中文摘要：

本文对带有复合冷却结构的航空燃机高压涡轮导向叶片进行了气热耦合数值模拟研究，分析了温度径向分布不均匀和存在“热斑”涡轮进口条件下对气冷涡轮叶片传热的影响，研究发现进口温度径向不均匀分布在涡轮叶片径向中上部形成相对集中的带状高温区域，并使下游气膜冷却效果降低，热斑的存在进一步加剧对叶片局部区域的热冲击，复合冷却结构能够比较有效地降低由于进口温度不均匀所形成叶片表面局部高热区域的热负荷。

英文摘要：

Conjugate heat transfer numerical simulation was employed to aero engine high pressure guide vane with compound cooling techniques in this paper. Effects of non-uniform inlet temperature distributions on heat transfer of guide vane was investigated. The analyses showed that the non-uniform turbine inlet temperature distribution in radial direction could usually increase the heat load near the mid-span region on vane surface, and weaken the performance of downstream film cooling. The existence of combustor hot streak usually increased severer heat load on vane surface. The compound cooling techniques could effectively reduce the heat load which was caused by non-uniform turbine inlet temperature distribution.