期刊
AEROSPACE SCIENCE AND TECHNOLOGY
卷 86, 期 -, 页码 613-629出版社
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2019.01.060
关键词
Ceramic-matrix composites (CMCs); Fatigue; Damage evolution; Life prediction; Matrix cracking; Interface debonding
资金
- Fundamental Research Funds for the Central Universities [NS2016070]
In this paper, the fatigue damage development and lifetime of C/SiC and SiC/SiC ceramic-matrix composites (CMCs) under cyclic loading at an elevated temperature of 1300 degrees C in vacuum, in inert, in air and in steam atmospheres are investigated. The damage evolution versus applied cycles of C/SiC and SiC/SiC composites are analyzed through fatigue hysteresis-based damage parameters and fiber/matrix interface shear stress. The Global Load Sharing (GLS) criterion is used to determine the stress distribution between intact and broken fibers. The fibers failure probability of oxidized and unoxidized fibers in the oxidation region, fibers in the interface debonded region and interface bonded region are determined considering the damage mechanisms of interface wear, interface oxidation and fiber oxidation. The effects of fatigue peak stress, testing condition and fiber preforms on the damage evolution and lifetime are discussed. The fatigue life S-N curves and fatigue limit stresses of C/SiC and SiC/SiC composites at 1300 degrees C under different testing conditions are predicted. In the inert atmosphere, the fatigue limit stress is about 92% tensile strength for 3D C/SiC in vacuum atmosphere, 82% tensile strength for 2D C/SiC in argon atmosphere, 37% tensile strength for 2D SiC/SiC in N-2 atmosphere, and 32% tensile strength for 2D SiC/SiC in argon atmosphere, the fatigue limit stress of C/SiC is much higher than that of SiC/SiC; however, in air and in steam atmospheres, the fatigue limit stress of SiC/SiC composite is higher than that of C/SiC. (C) 2019 Elsevier Masson SAS. All rights reserved.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据