Micromechanical modeling for the in-plane mechanical behavior of orthogonal three-dimensional woven ceramic matrix composites with transverse and matrix cracking

Ceramic matrix composites (CMCs) are currently being considered for applications in the hot-section components of aviation gas turbines owing to their favorable characteristics. Herein, a micromechanical modeling is presented orthogonal 3 D woven CMCs under in-plane loading. The three-dimensional effective compliance composite was derived using laminate theory and continuum damage mechanics. variables were used describe stiffness reduction due transverse cracking each fiber bundle. calculation method evolutions loading established by introducing mixed-mode criteria. stress redistribution among bundles fiber/matrix interfacial debonding around capture interaction between crack evolutions. Additionally, mesomechanical model comprising finite element analysis mechanics evaluate perturbation geometry structure. edge face CMC experimentally observed measure cracks that occurred densities predicted models reasonably agreed with experimental results up saturation. Furthermore, reproduced nonlinear stress–strain response tensile shear