Abstract
Under stress-rupture loading, stochastic loading affects the internal damage evolution and lifetime of fiber-reinforced ceramic-matrix composites (CMCs) at intermediate temperatures. The damage mechanisms of the matrix cracking, fiber/matrix interface debonding and oxidation, and fiber fracture are considered in the analysis of stochastic loading. The strain, fiber/matrix interface debonding and oxidation length, and the broken fibers fraction versus the time curves of SiC/SiC composite under constant and three different stochastic loading conditions are analyzed. The effects of the stochastic loading stress level, stochastic loading time, and time spacing on the damage evolution and lifetime of SiC/SiC composite are discussed. When the stochastic loading stress level increases, the stress-rupture lifetime decreases, and the time for the interface complete debonding and oxidation decreases. When the stochastic loading time and time spacing increase, the stress-rupture lifetime decreases, and the time for the interface complete debonding and oxidation remains the same.
Highlights
Ceramic-matrix composites (CMCs) are a new type of thermal–structural–functional integrated material with the advantages of metal materials, ceramic materials, and carbon materials [1]
When ceramic-matrix composites (CMCs) are used in hot-section components in aeroengines, i.e., turbine, combustion chamber, combustion liner, and nozzles, the amount of cooling air can be significantly reduced or even zero, the combustion efficiency can be improved, and the pollution emission and noise level can be reduced
The strain, fiber/matrix interface debonding and oxidation length, and broken fibers fraction versus the time curves of SiC/SiC composite were analyzed for the Cases II, III, and IV
Summary
Ceramic-matrix composites (CMCs) are a new type of thermal–structural–functional integrated material with the advantages of metal materials, ceramic materials, and carbon materials [1]. They have the characteristics of material–structural integration. CMCs have high temperature resistance, corrosion resistance, wear resistance, low density, high specific strength, high specific modulus, low thermal expansion coefficient, insensitivity to cracks, no catastrophic damage, and other advantages [2]. CMCs can have a density reduction of 30–50% and can exceed the working temperature range [3]. With the increase of thrust–weight ratio and turbine inlet temperature, CMCs have become one of the preferred high-temperature structural materials for aeroengines. The application of CMCs in aeroengines follows the development idea from stationary parts to rotating parts, from intermediate temperature parts (i.e., 700–1000 ◦ C) to high temperature parts (i.e., 1000–1300 ◦ C), and gives priority to developing intermediate temperature and intermediate load (i.e., less than 120 MPa) stationary parts (i.e., seals and flaps, etc.), the high temperature intermediate load
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