CMAS Corrosion Behavior and Protection Method of Thermal Barrier Coatings for Aeroengine

doi:10.11900/0412.1961.2021.00121

Acta Metall Sin

2021, Vol. 57

Issue (9): 1184-1198 DOI: 10.11900/0412.1961.2021.00121

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CMAS Corrosion Behavior and Protection Method of Thermal Barrier Coatings for Aeroengine

GUO Lei¹^,²^,³(

), GAO Yuan¹, YE Fuxing¹^,²^,³, ZHANG Xinmu¹

^1.School of Materials Science and Engineering, Tianjin University, Tianjin 300072, China
^2.Tianjin Key Laboratory of Advanced Joining Technology, Tianjin University, Tianjin 300072, China
^3.Key Laboratory of Advanced Ceramics and Machining Technology, Ministry of Education, Tianjin University, Tianjin 300072, China

Cite this article:

GUO Lei, GAO Yuan, YE Fuxing, ZHANG Xinmu. CMAS Corrosion Behavior and Protection Method of Thermal Barrier Coatings for Aeroengine. Acta Metall Sin, 2021, 57(9): 1184-1198.

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Abstract

Thermal barrier coating (TBC) is a core aero-engine turbine blade technology, which can significantly increase an engine's operating temperature, thrust, and working efficiency. Moreover, high-engine operating temperatures make aero-engine turbine blades and their TBCs suffer from severe corrosion of environmental deposits (the main components are CaO, MgO, Al₂O₃, and SiO₂, together referred to as CMAS), causing premature failure. CMAS corrosion has become a key issue that limits the service temperature and lifetimes of TBCs, and its protection has been a research hotspot. In this paper, first, the scholars' understanding of CMAS corrosion to TBCs and the characteristics of CMAS were reviewed. Then, CMAS corrosion mechanisms for TBCs were briefly described. The protection methods of TBCs from CMAS corrosion were elaborated from the aspects of TBC's surface protection layer design, coating component modification, new CMAS-resistant coating materials development, and coating microstructure design. Finally, the application of TBCs in ultrahigh temperature environments and the development direction of corrosion protection were forecasted.

Key words: gas turbine engine thermal barrier coating CMAS corrosion failure mechanism protection method

Received: 24 March 2021

ZTFLH:

TG174.4

Fund: National Natural Science Foundation of China(51971156)

About author: GUO Lei, associate professor, Tel: 18322186422, E-mail: glei028@tju.edu.cn

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https://www.ams.org.cn/EN/10.11900/0412.1961.2021.00121 OR https://www.ams.org.cn/EN/Y2021/V57/I9/1184

Fig.1 Cross-section microstructures of yttria partially stabilized zirconia (YSZ) coatings by different preparation methods^[34](a) air plasma spraying (APS) (b) electron beam physical vapor deposition (EB-PVD)

Fig.2 Degradation of thermal barrier coatings (TBCs) by CMAS (CaO, MgO, Al₂O₃, and SiO₂) at high temperatures(a) thermochemical degradation^[43](b) thermomechanical degradation^[13]

Fig.3 Cross-sectional images of YSZ coatings with Pt films after heat treatment at 1250^oC for 4 h with CMAS deposits^[54]

Fig.4 Cross-sectional microstructures of Ti₂AlC (a) and EDS results of Ca (b), Mg (c), Al (d), Ti (e), and O (f) elements^[72]

Fig.5 Cross-sectional microstructures with low (a, c) and high (b, d) magnifications of LaPO₄/YSZ coatings after CMAS attack at 1250^oC for 2 h (a, b) and 10 h (c, d)^[95]

Fig.6 Surface and fracture cross-sectional morphologies of laser-glazed coatings before (a, c, e) and after (b, d, f) parameter optimization

Fig.7 Micrographs of laser-glazed coatings after CMAS attack at 1250^oC for 0.5 h (a, b) and 4 h (c, d)^[43]

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