超高温气冷堆氦气透平直接循环中高温透平叶片、深空核动力推进器尾喷管以及航空航天技术中发动机燃烧室、透平、喷管等部件面临高温、高热流密度的工作环境，亟需采用必要的热防护措施。气膜冷却具有结构简单，冷却效率高等优点，是解决上述热防护问题的有效手段之一。按主流速度的区别，气膜冷却可以分为亚声速气膜冷却和超声速气膜冷却。其中，在超声速流场中往往不可避免的存在激波的作用，对超声速气膜冷却产生重要影响，开展激波作用下超声速主流与冷却气膜相互作用的传热和流动机理的研究具有重要的意义。本文重点研究了激波与冷却气膜之间的作用及如何抑制激波的影响，并探讨了激波与冷却气膜之间的三维效应。首先实验研究了激波作用下超声速气膜冷却流场和被保护壁面温度场，结合数值模拟研究结果，揭示了激波作用下气膜边界层内的流动和传热特性，并深入分析了激波入射于超声速气膜冷却边界层不同区域的作用规律，结果表明激波入射会破坏气膜冷却效果，激波强度越大，破坏作用越强；当激波入射于气膜冷却的核心区时，破坏效果最大。针对激波对超声速气膜冷却效率的破坏作用，研究了如何在使用一定的冷却流流量下，通过改变冷却流入口条件，来获取更好的冷却效果。结果表明存在激波入射时，减小冷却流入口高度而增大冷却流马赫数有利于提升冷却效果，其机理在于增大冷却流马赫数会增大冷却气膜动量，从而增强抵御激波干扰的能力，冷却效率提高。对激波与冷却气膜之间的三维效应问题，本文首先研究激波的三维效应，研究不同宽度的激波发生器对超声速气膜冷却的影响。结果表明，在上游区域，完全贯通激波造成的破坏作用最大，而在中下游区域，非贯通激波的破坏作用更大，主要是由于非贯通激波入射在气膜边界层中形成不均匀压力分布，导致边界层内形成展向二次流，使高温主流卷入冷却气膜层，从而破坏冷却效果。其次，本文还研究了三维结构的气膜孔情况下的超声速气膜冷却，分析了圆孔结构的超声速气膜冷却规律，结果表明无激波入射时，存在最优冷却流入口压力，使冷却流既能够较好的贴近被保护壁面，又不至于穿透主流，脱离壁面。存在激波入射时，对低冷却流入口压力，激波入射反而使冷却流更好的贴近壁面，从而使冷却效率升高。对高冷却流入口压力，激波产生的高压与冷却流的压力相互作用下会使两侧高温主流卷入冷却气膜层，进而破坏冷却效果。

For the turbine blades in Very High Temperature gas-cooled Reactor (VHTR), propelling nozzles in deep space nuclear power, combustion chamber, turbines and nozzles in scramjets, which are enduring high temperature and extreme high heat flux environment, need active thermal protection. Film cooling is one of the effective means solving the above thermal protection problems due to its simple structure and high cooling efficiency. According to the mainstream velocity, film cooling can be divided into subsonic film cooling and supersonic film cooling. In the supersonic flow field, the shock wave always occurs, which will affect supersonic film cooling performance. It is of great significance to study the heat transfer and flow mechanism between the supersonic mainstream and the coolant flow with shock wave impingement.The present study focuses on the interaction between the shock wave and coolant flow, and how to inhabit the influence of shock wave impingement, and analysis the three-dimensional effect between the shock wave and the coolant flow. Firstly, the influence of shock wave impingement was experimentally investigated, the supersonic flow field was visualized using the schlieren photography, and the protected wall temperature distribution was measured by the infrared camera. Combined with the numerical simulation analysis, the flow and heat transfer characteristics in the boundary layer under shock wave impingement were studied. The results showed that the impingement of shock wave will decrease the film cooling effectiveness. The higher the shock wave intensity, the stronger the destructive effect. When the shock wave is impinging on the core region of supersonic film cooling boundary layer, the destructive effect is the largest. To inhibit the damaging effect of shock wave on supersonic film cooling effectiveness, how to get better cooling performance by changing the coolant inlet conditions under a certain coolant mass flow rate is studied. The results show that with shock wave impingement, reducing the coolant inlet height and increasing the coolant inlet Mach number is beneficial to improve the film cooling effectiveness.For the three-dimensional effect between the shock wave and coolant flow, the present study investigated the effect of three-dimensional shock wave by using non-through shock wave generators. The results showed that in the upstream region, the completely through shock wave has the largest influence, while in the middle and downstream regions, the non-through shock wave is more destructive, mainly due to the non-through shock wave caused the non-uniform pressure distribution in the boundary layer, which will form a secondary flow, and entangle the high temperature mainstream to the coolant boundary layer, thereby decreasing the cooling effectiveness. The effect of the three-dimensional structure of the film holes on supersonic film cooling was also studied. The supersonic film cooling performance of the cylindrical hole were analyzed. The results showed that, without shock wave impingement, there exists an optimal coolant inlet pressure, so that the coolant flow can adhere to the protected wall without penetrating into the mainstream. With shock wave impingement, the shock wave working mechanism differs under different coolant inlet pressure. For the low coolant inlet pressure, the low-intensity shock wave will force the coolant flow adhere to the protected wall, thereby increasing the film cooling effectiveness. While at the high coolant inlet pressure, the interaction between the high coolant inlet pressure and high pressure generated by the shock wave formed a secondary flow in the boundary layer, so the high temperature mainstream was entangled to the coolant boundary layer, thus decreasing the cooling effectiveness.