Fatigue life prediction of ceramic-matrix composites
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所属单位：民航学院
发表刊物：AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY
关键字：Fatigue Aero-engine Ceramic-matrix composites CMCs Interface wear Life prediction
摘要：Purpose This paper aims to predict fatigue life and fatigue limit of fiber-reinforced ceramic-matrix composites (CMCs) with different fiber preforms, i.e. unidirectional, cross-ply, 2D-, 2.5D- and 3D-woven, at room and elevated temperatures. Design/methodology/approach Under cyclic loading, matrix multicracking and interface debonding occur upon first loading to fatigue peak stress, and the interface wear appears with increasing cycle number, leading to degradation of the interface shear stress and fibers strength. The relationships between fibers fracture, cycle number, fatigue peak stress and interface wear damage mechanism have been established based on the global load sharing (GLS) criterion. The evolution of fibers broken fraction versus cycle number curves of fiber-reinforced CMCs at room and elevated temperatures have been obtained. Findings The predicted fatigue life S-N curve can be divided into two regions, i.e. the Region I controlled by the degradation of interface shear stress and fibers strength and the Region II controlled by the degradation of fibers strength. Practical/implications The proposed approach can be used to predict the fatigue life and fatigue limit of unidirectional, cross-ply, 2D-, 2.5D- and 3D-woven CMCs under cyclic loading. Originality/value The fatigue damage mechanisms and fibers failure model were combined together to predict the fatigue life and fatigue limit of fiber-reinforced CMCs with different fiber preforms.
ISSN号：1748-8842
是否译文：否
发表时间：2018-01-01
通讯作者：李龙彪