发汗热障涂层界面约束效应及瞬态相降温演化规律研究

面向先进航空发动机对聚酰亚胺树脂基复材更高服役温度的需求，本项目拟设计一种集隔热、散热功能一体化的发汗热障复合涂层体系，然而涂层的高温服役可靠性与涂层/复材界面结合区域的湿铺展特性和层间协同稳定性密切相关，涂层/复材界面过渡区及层间匹配性调控困难，项目拟通过表界面分析技术与数值模拟相结合的方法研究复材/粘结层/涂层体系中异质界面过渡区域的形成特征及其结构、热量及力学状态的演变规律，明确多界面层间结合机制和关键性能的主要控制因素，探索热、力耦合作用下该体系的表界面行为，以及在高温服役环境过程中瞬态烧蚀相的动态演化规律，阐明发汗热障涂层中陶瓷相的抗烧蚀隔热性能、烧蚀相的放热降温机制。本项目的实施将为复合材料耐高温防护涂层体系的发展提供新的理论和新的有效技术途径。

With the development of advanced aero-engines, it is required that the polyimide resin matrix composites have higher service performance in high temperature. This project is proposed to design a perspiration thermal barrier composite coating system with the function of heat insulation and heat dissipation, however, the high temperature service reliability of the coating is closely related to the wet spreading characteristics of the coating/composite interface zone and the interlayer coordination stability. At the same time, it is difficulty to control the matching of the interlayer and transition zone between coating/composite interface. This project is proposed to investigate the formation process of the bond interface and the evolution law of their structure, energy and mechanical state by combining surface analysis technology and numerical simulation method, explore their surface/interface behavior and reveal the main factors determining their failure mechanism and key property. It will focus on exploring the behavior of the surface/interface behavior while coupling effect of heat and force, analyzing the dynamic evolution process of transient ablative phase servicing at the high temperature environment and clarifying the mechanism of heat-insulating property of ceramic phase and heat release property of ablation phase. The results will provide new theory and new effective technical approach for the development of the thermal protective coating for resin based composites.