Based on numerical simulations, the heat transfer and flow field of a turbine vane are analyzed and the film cooling is improved. The optimization objective is increasing the overall cooling effectiveness with cascade pressure loss factors staying almost unchanged. Thus, cylindrical film holes were replaced by laidback holes and V-crater holes. To analyze the effect of structural adjustment on the vane, pressure distributions, mass flow distributions, and heat transfer coefficients were investigated for internal and external cooling systems. To explain the advantages of shaped holes over cylindrical holes, the flow mechanisms, film superposition, discharge coefficients, blow ratios, and film cooling effectiveness were compared. Meanwhile, the influence of mass flow ratios and mainstream Reynolds numbers was analyzed. After optimization, at the design condition, the overall cooling effectiveness increased by 4.19% on the pressure surface and 1.78% on the suction surface. However, the cascade pressure loss factor increased by 0.26% only.

基于数值模拟，分析了涡轮叶片的传热和流场，并改进了薄膜冷却。优化目标是提高整体冷却效率，同时级联压力损失系数几乎保持不变。因此，圆柱形薄膜孔被后置孔和 V 形坑孔所取代。为了分析结构调整对叶片的影响，研究了内部和外部冷却系统的压力分布、质量流量分布和传热系数。为了解释异形孔相对于圆柱形孔的优势，比较了流动机制、薄膜叠加、排放系数、吹气比和薄膜冷却效率。同时，分析了质量流量比和主流雷诺数的影响。优化后，在设计工况下，压力面整体冷却效率提高了4.19%，吸力面提高了1.78%。然而，串级压力损失系数仅增加了 0.26%。