重型运载火箭发动机涡轮部件富氧燃气通道高温防护涂层技术研究  

Study on Cermet Composite Coating Technology for Oxygen Rich Gas Channel in Engine Turbo Parts of Heavy Launch Vehicle

作　　者：宋国新 王国强 SONG Guoxin;WANG Guoqiang(Xi’an Space Engine Company Limited,Xi’an 710100,China)

机构地区：[1]西安航天发动机有限公司

出　　处：《载人航天》2020年第1期76-81,共6页Manned Spaceflight

基　　金：载人航天预先研究项目(050102)

摘　　要：针对液体火箭发动机富氧燃气通道的传统搪瓷涂层在高温、高压、高速燃气冲刷工作环境下存在的开裂和脱落问题,对金属陶瓷复合涂层进行了高温氧化防护技术研究。采用喷涂和真空烧结工艺在高温合金基材表面制备了金属陶瓷复合涂层,对其组织结构、物理特性和高温抗氧化、热震、抗火焰冲刷性能进行了分析和试验。结果表明,金属陶瓷复合涂层通过真空热扩散形成了多孔组织,在1000℃氧化和冷热交变环境下表现出优异的抗氧化、抗热震性能,能够承受1100℃、1马赫燃气冲刷。According to the working environment of the gas channel in LOX/Kerosene rocket engine,a cermet composite coating was designed.Cermet composite coating was prepared on the surface of the superalloy by spraying and vacuum sintering,the microstructure,oxidation resistance,thermal shock and flame resistance of the coating were analyzed and tested.The results showed that cavernous coating was formed by vacuum heat treatment and the coating demonstrated excellent anti-oxidation and thermal shock performance which could withstand 1000℃and a Maher gas scour.

关 键 词：金属陶瓷复合涂层 抗氧化 热震 火焰冲刷 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]