, improve engine efficiency, and prolong engine life.

涡轮导向叶片面临极高的热负荷，特别是在前缘区域。为了增强冷却性能，本研究通过绝热和气热耦合模拟研究了前沿薄膜冷却装置的效果。带有沟槽孔的25°倾斜角的三排冷却设计用于替代五排喷头孔。这$\text{SST}ķ-\omega \gamma -\text{[R}{\text{Ë}}_{\theta }$进行数值验证后，采用模型。结果表明，在冷却剂质量流量为0.00171 kg / s的情况下，带有三排孔的三排喷淋头薄膜冷却比三排圆孔可提供更高的横向绝热冷却效率。与五排喷头冷却装置相比，它还可以改善大多数前沿区域的冷却性能。带有沟槽孔的三排冷却设计仍可以在前缘的吸力侧或压力侧获得最高的平均面积效率。此外，沟槽孔也有利于减少空气动力学损失。在空气热耦合模拟中，由于内部冷却效果，带有沟槽孔的三排冷却设计的改进有所减少。还证明了横向沟槽不会导致金属表面上的局部高温区域。上面的沟槽结构可用于第一级涡轮叶片，以提高涡轮进口温度，提高发动机效率并延长发动机寿命。