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碳/碳(C/C)复合材料是世界各国空天战略急需的空天飞行器热防护系统和高性能航空发动机热端部件的重要候选材料。传统的抗氧化陶瓷涂层因自身脆性,以及与C/C复合材料界面不相容等问题,限制了其高温应用。付前刚教授课题组发明了多步包埋固渗制备硅化物多相镶嵌涂层,由此形成的多相界面可诱导涂层中的裂纹转向,对裂纹尖端的热应力起到有效的释放和再分配作用,成功解决了硅化物与C/C复合材料热膨胀系数不匹配问题。研制的硅化物多相
Carbon / Carbon (C / C) composites are important candidates for thermal protection systems and hot-end components of high-performance aero-engines that are urgently needed by air-space strategies of various countries in the world. Traditional anti-oxidant ceramic coatings have limited their high temperature applications due to their inherent brittleness and incompatibility with C / C composite interfaces. Professor Qian Qiangang’s group invented multi-step embedding and solidification to prepare silicide multi-phase mosaic coating. The multi-phase interface formed by this method can induce crack in the coating and effectively release the thermal stress at the crack tip And redistribution, successfully solved the silicide and C / C composite thermal expansion coefficient does not match the problem. Development of multi-phase silicide