贾宜委,王鹤峰,王宇迪,赵帅,昂康.航空发动机涡轮叶片热障涂层研究现状[J].表面技术,2023,52(11):139-154.
JIA Yi-wei,WANG He-feng,WANG Yu-di,ZHAO Shuai,ANG Kang.Research Status on Thermal Barrier Coating of Aircraft Engine Turbine Blade[J].Surface Technology,2023,52(11):139-154 |
| 航空发动机涡轮叶片热障涂层研究现状 |
| Research Status on Thermal Barrier Coating of Aircraft Engine Turbine Blade |
| 投稿时间：2022-08-13 修订日期：2023-03-01 |
| DOI：10.16490/j.cnki.issn.1001-3660.2023.11.011 |
| 中文关键词: 航空发动机 热障涂层 涂层结构 涂层材料 涂层失效形式 |
| 英文关键词:aircraft engines thermal barrier coatings coating structures coating materials coating failure forms |
| 基金项目:山西省回国留学人员科研项目“动态压剪条件下南极固定冰屈服行为的研究”(2020-030);中国—白俄罗斯电磁环境效应“一带一路”联合实验室(ZBKF2022031101) |
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| Author | Institution |
| JIA Yi-wei | College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China |
| WANG He-feng | College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China |
| WANG Yu-di | College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China |
| ZHAO Shuai | College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China |
| ANG Kang | College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China |
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| 中文摘要: |
| 热障涂层是一种可以有效保障航空发动机涡轮叶片正常工作，同时显著提高其工作效率和服役时间的表面防护技术。热障涂层的性能在很大程度上影响叶片的承温和抗腐蚀能力，进而间接影响航空发动机的服役性能。涂层性能主要受其结构和材料2个方面的影响。介绍了涂层结构的优缺点和研究进展，当前常见的结构形式有双层结构、多层结构和梯度结构;介绍了粘结层材料的研究进展;对陶瓷层材料的研究进展进行了详述，如YSZ的掺杂改性、A2B2O7型化合物、钙钛矿结构材料以及近年来兴起的几种高熵陶瓷材料，其中高熵陶瓷材料包括:高熵稀土钽酸盐、铝酸盐、锆/铪酸盐、磷酸盐、硅酸盐以及高熵稀土氧化物，分别从热导率、热膨胀系数、断裂韧性、热循环寿命和抗腐蚀能力等方面对其进行介绍;概述了热障涂层常见的几种失效形式如:TGO失效、CMAS腐蚀以及高温烧结，并且对其发生机理进行简要的介绍;展望了热障涂层未来的发展趋势和方向。 |
| 英文摘要: |
| With the continuous development of the aviation industry, people are putting forward higher requirements for the performance of aircraft engines. Thermal barrier coating is a surface protection technology and depositing it on the engine turbine blade surface can significantly isolate high temperature and reduce thermal shock and thermal corrosion impact, to ensure the normal operation of aircraft engine turbine blade in harsh and complex environment, and can also significantly improve engine efficiency and service time. The performance of the thermal barrier coating largely affects the bearing and corrosion resistance of the blade, which in turn has an impact on the service capabilities of the aircraft engine. The performance of the coatings is mainly affected by their structure and material system. Firstly, several structural systems of thermal barrier coatings are briefly described in terms of their advantages, disadvantages and research advances. Currently common structural forms include:double-layer structures, multi-layer structures and gradient structures. The classical double-layer structure is still most widely used. The preparation process of multi-layer and gradient structures is more complex and both multi-layer and dual ceramic layer structures are prone to interfacial bonding problems in use, which limits their widespread application. Secondly, the current research status of binder layer materials for thermal barrier coatings is summarized. The current research on MCrAlY alloy and NiAl alloy mainly focuses on the modification of doping elements and MCrAlY alloy still needs to be improved in terms of interfacial bonding and high temperature oxidation resistance, while the advantage of NiAl alloy mainly lies in its creep resistance and oxidation resistance, which can be used as a more ideal binder layer material after modification. At the same time, the research progress of several ceramic layer materials is introduced, such as the doping modification of YSZ, A2B2O7-type compounds, chalcogenide structural materials and several high-entropy ceramic materials that have emerged in recent years. The high-entropy ceramic materials mainly include:high-entropy rare-earth tantalates, high-entropy rare-earth aluminates, high-entropy rare-earth zirconates/hafniumates, high-entropy rare-earth phosphates, high-entropy rare-earth silicates and high-entropy rare-earth oxides, in terms of thermophysical attributes such as thermal cycle life and CTE. Currently, among the doping modifications of YSZ, multi-oxide doping provides more comprehensive performance enhancement. Doping modifications of A2B2O7-type compounds have also yielded good results, but the strength and fracture toughness of the materials need further improvement. Among the high-entropy ceramic materials, high-entropy rare-earth zirconates and high-entropy rare-earth oxides are highly promising materials for ceramic layers. In order to meet the increasing requirements for engine performance, the improvement of the performance of thermal barrier coatings still needs to be continuously explored. Common forms of failure of thermal barrier coatings, such as TGO failure, CMAS corrosion, salt spray corrosion and high temperature sintering, are reviewed and the mechanisms by which they occur are briefly described. Finally, future trends and directions for thermal barrier coatings are presented. In future research, attention should be paid to improving the mechanical properties of coatings, as well as to investigating the mechanisms behind changes in coating performance, and to achieving more accurate predictions of coating life based on current research. |
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