航空发动机热端部件隔热陶瓷涂层应用研究

A SURVEY ON APPLICATION OF TBC FOR AEROENGINE HOT SECTIONS

针对涡轮导向器叶片和转子叶片隔热陶瓷涂层的结构体系及喷涂工艺技术发展，等离子和电子束物理气相沉积（ＥＢ－ＰＶＤ）涂层优缺点，涂层失效机理、涂层界面强度特性分析及寿命分析方法进行了阐述。并针对国内隔热涂层研究的现状及所做的初步研究工作，对我国隔热陶瓷涂层的发展提出了看法。

A systematical study on the mechanical behaviors of Thermal Barrier Coating(TBC),the thermal compatibility of TBC with basic material of turbine blade,and the interface residual stress caused by various TBC materials.The change of the blade working temperature leads to crack,separation and scars between TBC and substrate,that results in TBC failure,so the blade cannot work normally.It is discovered from the experiments that addition of trace elements Zr-Y-Nb-AL in the thermal barrier coating as the interface coherent layer enhances the combination strength between TBC and substrate significantly,increases the thermal burst resistance,improves the surface smoothness.The operating temperature of the blades with TBC is enhanced up to 200℃-300℃ higher than that of the blades without TBC.The thermal barrier coating not only can be applied to turbine blade,but also has a significant effect on the surface protection of the combustor and jet exhaust nozzle of aeroengine.