Abstract
In this paper, the cyclic fatigue hysteresis loops of 2D woven SiC/SiC ceramic matrix composites (CMCs) at elevated temperatures in steam have been investigated. The interface slip between fibers and the matrix existing in matrix cracking modes 3 and 5, in which matrix cracking and interface debonding occurred in longitudinal yarns, is considered as the major reason for hysteresis loops of 2D woven CMCs. The hysteresis loops of 2D SiC/SiC composites corresponding to different peak stresses, test conditions, and loading frequencies have been predicted using the present analysis. The damage parameter, i.e., the proportion of matrix cracking mode 3 in the entire matrix cracking modes of the composite, and the hysteresis dissipated energy increase with increasing fatigue peak stress. With increasing cycle number, the interface shear stress in the longitudinal yarns decreases, leading to transition of interface slip types of matrix cracking modes 3 and 5.
Highlights
With the demand for high thrust–weight ratio and more efficient aero-engines, the temperature of the turbine sections will be raised to a level exceeding the limit of current metallic materials
Ceramic matrix composites (CMCs) rotating low-pressure turbine blades in a F414 turbofan demonstrator engine were successfully tested for 500 grueling cycles to validate the unprecedented temperature and durability capabilities by GE Aviation
The objective of this paper is to investigate the fatigue hysteresis loops of 2D woven SiC/SiC
Summary
With the demand for high thrust–weight ratio and more efficient aero-engines, the temperature of the turbine sections will be raised to a level exceeding the limit of current metallic materials. New materials will have to be tested and validated at very high temperatures that surpass 1300 ̋ C. Ceramic matrix composites (CMCs) are lighter than superalloys and maintain structural integrity even at higher temperatures, desirable qualities for improving-aero engine efficiency, and have already been implemented in some aero-engines’ components [1]. The CMC combustion chamber and high-pressure turbine components were designed and tested in the ground testing of GEnx aero engine [2]. The. CMC rotating low-pressure turbine blades in a F414 turbofan demonstrator engine were successfully tested for 500 grueling cycles to validate the unprecedented temperature and durability capabilities by GE Aviation. CMCs will play a key role in the performance of CFM’s LEAP turbofan engine, which will enter into service in 2016 for Airbus
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