NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)热障涂层在1150℃水淬–热震环境中的服役行为  

Service Performance of NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12) Thermal Barrier Coating System under Water-Quenched Thermal Shock Environment at 1150℃

作　　者：邱质彬 李飞[2] 乔立捷 王浩瀚 吴淑琴 张振亚[2] 薛召露 QIU Zhibin;LI Fei;QIAO Lijie;WANG Haohan;WU Shuqin;ZHANG Zhenya;XUE Zhaolu(Huadian Electric Power Research Institute Co.,Ltd.,Hangzhou 310030,China;Key Laboratory of Green Fabrication and Surface Technology of Advanced Metal Materials(Ministry of Education),Anhui University of Technology,Anhui Ma'anshan 243000,China;School of Materials Science and Engineering,Zhejiang University,Hangzhou 310027,China)

机构地区：[1]华电电力科学研究院有限公司,杭州310030 [2]安徽工业大学先进金属材料绿色制备与表面技术教育部重点实验室,安徽马鞍山243000 [3]浙江大学材料科学与工程学院,杭州310027

出　　处：《表面技术》2024年第15期216-223,233,共9页Surface Technology

基　　金：国家自然科学基金(U22A20110);安徽省杰出青年项目(2108085J22);安徽省高校自然科学基金(RZ2100003743)。

摘　　要：目的热障涂层是主要应用于航空发动机涡轮叶片表面的高温防护材料,它可以有效降低基体的工作温度,是提高涡轮叶片的工作温度、延长其服役寿命的重要技术手段。氧化钇部分稳定的氧化锆(YSZ)在高温环境中易发生烧结、相转变等行为,降低了热障涂层的服役寿命,因此有必要研发新的热障涂层材料。方法利用大气等离子喷涂技术制备了NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7)和NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)热障涂层体系,利用XRD、DSC、SEM等系统地研究了沉积态0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)涂层的相结构和热导率等。然后,将其在室温和1150℃水淬–热震环境中进行循环服役行为测试,研究热障涂层体系在水淬–热震环境中的相结构演变、失效模式和失效机理等。结果利用大气等离子技术沉积的0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)涂层中具有非晶相,在1200℃下热处理5h后发现了SmAlO_(3)相。沉积态0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)涂层的热导率维持在1.5 W/(m·K),但随着温度的升高稍增大,经退火处理后其热导率高于沉积态0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)涂层的热导率,随着温度的升高呈先降低后升高的趋势。NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7)热障涂层体系在12次循环后失效,而NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)热障涂层体系在90次循环后失效。结论与NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7)热障涂层体系相比,NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)热障涂层体系的循环服役寿命提高了约7倍。表明0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12)是一种有潜力的热障涂层材料。Thermal barrier coatings are mainly used as high-temperature protective materials on the surface of aero-engine turbine blades to reduce the service temperature of substrate effectively,and are a key technical means to further improve the service temperature and extend the service life of turbine blades.The stabilized yttrium oxide zirconia(YSZ)undergoes sintering and phase transformation in high-temperature environments,reducing the service life of thermal barrier coatings.Therefore,it is necessary to develop new thermal barrier coating materials.The NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7) and NiCrAlY/YSZ/0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12) thermal barrier coating system was prepared by the atmospheric plasma spraying technology in this work,and the phase structure and thermal conductivity of the thermal barrier coating system were systematically studied with XRD,DSC,SEM,etc.As a comparison,NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7) thermal barrier coating system was deposited by the atmospheric plasma spraying technology,and the properties of NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7) thermal barrier coating system were also tested under the same conditions.Then,its service behavior in a water-quenched thermal shock environment between room temperature and 1150℃was studied,and the phase evolution,failure mode,and failure mechanism of thermal barrier coatings were elucidated.The 0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12) coating deposited by atmospheric plasma technology contained amorphous phases.After 5 hours of heat treatment at 1200℃,the SmAlO_(3) phase was discovered.Microcracks and pores were found on the surface and cross-sectional area of the 0.8Sm_(2)Zr_(2)O_(7)-0.2Y_(3)Al_(5)O_(12) coating,which was the typical feature of preparing thermal barrier coatings by atmospheric plasmon spraying technology.Cracks were not found at the adjacent layers in the NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7) thermal barrier coating system,indicating that the NiCrAlY/YSZ/Sm_(2)Zr_(2)O_(7) thermal barrier coating system possessed excellent adhesion.The thermal

关 键 词：热障涂层 服役温度 大气等离子喷涂技术 热导率 服役寿命 

分 类 号：TG174.4[金属学及工艺—金属表面处理]