硅酸盐学报

航空发动机用SiC_f/SiC陶瓷基复合材料及防护涂层研究进展

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王慧明 ¹ , 罗文东 ² , 王杰民 ³ , 吴贞 ³ , 罗颐秀 ³ , 孙鲁超 ³ , 王京阳 ³

硅酸盐学报 | 综合评述 2026,54(6): 2113-2136

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硅酸盐学报 |综合评述 2026 , 54 (6) : 2113 -2136

航空发动机用SiC_f/SiC陶瓷基复合材料及防护涂层研究进展

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王慧明¹, 罗文东², 王杰民³, 吴贞³, 罗颐秀³, 孙鲁超³, 王京阳³

作者信息

^1．辽宁材料实验室燃氢防护技术研究所，沈阳 110167

^2．中国航空制造技术研究院，北京 100024

^3．中国科学院金属研究所，沈阳材料科学国家研究中心，沈阳 110016

通讯作者:

罗文东（1987—），男，硕士，高级工程师；

孙鲁超（1984—），男，博士，研究员。

作者简介:

王慧明（1999—），男，硕士，初级工程师。

Research Progress on SiC_f/SiC Ceramic Matrix Composites and Protective Coatings in Aero Engines

Huiming WANG¹, Wendong LUO², Jiemin WANG³, Zhen WU³, Yixiu LUO³, Luchao SUN³, Jingyang WANG³

Affiliations

^1.Hydrogen fuel protection Technology Institute, Liaoning Academy of Materials, Shenyang 110167, China

^2.Manufacturing Technology Institute, Aviation Industry Corporation of China, Beijing 100024, China

^3.Institute of Metal Research, Chinese Academy of Sciences, Shenyang 110016, China

Corresponding Author:

LUO Wendong (1987-), male, Master, senior Engineer. E-mail: lwd524057@163.com;

SUN Luchao (1984-), male, Ph.D., Researcher. lcsun@imr.ac.cn

WANG Huiming (1999-), male, Master, Junior Engineer. E-mail: hmwang@lam.ln.cn

出版时间: 2026-05-12 doi: 10.14062/j.issn.0454-5648.20250926

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摘要

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碳化硅纤维增强碳化硅（SiC_f/SiC）陶瓷基复合材料具有低密度、高比强、高比模、耐高温等优点，同时克服了SiC陶瓷断裂韧性低和抗外部冲击载荷性能差的缺陷，作为航空发动机结构部件应用能减少发动机热端部件气体冷却需求，并减轻发动机重量、提升推重比和部件耐久性，在先进航空发动机热端部件上的应用趋势日益明显。美国通用、普惠和法国赛峰集团等国外企业已实现SiC_f/SiC复合材料部件的大规模生产，并成功应用于各类航空发动机燃烧室火焰筒内外环、高压涡轮外环、导向器等核心部件。同时，随着航空发动机服役温度的不断突破，陶瓷基复合材料热端部件面临的高温腐蚀问题日趋严重，发展SiC_f/SiC复合材料用防护涂层显得尤为重要。

关键词

陶瓷基复合材料 / 碳化硅纤维 / 腐蚀 / 防护涂层

Abstract

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Silicon carbide fiber reinforced silicon carbide (SiC_f/SiC) ceramic matrix composite material exhibits exceptional mechanical properties (i.e., low density, high specific modulus, high temperature resistance, etc.) due to the direct and complex interactions among the matrix, fibers, and interface phases, thus overcoming the low fracture toughness and poor performance against external impact load defects of original SiC ceramic. Consequently, SiC_f/SiC composites used as aeroengine structural components can significantly reduce the need for gas cooling in the engine's hot-end components, leading to decreased engine weight, enhanced thrust-to-weight ratio, and improved component durability.

Some international enterprises like General (GE), Pratt & Whitney (PW) and SAFRAN Group of France have realized the large-scale production of SiC_f/SiC composite components, which are successfully applied to the inner and outer rings of various aero engine combustion chamber flame tubes, high pressure turbine outer rings, guides and other core components. For instance, the ceramic matrix composite seal/regulator developed by GE is commercialized and applied to military engines such as F100, F414 and F110. Pratt & Whitney (PW) adapts the F119 engine of the world's most advanced fighter jet, the F22, with ceramic matrix composite nozzle regulator and seal validated under the IHPTET program. SNECMA develops composite systems such as A500 C/SiBC, A410 SiC/SiBC (1200 ℃) and A416 SiC/SiBC (1400 ℃). The F100-PW-229 engine nozzle regulator of F15/F16 fighter jet is prepared by A410 SiC/SiBC system and is needed to pass the 265-h test.

