热循环作用下圆筒基体热障涂层的失效过程分析  

Failure Process Analysis of Thermal Barrier Coated Cylindrical Structure under Thermal Cycling

作　　者：胡浩炬[1] 张建宇[1] 齐红宇[2] 李志永[1] 费斌军[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《材料科学与工程学报》2010年第1期13-17,61,共6页Journal of Materials Science and Engineering

摘　　要：用等离子喷涂的方法在高温合金圆筒上制备热障涂层,通过红外线辐照圆筒外部对试件进行加热以及内部通冷却空气强制冷却的方法对热障涂层系统进行了热循环失效试验。利用有限元工具ABAQUS对热障涂层系统中的瞬时温度场与应力场进行了计算以分析热障涂层的失效原因。计算结果表明,试样处于稳态最高温度时以及降温过程开始的很短时间内,陶瓷层中出现较大的周向拉应力,该应力将导致热障涂层出现表面垂直裂纹;陶瓷层与粘接层界面的径向应力不足以引起界面的开裂,界面的起裂来源于垂直裂纹出现后所带来的边缘效应。Thermal barrier coated specimens were prepared by the plasma spraying technique.Thermal cycling experiments were carried out with infrared radiating the outer surface and forced cooling the inner surface.Finite element analysis software ABAQUS was employed to study the transient temperature and stresses in thermal barrier coatings under thermal cycling.It is showed that,the hoop tensile stress in the ceramic coat is very large when temperature reached the highest on heating up and at the beginning of cooling process,and the tensile stress exceeds the strength of ceramic coat at that time,which results in axial crack＇ appearance.In addition,radial stress at the ceramic coat/bond coat interface in an intact system is not able to induce interface cracks,interface cracks initiated by radial stress are affected by the presence of the axial cracks,possibly,edge effects.

关 键 词：热障涂层 热循环 有限元 裂纹萌生 

分 类 号：V231.91[航空宇航科学与技术—航空宇航推进理论与工程]