| 航空发动机热障涂层材料体系的研究 |
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| 引用本文： | 徐惠彬,宫声凯,刘福顺.航空发动机热障涂层材料体系的研究[J].航空学报,2000,21(1):7-12. |
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| 作者姓名： | 徐惠彬 宫声凯 刘福顺 |
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| 作者单位： | 北京航空航天大学,材料科学与工程系,北京,100083 |
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| 摘 要： | 介绍了热障涂层的结构、陶瓷表层材料和中间粘结层的材料发展趋势。热障涂层的结构已由经典的双层结构向成分、结构连续变化的梯度结构发展,涂层的寿命有明显的提高。制备方法中电子束物理气相沉积技术具有明显优势。热障涂层表层材料的最佳成分是(质量百分数6%～8%)Y2O3部分稳定的ZrO2陶瓷材料。粘结层体系发展的一个重要趋势是能同时保证力学性能和抗氧化性能的低Al含量NiCoCrAlY。
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| 关 键 词： | 热障涂层 ZrO2 涡轮发动机 |
| 文章编号： | 1000-6893(2000)01-0007-06 |
| 收稿时间： | 1998-11-11; |
| 修稿时间： | 1998-11-11 |
RECENT DEVELOPMENT IN MATERIALS DESIGN OF THERMAL BARRIER COATINGS FOR GAS TURBINE |
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| XU Hui-bin,GONG Sheng-kai,LIU Fu-shun.RECENT DEVELOPMENT IN MATERIALS DESIGN OF THERMAL BARRIER COATINGS FOR GAS TURBINE[J].Acta Aeronautica et Astronautica Sinica,2000,21(1):7-12. |
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| Authors: | XU Hui-bin GONG Sheng-kai LIU Fu-shun |
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| Affiliation: | Department of Materials Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing,100083,China |
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| Abstract: | Ceramic thermal barrier coatings (TBCs) have been increasingly used to extend the durability of aircraft gas turbine engine. This not only increases component lifetime, but also allows higher engine temperatures and therefore better efficiency. The TBCs structure has been developed from the conventional two layer structure to a gradient structure, which provided much better thermal cycle life than the former one. Compared with the plasma spray technique, the electron beam physical vapor deposition (EB\|PVD) has led to the incorporation of very durable coatings on the most demanding rotating turbine components. The optimal chemical composition of the ceramic top coat has been determined to be 6wt%~8wt%Y 2O 3 stabilized ZrO 2(YSZ); however, more temperature resistant and more durable ceramic coating materials are still required for the future applications. The bond coat material NiCoCrAlY with more Cr and less Al content can take account of advantages for both mechanical and chemical properties of the coatings. |
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| Keywords: | TBCs ZrO_2 gas turbine |
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