When the hot-end components made of the ceramic matrix composite are used in the extreme gas environment of aircraft engine, the surface of the components can be faced with corrosion from high-temperature water vapor, high-temperature molten salt, and molten oxide CaO-MgO-Al₂O₃-SiO₂ (CMAS), leading to a rapid performance degradation of SiC_f/SiC composites and premature failure of structural components. Therefore, protective coatings that are resistant to typical gas environment are needed to protect the SiC_f/SiC components, such as high-temperature oxidation resistance coating, environmental barrier coating, abrasion resistance coating, etc.. These functional coatings are expected to provide a long-term and reliable protection for SiC_f/SiC components. An investigation on the design of high-quality coatings and advanced coating preparation technology is thus an essential method to reduce damage to the SiC_f/SiC composite matrix and a critical factor in achieving breakthroughs in next-generation high thrust-to-weight ratio aeroengine technology.

Summary and Prospects

The existing domestic research and applications of SiC_f/SiC composites on static parts of turbine engines is not mature yet, and that on rotor parts is still in a preliminary research stage. For instance, the working conditions for the rotor blade are extremely harsh and its configuration is complex, which make the component structure design a core and critical technology. The turbine rotor blade must ensure the structural integrity of the blade body and tenon, as well as the continuity of the fiber in the bearing direction due to the huge centrifugal mechanical load, thereby leveraging a high tensile strength of the fibers. The structural design of turbine rotor thus must consider the characteristics of composite materials, forming a structure/material integration design method.

The upper limit of long-term service temperature for SiC_f/SiC composites based on the third-generation SiC fibers is approximately 1400 ℃. However, the wall temperature requirements for the combustion chambers of the new generation of aero-engines exceed 1600 ℃. To ensure the long-term service reliability of SiC_f/SiC composite hot-end components in high-temperature gas and corrosive environments, the design and preparation of high-quality protective coatings become one of the key breakthroughs in the technological iteration of aero-engine research and development. The development of protective coatings for the hot-end components of the new generation of aero-engines must rely on advanced technologies such as efficient screening and design of new multi-functional coating materials, innovative coating structure design and precise control of coating microstructure, large-scale preparation of coating feedstock powders, and performance evaluation and failure control of coating systems under typical service environments.

In summary, there remains a significant gap between domestic SiC_f/SiC composite materials and protective coatings, as compared with those of the Western developed countries such as the United States. There is an urgent need to systematically and progressively develop the application technology for ceramic matrix composite materials suitable for aero engines, accelerate the establishment of technical reserves, and provide competitive hot-end components materials and technological support for the high-performance aero engines in China.

Key words

ceramic matrix composites / silicon carbide silicon carbide fiber / corrosion / protective coating

引用本文

王慧明, 罗文东, 王杰民, 吴贞, 罗颐秀, 孙鲁超, 王京阳. 航空发动机用SiC_f/SiC陶瓷基复合材料及防护涂层研究进展. 硅酸盐学报, 2026 , 54 (6) : 2113 -2136 . DOI: 10.14062/j.issn.0454-5648.20250926

Huiming WANG, Wendong LUO, Jiemin WANG, Zhen WU, Yixiu LUO, Luchao SUN, Jingyang WANG. Research Progress on SiC_f/SiC Ceramic Matrix Composites and Protective Coatings in Aero Engines[J]. Journal of the Chinese Ceramic Society, 2026 , 54 (6) : 2113 -2136 . DOI: 10.14062/j.issn.0454-5648.20250926

基金

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国家自然科学基金(U21A2063)
中国航发集团产学研合作项目(HFZL2023CXY022)

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2026年第54卷第6期

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文章信息

doi: 10.14062/j.issn.0454-5648.20250926

接收时间：2025-07-17
首发时间：2026-10-22
出版时间：2026-05-12

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出版历史

收稿日期：2025-07-17
修回日期：2025-09-10

基金

国家自然科学基金(U21A2063)

中国航发集团产学研合作项目(HFZL2023CXY022)

作者信息

^1．辽宁材料实验室燃氢防护技术研究所，沈阳 110167

^2．中国航空制造技术研究院，北京 100024

^3．中国科学院金属研究所，沈阳材料科学国家研究中心，沈阳 110016

通讯作者:

罗文东（1987—），男，硕士，高级工程师；

孙鲁超（1984—），男，博士，研究员。

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https://castjournals.cast.org.cn/joweb/gsyxb/CN/10.14062/j.issn.0454-5648.20250926

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2种不同金属材料的力学参数

科 Family	属数 Number of genus	种数 Number of species	占总种数比例 Percentage of total species (%)	属 Genus	种数 Number of species	占总种数比例 Percentage of total species (%)
鹅膏菌科Amanitaceae	2	11	5.26	鹅膏菌属 Amanita	10	4.78
小菇科 Mycenaceae	2	12	5.74	丝盖伞属 Inocybe	5	2.39
多孔菌科 Polyporaceae	8	14	6.70	蜡蘑属 Laccaria	5	2.39
红菇科 Russulaceae	3	23	11.00	小皮伞属 Marasmius	6	2.87
				小菇属 Mycena	11	5.26
				光柄菇属 Pluteus	5	2.39
				红菇属 Russula	17	8.13
				栓菌属 Trametes	5	2.39

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