我国新一代载人火箭液氧煤油发动机  

The LOX/Kerosene Rocket Engine for Chinese New-generation Manned Launch Vehicle

作　　者：李斌[1] 张小平[1] 马冬英[1] 

机构地区：[1]西安航天动力研究所,西安710100

出　　处：《载人航天》2014年第5期427-431,442,共6页Manned Spaceflight

摘　　要：分析了国内外载人火箭主动力的发展情况与发展趋势,介绍了我国1200 kN和180 kN两型液氧煤油发动机的研制历程、系统组成、工作原理、性能参数、关键技术和应用情况。两型发动机突破了补燃循环、自身起动、大范围工况调节、高效稳定燃烧、高压推力室冷却、反力式涡轮、大范围轴向力平衡、低温高DN值轴承、组合式涡轮泵密封、大直径低温阀、高精度调节器、推力矢量控制等关键技术。目前,两型发动机研制工作已基本完成,将成为我国新一代载人火箭的动力组合,实现我国航天主动力的更新换代。The development status and the trend of foreign and Chinese manned launch vehicles main power system were analyzed , and the research history , system composition , working principle , performance parameters , key technology and application prediction of the engines were introduced . The key technologies including staged combustion power cycle , self start-up, work condition adjus-ting in large range , high-efficiency stable burning , high pressure thrust chamber cooling , reaction turbine, axial thrust balance in large range , low temperature high DN bearing , combined face-riding seal, big diameter low temperature valve , high precision regulator and thrust vector control were re-solved .The engines have been successfully developed in China and will be used in the new -genera-tion manned launch vehicle .

关 键 词：载人航天 运载火箭 液体火箭发动机 液氧煤油 补燃循环 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]