全流量补燃循环液氧甲烷发动机系统方案研究  

Research on Schemes of Full Flow Staged Combustion Cycle Liquid Oxygen/Liquid Methane Engine System

作　　者：王海燕[1] 高玉闪[1] 邢理想[1] WANG Haiyan;GAO Yushan;XING Lixiang(Xi′an Aerospace Propulsion Institute,Xi′an 710100,China)

机构地区：[1]西安航天动力研究所,西安710100

出　　处：《载人航天》2019年第2期236-242,共7页Manned Spaceflight

摘　　要：为了在现有火箭发动机的技术条件下,研制高性能、高可靠性、重复使用的液氧甲烷发动机,采用与液氧煤油和液氧甲烷发动机对比的方法,从推力室冷却难易程度、影响涡轮寿命的燃气温度、发动机运载能力等角度考虑,对全流量补燃循环液氧甲烷发动机的混合比和室压进行了优化选择,发动机在高室压和高混合比下工作性能更优;参考目前液氧煤油和液氧液氢发动机方案,对发动机的部分子系统配置进行了对比,采用泵后高压液体驱动预压涡轮、分段冷却推力室的方案技术风险小,且涡轮燃气温度较低。In order to develop a high performance,high reliability and reusable LOX(liquid oxygen)/LCH4(liquid methane)engine based on the existing rocket engine technology conditions,the mixing ratio and chamber pressure of full flow staged combustion cycle LOX/LCH4 engine were optimally selected by comparing with the LOX/LH2(liquid hydrogen)and LOX/kerosene engine and taking into account the cooling capacity of thrust chamber,the gas temperature that influencing the life of turbine and the engine’s carriage capacity.Full flow staged combustion cycle LOX/LCH4 engine had better performance in higher chamber pressure and mixing ratio.According to the current projects of LOX/LH2 and LOX/kerosene engines,comparison of some subsystem configurations were carried out.The engine with boost turbo driven by pumped propellant and thrust chamber cooled separately had smaller risk,and the turbine gas temperature did not exceed the present technical level.

关 键 词：全流量补燃循环 液氧甲烷推进剂 火箭发动机 系统配置 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]