Oxide‐Based Ceramic Matrix Composites for High‐Temperature Environments: A Review

The increase in demand for more efficient gas turbine engines has driven the advancement of new materials and their specific requirements. Ceramic matrix composites (CMCs) have emerged as promising materials for aerospace applications due to their stability at high temperatures and their superior weight‐to‐thrust ratio compared to Ni‐based superalloys. Within the realm of CMCs, oxide‐based variants stand out for their exceptional oxidation resistance and thermo‐mechanical properties. While oxide‐based CMCs offer superior qualities at a lower manufacturing cost, their adoption remains rather limited in comparison to non‐oxide CMCs. This limitation stems from their higher thermal expansion coefficient and reduced operational temperature. This review delves into the processing techniques, material composition, and fiber architecture design of oxide‐based CMCs. Additionally, it explores their mechanical properties and investigates failure mechanisms such as fiber debonding, delamination, and fiber pull‐outs in various thermo‐mechanical environments to ascertain their stability across diverse applications. To widely comprehend the usage of oxide‐based CMCs in aerospace applications, this review thoroughly examines their corrosion behavior and delineates effective prevention methods. The corrosion characteristics of oxide‐based CMCs are critically evaluated, along with a nuanced exploration of their potential applications beyond aerospace, encompassing sectors like nuclear power and other industries.