Long-term ceramic matrix composite for aeroengine  

作　　者：Chaokun SONG Fang YE Laifei CHENG Yongsheng LIU Qing ZHANG 

机构地区：[1]Science and Technology on Thermostructure Composite Materials Laboratory,Northwestern Polytechnical University,Xi’an 710072,China

出　　处：《Journal of Advanced Ceramics》2022年第9期1343-1374,共32页先进陶瓷（英文）

基　　金：This work was supported by the National Natural Science Foundation of China(Grant Nos.92060202,51632007,51872229,and 51521061);the 111 Project of China(Grant No.B08040);National Science and Technology Major Project(Grant No.2017-VI-0007-0077).

摘　　要：Three strategies were proposed to prolong the service life of continuous fiber-reinforced silicon carbide ceramic matrix composite(CMC-SiC),which served as thermal-structure components of aeroengine at thermo-mechanical-oxygenic coupling environment.As for 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 were 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 were associated withσ_(mc)in this review.Introducing self-healing components was quite significant with the appearance of matrix microcracks when CMC-SiC worked at 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 was first summarized and distinguished.The structure,composition,and preparation process of CMC-SiC should be systematically designed and optimized to achieve long duration target.

关 键 词：high degree of densification matrix cracking stress SELF-HEALING DURATION silicon carbide ceramic matrix composite(CMC-SiC) 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]