热障涂层(TBC)被用于航空发动机涡轮叶片表面的热防护，主要由粘结层和陶瓷层组成，准确测量陶瓷层表面与粘结层/陶瓷层界面温度分布对指导涂层高隔热结构设计与制备具有重要意义。现有非接触式与接触式测温技术可测量表面温度，接触式测温技术可测量界面温度。主要介绍了3种用于测量航空发动机涡轮叶片表面温度的技术，其中，适用于TBC表面测温的包括以光学原理为主的红外辐射、荧光、晶体、光纤测温技术；以热致变原理为主的示温漆测温技术；适用于TBC界面测温的以热电原理为主的填埋式热电偶、薄膜热电偶测温技术，并介绍了其测温的原理、优势和局限性。进一步对TBC隔热机理及性能优化进行了介绍，并对TBC表/界面测温技术及涂层结构设计方向进行了展望。

Thermal barrier coatings (TBC) are used for thermal protection of aero-engine turbine blade surface, which mainly consist of bond coatings and ceramic coatings. Accurate measurement of temperature distribution on the surface of ceramic coating and bond coating/ceramic coating interface is of great significance for guiding the design and preparation of high-heat insulation structure of coating. At present, the surface temperature can be measured by the existing non-contact and contact temperature measurement technologies, and the interface temperature can be measured by the contact temperature measurement technology. In this paper, three kinds of technologies applied to the turbine blade surface temperature measurement of aeroengine were introduced. Among them, the thermal barrier coating surface temperature measurement technologies included infrared radiation, fluorescence, crystal and optical fiber, which based on the optical principle, and temperature indicating paint temperature measurement, which based on thermotropic principle. Moreover, the temperature measurement technologies of landfill thermocouple and film thermocouple based on thermoelectric principle were applied to the temperature measurements of thermal barrier coating interface, and their principle, advantages and limitations were introduced. Furthermore, the thermal insulation mechanism and performance optimization of thermal barrier coating were introduced, and the temperature measurement technology of thermal barrier coating surface or interface and the direction of coating structure designs were prospected.