| Abstract Scope |
The use of continuous fiber reinforced ceramic matrix composites (CMCs) has recently rapidly accelerated, particularly in aero-propulsion. For example, GE Aviation has successfully certified their 2400F SiC/SiC CMC shroud in the CFM International LEAP® engine and an Ox-Ox mixer, center body and cowl cover for the new GE Passport engine (J. Steibel, American Ceramic Society Bulletin, Vol. 98, No. 3). However, despite the recent success of the implementation of advanced CMCs in new systems, damage models to support the design, certification and sustainment of safety critical CMC components are lacking. Here we propose a simple but robust formulation for a two-dimensional continuum damage model derived via a thermodynamics-based approach. Specifically, we account for damage due to matrix cracking in both the fiber and transverse directions. The process of model calibration, verification and validation is discussed. The model is implemented using nonlinear laminate theory to analyze unidirectional laminate-based CMCs. |