Ceramic Matrix Composites for Commercial Aircraft Engines

The preparation technologies of continuous fiber-reinforced silicon carbide ceramic matrix composite (CMC-SiC) are carefully described, and the application fields introduced in an orderly way. As for CMC-SiC served as thermal-structure components of aero engine at thermo-mechanical-oxygenic coupling environment, three strategies were proposed to prolong the service life. With regard to some thermal-structure components with low working stress, improving the degree of densification was crucial to prolong the service life, and the related process approaches are recited. If the thermal-structure components worked under moderate stress, the matrix cracking stress (σ mc) should be improved as far as possible. The fiber preform architecture, interface shear strength, residual thermal stress and matrix strengthening are associated with σmc in this section. Introducing self-healing components was quite significant with the appearance of matrix microcracks when CMC-SiC worked in a more severe environment for hundreds of hours. The damage can be sealed by glass phase originating from the reaction between self-healing components and oxygen. The effective self-healing temperature range of different self-healing components is first summarized and distinguished. The structure, composition and preparation process of CMC-SiC should be systematically designed and optimized to achieve long duration target.