【作者】 齐红宇； 李旭； 杨晓光； 石多奇； 周立柱；

【机构】 北京航空航天大学能源与动力工程学院；

【摘要】 热障涂层作为先进的热防护技术,在航空发动机热端部件上有重要的应用,它与先进气膜冷却技术、先进单晶合金材料技术并重为航空发动机涡轮叶片三大关键技术。为了保证发动机安全可靠地工作,研究并测试热障涂层的力学参数和热疲劳特性是其工程应用的前提与基础。以我国等离子喷涂工艺获得的热障涂层为研究对象,利用共振原理和复合梁理论,获得了热障涂层表层—陶瓷层从常温到1150℃高温条件下的杨氏模量。同时鉴于热障涂层的热疲劳失效模式为剥落形式,着重对热障涂层的热疲劳特性开展研究,以带热障涂层的圆管试样为模拟件开展了热疲劳试验,试验载荷选择从50℃ /1050℃的梯形波。利用所测试的材料参数和有限元方法进行了热变形分析,提取了热疲劳寿命控制参量,对模拟试样的热疲劳寿命进行了预测,结果显示精度较为精确。更多还原

【Abstract】 The thermal barrier coatings(TBCs) are used as protective coatings for aircraft and power generation gas engine.During the last few years this technology have been introduced to the hottest parts of gas turbine.There are three advanced technologies for advanced aero-engine,the film cooling technology,single crystal superalloys and TBCs.The TBCs systems are multiplayer material systems.The material properties are not easily determined, such as Young’s modulus of the top-coating of TBCs.Using the resonant frequency and the laminated plate theory,the Young’s modulus of APS TBCs was gotten under from room temperature to 1150℃.Using a commercial finite-element program,the model geometry is that of a solid cylinder.The interface region between bond coat and TBC is modeled with a sinusoidal geometry.The temperature was cycled over a range from 50℃/1050℃.The fatigue life of TBCs was predicated.更多还原