双推力室起动同步性研究  

Study on synchronous ignition of dual-thrust chamber engine

作　　者：李程[1] 刘站国[1] 徐浩海[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2014年第4期16-21,56,共7页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司支撑项目(2012JY67)

摘　　要：我国新一代大推力液氧/煤油补燃发动机采用双推力室方案,发动机起动时存在推力室点火不同步情况。以500 t级液氧/煤油补燃发动机为研究对象,针对起动时推力室点火不同步问题,对发动机推力室燃料路的控制方案进行了研究。建立了描述补燃循环发动机起动过程的数学模型,搭建了双推力室发动机起动仿真平台。通过对推力室燃料路两种控制方案的对比分析:指出了从降低发动机系统对双推力室不同步点火的敏感程度考虑,采用2个燃料节流阀分别控制各分支燃料路的方案较优;推力室燃料路采用一个燃料节流阀的控制方案时,推力室冷却套流阻偏差不宜大于1 MPa。LOX/kerosene staged combustion cycle engine of 500 t thrust level is a new generationhigh thrust liquid propellant rocket engine with dual-thrust chamber system made in China. Toeliminate the asynchronous ignition of the LOX/kerosene staged combustion cycle engine withdual-thrust chamber, a control scheme for fuel pathway is investigated in this paper. A mathematicmodel describing the start-up process and a start-up simulation platform of the rocket engine withdual-thrust chamber were established. Two control schemes for fuel pathway of the thruster werecomparatively analyzed. The results show that a control scheme that two throttle valves are adoptedrespectively on corresponding branch lines is better for the purpose of reducing the sensitivity ofasynchronous ignition of dual-thrust chamber engine. The deviation of the resistance betweendual-thrust cooling jackets should be less than 1 MPa if only one throttle valve is used.

关 键 词：液氧/煤油发动机 双推力室 同步点火 数值仿真 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]