韩志勇,赖浩瀚,张权,严慧羽.热障涂层抗CMAS腐蚀的表面改性研究进展[J].表面技术,2024,53(16):35-50.
HAN Zhiyong,LAI Haohan,ZHANG Quan,YAN Huiyu.Advances in the Research of Surface Modification on the Resistance of Thermal Barrier Coatings to CMAS Corrosion[J].Surface Technology,2024,53(16):35-50 |
| 热障涂层抗CMAS腐蚀的表面改性研究进展 |
| Advances in the Research of Surface Modification on the Resistance of Thermal Barrier Coatings to CMAS Corrosion |
| 投稿时间：2023-10-26 修订日期：2024-03-17 |
| DOI：10.16490/j.cnki.issn.1001-3660.2024.16.003 |
| 中文关键词: 热障涂层 硅酸盐环境沉积物(CMAS) 表面改性技术 材料计算与模拟 新型热障涂层陶瓷材料 |
| 英文关键词:thermal barrier coatings silicate environmental deposits (CMAS) surface modification technologies material calculation and simulation novel ceramic-based materials for thermal barrier coatings |
| 基金项目:国家自然科学基金(U1933124) |
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| Author | Institution |
| HAN Zhiyong | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| LAI Haohan | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| ZHANG Quan | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| YAN Huiyu | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
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| 中文摘要: |
| 近年来，CaO-MgO-Al2O3-SiO2(CMAS)的高温腐蚀成为热障涂层(TBCs)失效的重要原因，严重影响航空发动机热端部件的服役安全。表面改性作为提升热障涂层耐CMAS腐蚀性能的重要途径，不仅能够抑制熔融CMAS黏附在涂层表面，还能通过物理屏障或化学牺牲层的形式来阻挡熔融CMAS的渗入与反应。重点围绕国内外表面改性技术提高热障涂层抗CMAS腐蚀性能方面取得的研究与突破，根据作用机理划分为机械法、物理表面改性、化学表面改性和电化学表面改性四大类，阐述了这4类改性技术的原理与应用，同时归纳了不同表面改性工艺的优缺点。探讨了第一性原理计算与有限元模拟在稀土氧化物掺杂的氧化钇稳定的氧化锆、稀土锆酸盐、稀土钽酸盐和钙钛矿等新型热障涂层陶瓷材料方面的研究进展，以充分了解涂层微观组织结构和界面结构演变，为新型热障涂层的设计研究提供指导。最后，展望了TBCs在高温环境应用以及腐蚀防护的发展方向。 |
| 英文摘要: |
| Thermal Barrier Coatings (TBCs) are utilized in aero-engines to reduce the temperature of hot-end components and offer mechanical and chemical protection. However, as engine service temperature rises, TBCs will be corroded due to the introduction of siliceous mineral fragments such as sand, dust, and volcanic ash composed predominantly of CaO, MgO, Al2O3, and SiO2 (CMAS). This corrosion can pose a potential hazard and jeopardize the safety of aero-engine hot-end components. To ensure the safe operation of aero-engines, it is essential to addressing this issue. Surface modification is one potentially effective method that can enhance the CMAS corrosion resistance of TBCs. This method can prevent the adhesion of molten CMAS to the coating surface, as well as hinder the infiltration and reaction of molten CMAS by creating physical barriers or chemical sacrificial layers. Surface modification technologies can consist of four categories based on their principles of mechanical, physical, chemical, and electrochemical surface modification technologies. Each category has its unique advantages and disadvantages, which are briefly outlined in the present study. Physical surface modification is a modification method that does not result in a chemical reaction on the surface of the material. This method can construct a protective layer on the surface of the material, including physical vapor deposition, laser surface modification, and intense pulsed electron beam surface modification. Chemical surface modification technology mainly includes two modification methods of sol-gel method and chemical vapor deposition. Modifying the surface composition, organization, and morphology of the material through atomic diffusion, chemical reaction, and other means, improves the surface properties of the material. Electrophoretic deposition is a type of electrochemical surface modification technology. The recent research progress in surface modification technologies for thermal barrier coatings is summarized and the design studies of new thermal barrier coatings are guided to improve the microstructure and reduce defects of thermal barrier coatings, achieving the purpose of enhancing the corrosion resistance of CMAS. Coating surface modification technologies have limitations such as thickness limitations, coating bonding issues, temperature limitations, and coating consistency that need to be overcome and improved in practice. As the temperature of aero-engines increases in the future, the requirements for surface properties will also increase. Traditional experimental methods are costly and inefficient, while computational simulation can predict and model the properties and structure of materials, reducing costs and increasing efficiency. The research progress of first-principles calculations and finite-element simulations on new thermal barrier-coated ceramic materials such as rare-earth oxide-doped yttrium oxide-stabilized zirconia, rare-earth zirconate, rare-earth tantalate, and chalcocite is discussed to fully understand the evolution of the coating microstructures and the interfacial structures. In future research, new materials and additional surface modification technologies will be explored for applications in high/ultra-high temperature environments. The emergence of these new coatings provides innovative ideas for improving and enhancing the performance of ultrahigh-temperature thermal protection, and will greatly promote the development and progress of China's high-temperature/ultrahigh-temperature field. In conclusion, by utilizing surface modification technologies and exploring new materials, it can guarantee the safety and reliability of aero-engines in high/ultra-high temperature environments. Therefore, investing in research and development to further improve the performance and reliability of TBCs is essential. |
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