耐温1600℃超高温Zr1-xYxTaxNbxRExO2热障涂层设计及其性能评价研究

热障涂层是先进航空发动机服役安全性与可靠性的关键。随着发动机服役温度的提升，现役氧化钇稳定氧化锆（YSZ）热障涂层材料存在高温稳定性不足(>1200℃发生相变)、抗熔盐腐蚀（CMAS）能力差的缺陷，无法满足更高温度应用需求。针对上述问题，本项目提出以“熵稳定”效应设计一种兼具相变增韧与铁弹性增韧机制的Zr1-xYxTaxNbxRExO2高熵陶瓷体系，突破传统低热导热障涂层材料脆性局限，实现服役温度1600℃且抗CMAS腐蚀性能优异。通过添加元素调控晶体结构研究，建立“耐高温-高韧性-抗熔盐腐蚀”陶瓷层材料设计方法。在此基础上，采用大气等离子喷涂方法制备涂层，开展涂层微观结构与热力学性能表征，揭示模拟服役环境下涂层结构与性能的演变行为，建立涂层成分、结构与性能之间的关联机制，进一步指导涂层材料与结构设计，为下一代航空发动机超高温热障涂层材料设计提供支撑。

Thermal barrier coatings (TBCs) is the key to the safety and reliability of advanced areo-engines. With the increasing service temperature, the insufficient high-temperature stability (phase transformation above 1200℃) and the degradation caused by melting salt (CMAS) of the current YSZ TBCs result in an ineptitude for higher temperature application. This project aims to conquer the defects of current YSZ TBCs by designing Zr1-xYxTaxNbxRExO2 materials with both phase transformation and ferro-elastic toughing based on the “entropy stabilization” effect, which is expected to break the limitation of brittleness, and realize higher service temperature (1600℃) and better CMAS corrosion resistance. The collaborative performance of “high-temperature stability/high fracture toughness/CMAS corrosion resistance” will be achieved by the regulation of crystal structures through elements selection. On this basis, the atmospheric plasma spray (APS) technique is used to prepare the target coating, the microstructures and thermodynamic performance of lamellar coatings will be characterized. The microstructure evolution and service performance of APS Zr1-xYxTaxNbxRExO2 coating under simulative extreme thermal-mechanical coupling condition will be described to establish the correlation between coating composition, coating structure and coating performance. This project will provide further guidance for the design of coating materials and coating structure, also the theoretical basis and technical support for next generation of ultra-high temperature TBCs.