Modeling for Matrix Multicracking Evolution of Cross-ply Ceramic-Matrix Composites Using Energy Balance Approach
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Modeling for Matrix Multicracking Evolution of Cross-ply Ceramic-Matrix Composites Using Energy Balance Approach Li Longbiao
Received: 3 November 2014 / Accepted: 11 December 2014 # Springer Science+Business Media Dordrecht 2014
Abstract The matrix multicracking evolution of cross-ply ceramic-matrix composites (CMCs) has been investigated using energy balance approach. The multicracking of crossply CMCs was classified into five modes, i.e., (1) mode 1: transverse multicracking; (2) mode 2: transverse multicracking and matrix multicracking with perfect fiber/matrix interface bonding; (3) mode 3: transverse multicracking and matrix multicracking with fiber/matrix interface debonding; (4) mode 4: matrix multicracking with perfect fiber/matrix interface bonding; and (5) mode 5: matrix multicracking with fiber/matrix interface debonding. The stress distributions of four cracking modes, i.e., mode 1, mode 2, mode 3 and mode 5, are analysed using shear-lag model. The matrix multicracking evolution of mode 1, mode 2, mode 3 and mode 5, has been determined using energy balance approach. The effects of ply thickness and fiber volume fraction on matrix multicracking evolution of cross-ply CMCs have been investigated. Keywords Ceramic matrix Composites (CMCs) . Cross-ply . Matrix cracking . Energy balance approach
1 Introduction Ceramic materials possess high strength and modulus at elevated temperature. But their use as structural components is severely limited because of their brittleness. Continuous fiberreinforced ceramic-matrix composites (CMCs), by incorporating fibers in ceramic matrices, however, not only exploit their attractive high-temperature strength but also reduce the propensity for catastrophic failure. Carbon fiber-reinforced silicon carbide ceramic-matrix composites (C/SiC CMCs) are one of the most promising candidates for many high temperature applications, particularly as aerospace and aircraft thermostructural components [1]. The CMC flaps for exhaust nozzles of SNECMA M53 and M88 aero engines have been used for more than one decade [2]. The CMC turbine vanes have been designed and tested in the aero L. Longbiao (*) College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, No. 29, Yudao St, Nanjing 210016, People’s Republic of China e-mail: [email protected]
Appl Compos Mater
engine environment under implementation of Ultra Efficient Engine Technology (UEET) program [3]. A CMC turbine blade has been tested for 4 hours by General Electric in a modified GE F414 engine, which represents the first application of CMC material in a rotating engine part. Incorporating CMC turbine blades on a GE90-sized engine, the overall weight can be reduced by 455 kg, which represents~6 % of dry weight of full sized GE90-115 [4]. The CMC combustion chamber floating wall tiles have also been tested in the aero engine environment for 30 min, with temperature range of 1047–1227 °C and pressure of 2 MPa [5]. Knowledge of matrix multicracking evolution is very important for development and application of
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