摘要
陶瓷热障涂层用于涡轮发动机的热端部件可显著提高其使用温度 ,延长部件的使用寿命 ,并提高发动机的效率。介绍了制备陶瓷热障涂层的电子束物理气相沉积技术。分析了热障涂层的剥落失效机理 ,同时对热障涂层的隔热效果的研究也进行了介绍。
Ceramic thermal barrier coatings (TBCs) have been increasingly used to extend the durability of aircraft gas turbine engine. This not only increases components lifetime, but also allows higher engine temperatures and therefore better efficiency. Compared with the plasma spray technique, the electron beam physical vapor deposition has led to the incorporation of very durable coatings on the most demanding rotating turbine components. The failure mode and the thermal barrier effect of TBCs are also discussed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2000年第C00期30-34,共5页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金! ( No.5 97710 5 8)
航空科学基金! ( N o.97H5 10 60 )
