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

陶瓷基复合材料（CMC）由于其良好的特性，目前正被考虑用于航空燃气轮机的热段部件。在此，提出了在面内载荷下正交 3D 编织 CMC 的微机械建模。使用三维层压理论和连续介质损伤力学推导出 3D 编织复合材料的三维有效柔度。损伤变量用于描述由于每个纤维束中的横向和基体开裂引起的刚度降低。通过引入混合模式损伤准则，建立了面内载荷下横向和基体开裂演化的计算方法。由于基体开裂周围的纤维/基体界面脱粘，3D 编织 CMC 的纤维束之间的应力重新分布被认为是捕捉基体和横向裂纹演变之间的相互作用。此外，还建立了包括有限元分析和损伤力学的细观力学模型，以评估由于编织结构几何形状引起的应力扰动。通过实验观察 3D 编织 CMC 的边缘面，以测量每个纤维束中发生的横向和基体裂纹。由微观力学和细观力学模型预测的横向和基体裂纹密度与实验结果合理一致，直至裂纹饱和。此外，