航空发动机及燃气轮机涡轮叶片热障涂层技术研究及应用

Research and Application of Thermal Barrier Coatings for Aeroengine and Gas Turbine Blades

中文关键词:  涡轮叶片  热障涂层  制备技术  失效分析  航空发动机

英文关键词:turbine blade  thermal barrier coatings（TBCs）  fabrication technology  failure analysis  aeroengine

中文摘要:

      介绍了航空发动机及燃气轮机涡轮叶片热障涂层技术的研究和应用情况，对热障涂层黏结层和陶瓷层的材料、制备、应 用及主要失效原因等4个方面的现状和发展趋势进行了综述。详细介绍了应用广泛的黏结层材料MCrAlY以及近几年新兴的 PtAl；包括多元稀土氧化物掺杂ZrO2、萤石结构化合物、稀土锆酸盐等的陶瓷层材料；目前广泛用于生产的等离子喷涂、电子束物 理气相沉积等制备技术；着重介绍了热障涂层在中国的应用情况。主要从TGO和CMAS 2方面对热障涂层的失效原因分别进行 了分析。简要论述了涡轮叶片热障涂层研究未来将向着1300 ℃以上超高温陶瓷层、1200 ℃以上抗氧化并与先进单晶高温合金界 面匹配良好的金属黏结层、长寿命且抗CMAS性能良好的方向发展。

英文摘要:

      The research and application of TBCs for aeroengine and gas turbine blades were introduced. The present situation and de? velopment trend of TBCs adhesive layer and ceramic layer were reviewed in terms of material，fabrication，application and main failure rea? sons. MCrAlY，which was widely used as binder，and PtAl，which was emerging in recent years，were introduced in detail. The ceramic lay? er materials，including multiple rare earth oxides doped with ZrO2，fluorite structure compounds and rare earth zirconates，were introduced in detail. Plasma spraying and electron beam physical vapor deposition，which were widely used in production，were introduced in detail. The application of TBCs in China was emphatically introduced. The failure reasons of the TBCs were mainly analyzed from TGO and CMAS. Finally，it is briefly discussed that the development direction will be more than 1300 ℃ ultra-high temperature ceramic layer，more than 1200 ℃ oxidation resistant metal bonding layer and match well with advanced single crystal superalloy interface，long life and good CMAS resistance.