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。 In this paper, the numerical simulation of the high pressure turbine guide vane with composite cooling structure is carried out. The effects of uneven temperature distribution and turbine inlet conditions on the air cooled turbine blade transmission It is found that the radial inlet temperature is unevenly distributed in the middle of the radial direction of the turbine blade to form a relatively concentrated band-shaped high temperature zone, and the cooling effect of the downstream gas film is reduced. The presence of hot spots further aggravates the heat in the local area of ​​the blade The impact and composite cooling structure can effectively reduce the heat load on the locally hot area of ​​the blade surface caused by the non-uniform inlet temperature.