SiC/SiC陶瓷基复合材料环境障涂层热冲击失效机理分析  

Failure Mechanism Analysis of Environmental Barrier Coatings for SiC/SiC Ceramic-Matrix Composites Under Thermal Shock Tests

作　　者：郭小军 李龙彪[2] 胡庆[3] 曹学强[3] 胡晓安 GUO Xiao-jun;LI Long-biao;HU Qing;CAO Xue-qiang;HU Xiao-an(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Hunan Zhuzhou 412000,China;College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;State Key Laboratory of Silicate Materials for Architectures,Wuhan University of Technology,Wuhan 430070,China;School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412000 [2]南京航空航天大学民航学院,南京211106 [3]武汉理工大学硅酸盐建筑材料国家重点实验室,武汉430070 [4]南昌航空大学飞行器工程学院,南昌330063

出　　处：《失效分析与预防》2022年第5期279-285,共7页Failure Analysis and Prevention

基　　金：国家自然科学基金重点项目(92060201)。

摘　　要：环境障涂层(EBCs)是确保陶瓷基复合材料在航空发动机使用环境下可靠性与耐久性的关键因素。以聚合物浸渍热解(PIP)和化学气相渗透(CVI)工艺制备的SiC/SiC陶瓷基复合材料为基体,采用大气等离子喷涂(APS)在SiC/SiC复合材料表面制备EBCs,并分别在1200、1300℃进行热冲击试验。结果表明:PIP-SiC/SiC基体表面的EBCs在1200℃经历1425次热冲击出现了涂层剥落现象,而CVISiC/SiC基体表面的EBCs在1300℃经历2000次热冲击循环后,涂层表面依然完整,未见失效和剥落现象,这主要是由于基体的热导率差异造成的。Environmental barrier coatings(EBCs) are crucial for ensuring the reliability and durability of ceramic-matrix composites in aeroengine service environments. In this study, SiC/SiC composite fabricated by polymer impregnation and pyrolysis(PIP) and chemical vapor infiltration(CVI) processes were used as the substrate, and the EBCs on the SiC/SiC composite surface were synthesized by an atmospheric plasma spraying(APS) method. The thermal shock tests were conducted at 1200 ℃ and 1300 ℃ for the PIP and CVI-SiC/SiC with EBCs, respectively. The EBCs on the PIP-SiC/SiC surface peel off at 1200 ℃ after 1455 cycles,while the EBCs on the CVI-SiC/SiC surface remain intact with no failure or peeling after 2000 cycles at 1300 ℃, which is mainly due to the difference in thermal conductivity of the substrates.

关 键 词：SIC/SIC复合材料 环境障涂层 热冲击 涂层失效 

分 类 号：TB332[一般工业技术—材料科学与工程]