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无机材料学报

• 研究论文 • 上一篇    

SiC过渡层对SiC/SiC陶瓷基复合材料表面MoSi2-SABB涂层结合性能的影响

曹路涵1,2, 孟佳1, 薛玉冬3,4, 盛晓晨1, 崔苑苑5, 乐军1, 宋力昕1,2   

  1. 1.中国科学院特种无机涂层重点实验室,上海 200050;
    2.中国科学院大学 材料科学与光电工程中心, 北京 100049;
    3.中国科学院上 海硅酸盐研究所,高性能陶瓷和超微结构国家重点实验室,上海 200050;
    4.中国科学院 上海硅酸盐研究所,结构陶瓷与复合材料工程研究中心, 上海 200050;
    5.上海大学 材料科学与工程学院,上海 200444
  • 收稿日期:2024-12-26 修回日期:2025-03-15
  • 作者简介:曹路涵(2000-), 女, 硕士研究生. E-mail: caoluhan22@mails.ucas.ac.cn

Effect of SiC Transition Layer on Bonding Properties of MoSi2-SABB Coating on SiC/SiC Ceramic Matrix Composites

CAO Luhan1,2, MENG Jia1, XUE Yudong3,4, SHENG Xiaochen1, CUI Yuanyuan5, LE Jun1, SONG Lixin1,2   

  1. 1. Key Laboratory of Inorganic Coating Materials CAS, Shanghai Institute of Ceramics, Chinese Academy of Sciences (SICCAS), Shanghai 200050, China;
    2. Center of Materials Science and Optoelectronics Engineering, University of Chinese Academy of Sciences,Beijing 100049, China;
    3. State Key Laboratory of High-Performance Ceramics & Superfine Microstructure, Shanghai Institute of Ceramics, Chinese Academy of Sciences, Shanghai 200050, China;
    4. Structural Ceramics and Composites Engineering Research Centre, Shanghai Institute of Ceramics, Chinese Academy of Sciences, Shanghai 200050, China;
    5. School of Materials Science and Engineering, Shanghai University, Shanghai 200444, China
  • Received:2024-12-26 Revised:2025-03-15
  • About author:CAO Luhan (2000-), female, Master candidate. E-mail: caoluhan22@mails.ucas.ac.cn

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摘要： SiC/SiC陶瓷基复合材料以其耐高温、低密度、高强度等优点有望被用于可重复使用空天飞行器的热防护系统。鉴于空天飞行器面临的复杂恶劣使用环境,为满足可重复使用的要求亟需在SiC/SiC陶瓷基复合材料表面制备高温抗氧化封严涂层,因SiC/SiC陶瓷基复合材料粗糙且各向异性的表面易诱导涂层开裂失效,封严涂层设计和涂层结合性能优化有待进一步研究。本工作通过化学气相沉积法在SiC/SiC陶瓷基复合材料表面设计制备了SiC过渡层,解决了MoSi2掺杂的SiO2-Al2O3-BaO-B2O3玻璃陶瓷复合涂层(MoSi2-SABB)的开裂剥落问题,使涂层展现出良好的抗热震性能。有限元分析表明SiC过渡层能够有效降低MoSi2-SABB涂层与基材界面的残余应力,缓解残余应力的各向异性,显著提升了涂层的结合性能。结合第一性原理计算探究了不同晶型极性SiC过渡层与MoSi2-SABB涂层的结合机制,结果表明SiC过渡层的晶型与极性是影响涂层结合性能的关键因素,为SiC/SiC陶瓷基复合材料表面封严涂层的设计与涂层结合性能的优化提供了重要依据。

关键词: SiC/SiC陶瓷基复合材料, SiC过渡层, 玻璃陶瓷复合涂层, 结合性能

Abstract: SiC/SiC ceramic matrix composites (SiC/SiC CMCs) are expected to be used in the thermal protection system of reusable aerospace vehicles due to their advantages of high temperature resistance, low density, and high strength. Given the complex and harsh working environment of aerospace vehicles, it is urgent to develop a high-temperature anti-oxidation sealing coating on the surface of SiC/SiC ceramic matrix composites to meet the requirements for reusability. Since the rough and anisotropic surface of SiC/SiC ceramic matrix composites can easily induce coating cracking and failure, the design of the sealing coating and the optimization of the coating's bonding performance need to be further studied. In this work, a SiC transition layer was designed and prepared on the surface of SiC/SiC ceramic matrix composites by chemical vapor deposition, which solved the cracking and spalling problems of the MoSi2-doped SiO2-Al2O3-BaO-B2O3 glass-ceramic composite coating (MoSi2-SABB), and enabled the coating to exhibit excellent thermal shock resistance. Finite element analysis showed that the SiC transition layer could effectively reduce the residual stress at the interface between the MoSi2-SABB coating and the substrate, alleviate the anisotropy of the residual stress, and significantly improve the bonding performance of the coating. The binding mechanism of SiC transition layer with different crystal structures and polarities and MoSi2-SABB coating was investigated by first principles calculation. The results showed that the crystal structure and polarity of SiC transition layer were the key factors affecting the coating bonding performance, providing a basis for the design and optimization of the bonding performance of the surface sealing coating of SiC/SiC ceramic matrix composites.

Key words: SiC/SiC ceramic matrix composites, SiC transition layer, glass-ceramic composite coating, bonding performance

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