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Journal of Advanced Ceramics 2022, 11(9): 1343-1374 https://doi.org/10.1007/s40145-022-0611-5
Review | Open Access | Issue | Published: 05 September 2022

Long-term ceramic matrix composite for aeroengine

Show Author's Information Chaokun SONG,  Fang YE( ),  Laifei CHENG( ),  Yongsheng LIU,  Qing ZHANG( )
Science and Technology on Thermostructure Composite Materials Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
Keywords:
self-healing, high degree of densification, matrix cracking stress, duration, silicon carbide ceramic matrix composite (CMC-SiC)
Cite this article:
SONG C, YE F, CHENG L, et al. Long-term ceramic matrix composite for aeroengine. Journal of Advanced Ceramics, 2022, 11(9): 1343-1374. https://doi.org/10.1007/s40145-022-0611-5
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Abstract Full text About this article

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 (σmc) should be improved as far as possible. The fiber preform architecture, interface shear strength, residual thermal stress, and matrix strengthening were associated with σmc 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.


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About this article

Long-term ceramic matrix composite for aeroengine

Show Author's information Chaokun SONG, Fang YE( ), Laifei CHENG( ), Yongsheng LIU, Qing ZHANG( )
Science and Technology on Thermostructure Composite Materials Laboratory, Northwestern Polytechnical University, Xi’an 710072, China

Abstract

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 (σmc) should be improved as far as possible. The fiber preform architecture, interface shear strength, residual thermal stress, and matrix strengthening were associated with σmc 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.

Keywords: self-healing, high degree of densification, matrix cracking stress, duration, silicon carbide ceramic matrix composite (CMC-SiC)

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Publication history
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Acknowledgements
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Publication history

Received: 03 March 2022
Revised: 01 May 2022
Accepted: 07 May 2022
Published: 05 September 2022
Issue date: September 2022

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© The Author(s) 2022.

Acknowledgements

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), and National Science and Technology Major Project (Grant No. 2017-VI-0007-0077).

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