首页 | 本学科首页   官方微博 | 高级检索  
     检索      

等离子涂层热疲劳失效模式及失效机理研究
引用本文:魏洪亮,杨晓光,齐红宇,韩增祥.等离子涂层热疲劳失效模式及失效机理研究[J].航空动力学报,2008,23(2):270-275.
作者姓名:魏洪亮  杨晓光  齐红宇  韩增祥
作者单位:1.北京航空航天大学 能源与动力工程学院, 北京 100083
摘    要:开展了等离子涂层构件热疲劳实验研究,对失效过程及失效模式进行考察,分析了对失效起主导作用的应力分量.针对陶瓷层材料引入粘塑性本构模型,对涂层的热疲劳进行数值模拟研究.分析表明,氧化层厚度为2 μm时,陶瓷层波峰位置容易萌生Ⅰ型横向裂纹,界面中部偏上位置容易萌生Ⅱ型横向裂纹;氧化层厚度为8 μm时,陶瓷层内部法向应力主导横向裂纹的扩展;不同厚度的氧化层内部将形成较高的应变能密度.给出了等离子涂层内部裂纹形成过程及机理. 

关 键 词:航空、航天推进系统    热障涂层    热疲劳    失效模式    失效机理
文章编号:1000-8055(2008)02-0270-06
收稿时间:2007/1/17 0:00:00
修稿时间:2007年1月17日

Study of failure mode and failure mechanisms on thermal fatigue of plasma sprayed thermal barrier coatings
WEI Hong-liang,YANG Xiao-guang,QI Hong-yu and HAN Zeng-xiang.Study of failure mode and failure mechanisms on thermal fatigue of plasma sprayed thermal barrier coatings[J].Journal of Aerospace Power,2008,23(2):270-275.
Authors:WEI Hong-liang  YANG Xiao-guang  QI Hong-yu and HAN Zeng-xiang
Institution:1.School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China2.Beijing Institute of Aeronautical Materials, Beijing 100095, China
Abstract:Thermal fatigue test was conducted to study the failure process and failure mode of the plasma sprayed thermal barrier coating structures.The controlling factors for failure were also analyzed.Aviscoplastic constitutive model was introduced for the ceramic coat.Moreover,the thermal fatigue behavior of the coating layer was studied numerically.The analysis indicates that: mode Ⅰ crack is easily initiated at the peak position,and mode Ⅱ crack at above middle position of interfaces when TGO(thermaly growth oxides) thickness is 2 μm;the extension of transverse crack is dominated by normal stress when TGOthickness is 8 μm;high strain energy density is formed within TGOof different thickness.The process and mechanisms of crack coalescence within PS-TBC(plasma sprayed thermal grown oxides) were presented. 
Keywords:aerospace propulsion system  thermal barrier coatings  thermal fatigue  failure mode  failure mechanisms
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号