刘嘉航,吕哲,周艳文,黄士罡,陈浩,徐能.热障涂层先进陶瓷材料研究进展[J].表面技术,2022,51(7):42-52.
LIU Jia-hang,LYU Zhe,ZHOU Yan-wen,HUANG Shi-gang,CHEN Hao,XU Neng.Research Progress of Advanced Ceramic Materials for Thermal Barrier Coatings[J].Surface Technology,2022,51(7):42-52
热障涂层先进陶瓷材料研究进展
Research Progress of Advanced Ceramic Materials for Thermal Barrier Coatings
  
DOI:10.16490/j.cnki.issn.1001-3660.2022.07.004
中文关键词:  热障涂层  陶瓷材料  微观结构  结构设计  使用性能  研究进展
英文关键词:thermal barrier coatings  ceramic materials  preparation method  structural design  functional performance  research progress
基金项目:国家自然科学基金(51702145)
作者单位
刘嘉航 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
吕哲 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
周艳文 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
黄士罡 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
陈浩 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
徐能 辽宁科技大学 材料与冶金学院,辽宁 鞍山 114051 
AuthorInstitution
LIU Jia-hang School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
LYU Zhe School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
ZHOU Yan-wen School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
HUANG Shi-gang School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
CHEN Hao School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
XU Neng School of Materials and Metallurgy, University of Science and Technology Liaoning, Liaoning Anshan 114051, China 
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中文摘要:
      随着航空航天技术的不断发展,恶劣的工作环境对镍基高温合金的使用性能提出了更高的要求,热障涂层是一种应用于涡轮发动机热端部件的表面技术,通过沉积在镍基高温合金表面以降低基底表面温度。概述了传统氧化钇部分稳定氧化锆热障涂层的性能优势,包括优异的隔热性能、较高的热膨胀系数与断裂韧性。同时归纳了氧化钇部分稳定氧化锆热障涂层在高温环境下存在的问题,包括氧化锆相变与涂层烧结造成的过早失效。在此基础上,重点综述了近年来热障涂层先进陶瓷材料的研究进展,包括稀土陶瓷材料与自愈合材料,其中稀土陶瓷材料包括稀土掺杂氧化锆、成分掺杂与结构设计的稀土锆酸盐、稀土磷酸盐、3种不同结构的稀土钽酸盐、高熵稀土陶瓷材料以及稀土铌酸盐等,自愈合材料包括二硅化钼与碳化钛。针对各种热障涂层陶瓷材料,分别从热震寿命、热膨胀系数、热导率、耐腐蚀性、断裂韧性等方面进行了归纳,并总结了各材料现阶段发展的不足之处。最后展望了热障涂层材料的发展方向。
英文摘要:
      With the continuous development of aerospace technology, the thrust-weight ratio of the engine continues to increase, and the hot end components of the turbine engine are in the face of a more severe and complex use environment. The temperature of the front air inlet of the turbine engine has exceeded the maximum operating temperature of the nickel-based superalloy, so it is necessary to protect the surface of the alloy to ensure that the heated end parts of the turbine engine can be used normally in hostile environment. Thermal barrier coating is a kind of surface technology applied to heating end parts of turbine engine, which is deposited on the surface of nickel-based superalloys to reduce the surface temperature of the substrate. The performance advantages of traditional yttria partially stabilized zirconia coatings are summarized, namely excellent thermal insulation performance, higher thermal expansion coefficient and fracture toughness. At the same time, the problems of yttria partially stabilized zirconia coatings in high temperature environments are summarized, including the premature failure of the coating caused by the phase transformation of zirconia and the sintering of the coating. On this basis, this paper focuses on the research progress of advanced ceramic materials used in thermal barrier coatings in recent years, including rare earth ceramic materials and self-healing materials. Among these materials, rare earth ceramic materials embrace rare earth doped zirconia, component doped and structurally designed rare earth zirconates, rare earth phosphates, three different structures of rare earth tantalates, high entropy rare earth ceramic materials and rare earth niobates, healing materials include molybdenum disilicide and titanium carbide. In terms of thermal shock life, high temperature thermal expansion coefficient, thermal conductivity, corrosion resistance, etc., various thermal barrier coating ceramic materials are summarized, and the current development deficiencies of each material are summarized. In conclusion, this paper prospects the development trend of thermal barrier coatings material.
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