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为了研究航空发动机热障涂层的失效机制,以及涂层界面间的三维形貌对涂层热应力的影响,使用ABAQUS有限元分析软件,计算了陶瓷层/粘结层结合界面间6种三维凹坑和凸起形貌单元形状以及尺寸对界面主应力σyy分布的影响规律.结果表明,形貌单元对界面应力有明显的影响,凹坑形貌界面上应力为压应力,凸起应力为拉应力,在形貌最低和最高处应力最大,尖角处应力相对集中.陶瓷层和粘结层的界面应力随着形貌单元尺寸的变化而发生变化,危险点处应力值随着纵向尺寸的增加而明显增大,曲率变化显著的地方存在着应力集中,曲率越大,应力越大.
In order to study the failure mechanism of the aero-engine thermal barrier coating and the influence of the three-dimensional topography of the coating interface on the thermal stress of the coating, ABAQUS finite element analysis software was used to calculate the three kinds of three-dimensional The results show that the morphological elements have a significant effect on the interface stress, the stress on the interface of the pits is compressive stress, the stress on the convexity is Tensile stress, the stress is highest at the lowest and highest part of the morphology, and the stress is relatively concentrated at the sharp corners.The interfacial stress between the ceramic layer and the adhesive layer changes with the change of the size of the topography unit.The stress value at the dangerous point varies with the longitudinal dimension Of the increase and significantly increased, there is a significant change in the curvature of the stress concentration, the greater the curvature, the greater the stress.