高温环境下热障涂层界面失效实验表征与评价方法研究

High performance thermal barrier coatings are crucial to the development of air- craft engines. This study will focus on interfacial failure behavior of thermal barrier coatings under high temperature environments. An in-situ experimental characterization technology and evaluation methodology will be developed. High temperature cross-sectional indentation tests will be conducted to induce inter- facial fracture. Digital image correlation technology will be used to study the interfacial failure process in real time. Then an in-situ experimental characte- rization method based on high temperature indentation technology will be developed to investigate interfacial failure behavior of thermal barrier coatings. According to mechanical properties and failure patterns obtained from high temperature in- situ experiment results, interfacial failure mechanism of thermal barrier coatings will be studied under high temperature service environments. A chemo-thermo-mech- anically coupled theory model will also be proposed. A cohesive model will be ad- opted to conduct finite element analysis of interfacial failure behavior during indentation experiments. An interfacial failure mechanism chart will be given. At last, an evaluation methodology of interfacial failure behavior of thermal barrier coatings under chemo-thermo-mechanically coupled environments will be developed. We believe this study will promote the understanding of failure mechanism of ther- mal barrier coatings in service, and give some guidance for the design, prepara- tion and application of thermal barrier coatings.

本项目针对航空发动机对高性能热障涂层材料的迫切需求，开展高温环境下热障涂层材料界面失效原位实验表征与评价方法研究。开展高温环境下热障涂层材料基底侧面压入实验以诱发界面破坏，并利用数字图像相关技术对界面失效过程进行实时监测，发展热障涂层材料界面失效高温压痕原位实验表征方法；基于高温原位实验得到的性能参数和失效模式，揭示高温服役环境下热障涂层材料的界面失效机理；建立热-力-化耦合本构理论模型，开展基于内聚力模型的界面失效压痕实验数值分析，得到界面失效机制图，发展热-力-化耦合作用下热障涂层材料界面失效评价方法。由此加深对服役环境下热障涂层材料失效机理的认知，以期为热障涂层材料的设计制备和工程应用提供指导。

本项目针对航空发动机对高性能热障涂层材料的迫切需求，开展了高温环境下热障涂层界面失效原位实验表征与评价方法研究。开展了室温、400和800℃下热障涂层基底侧面压入实验以诱发界面破坏，并对界面失效过程进行实时监测，发展了热障涂层界面失效高温压痕原位实验表征方法，得到了不同温度下的界面失效模式；基于高温原位实验得到的性能参数和失效模式，揭示了服役环境下热障涂层的界面失效机理；开展了基于内聚力模型的界面失效压痕实验数值分析，发展了热-力-化耦合作用下热障涂层界面失效评价方法，分析得到了不同温度下热障涂层界面韧性。本项目为服役环境下热障涂层的失效机理研究提供了一定的补充，有望支撑航空发动机用热障涂层的设计和研发。