Abstract
AbstractIn this paper, the temperature-dependent matrix multicracking evolution of carbon-fiber-reinforced silicon carbide ceramic-matrix composites (C/SiC CMCs) is investigated. The temperature-dependent composite microstress field is obtained by combining the shear-lag model and temperature-dependent material properties and damage models. The critical matrix strain energy criterion assumes that the strain energy in the matrix has a critical value. With increasing applied stress, when the matrix strain energy is higher than the critical value, more matrix cracks and interface debonding occur to dissipate the additional energy. Based on the composite damage state, the temperature-dependent matrix strain energy and its critical value are obtained. The relationships among applied stress, matrix cracking state, interface damage state, and environmental temperature are established. The effects of interfacial properties, material properties, and environmental temperature on temperature-dependent matrix multiple fracture evolution of C/SiC composites are analyzed. The experimental evolution of matrix multiple fracture and fraction of the interface debonding of C/SiC composites at elevated temperatures are predicted. When the interface shear stress increases, the debonding resistance at the interface increases, leading to the decrease of the debonding fraction at the interface, and the stress transfer capacity between the fiber and the matrix increases, leading to the higher first matrix cracking stress, saturation matrix cracking stress, and saturation matrix cracking density.
Highlights
Ceramic-matrix composites (CMCs) possess low density, high strength and modulus, and wear and corrosion resistance at elevated temperatures and have already been applied on hot-section components of aeroengines [1,2]
The CMC exhaust cone demonstrator that was designed, built, and tested by SAFRAN was certified for use on commercial aircraft by European Aviation Safety Agency and completed the first commercial flight on A320 jetliner on 2015
The occurrence of the evolution of matrix multicracking affects the mechanical behavior of fiber-reinforced CMCs [3,4,5,6,7]
Summary
Ceramic-matrix composites (CMCs) possess low density, high strength and modulus, and wear and corrosion resistance at elevated temperatures and have already been applied on hot-section components of aeroengines [1,2]. The occurrence of the evolution of matrix multicracking affects the mechanical behavior of fiber-reinforced CMCs [3,4,5,6,7]. Multiple matrix fracture and debonding of the interface and pullout of the fracture fibers at the matrix crack plane are the main damage mechanisms for the nonlinear behavior of CMCs [13,14,15,16,17,18,19,20,21]. The evolution rate of matrix multicracking, debonding fraction at the interface, and the broken fraction of the fibers affect the deformation characteristics of CMCs. For the problem of first matrix cracking, the energy balance relationship
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