航空发动机涡轮叶片气膜冷却孔设计与制备技术研究进展

随着先进航空发动机对涡轮前燃气温度需求不断提升，涡轮叶片高效冷却设计技术成为亟待解决的瓶颈技术，而气膜孔冷却是涡轮叶片高效冷却设计的核心技术。本文基于航空发动机涡轮叶片采用耐高温复合材料与高效气膜冷却结构相结合的技术发展背景，综述国内外相关研究工作的进展，从涡轮叶片气膜孔的冷却机理、气膜孔的空间几何结构设计技术、气膜孔表面完整性制备技术等方面，深入总结分析涡轮叶片气膜冷却设计与制备技术领域取得的研究成果，重点论述了各国异型气膜冷却孔的设计与制备技术，并提出我国在该技术上存在的差距及未来研究重点。

Research Progress on Design and Manufacture Technologies of Film Cooling Hole for Aeroengine Turbine Blade

Along with the requirement of continuous improvement of gas temperature in the front of turbine in advanced aeroengine, it is a bottleneck technology that the efficient turbine blade cooling design technology has become to be solved urgently, while the film hole cooling is the core technology of efficient cooling design for turbine blades. Based on the technology development background of the combination of high temperature resistant composite materials and efficient cooling, the research progress is generalized and analyzed from several aspects, which include the efficient cooling mechanism of film holes and the spatial geometric design method and the surface integrity preparation technology. Meanwhile, the research results of design and manufacture technologies are mainly summarized and analyzed, the risk problems are pointed out, and it is put forward to the future researching focus of the design and manufacture technologies of the film cooling hole.