摘要
利用数值计算的方法,研究了某型液体火箭发动机泵系统各构件及泵腔残余氧化剂在二次启动前滑行过程的温度变化。基于集总参数法建立了温度变化计算模型,并建立了泵腔残余氧化剂排空计算模型。计算结果与试车数据吻合良好。滑行过程中,涡轮温度下降,而泵壳体及进口管的温度升高;泵腔中残余氧化剂间歇排放。研究结果表明,滑行结束时泵系统的温度高于100℃,泵腔中残余氧化剂含汽率为1,不满足二次点火启动条件。
A model based on lumped parameter method was developed for numerical simulation of the temperature distribution in the Turbo-Pump System. A method for resolving the discharging process of remainder oxidant in pump room was also presented. An example simulation was implemented for parts of the Turbo-Pump System of a liquid rocket engine during gliding before the second start-up of the engine. The simulation results agree well with the experimental data. It is showed that during gliding, the temperature of turbo decreases, while the temperature of pump and inlet tube increases. The remainder oxidant in pump room exhausts discontinuously. It can be seen that temperature for the turbo, pump and inlet tube is higher than 100℃ and the quality in pump room is 1 at the end of gliding, obviously, which can not meet conditions of the second start-up.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2005年第5期394-397,共4页
Journal of Propulsion Technology
基金
国家自然科学基金资助项目(50323001)
关键词
液体推进剂火箭发动机
涡轮泵
温度计算
集总参数
Liquid propellant rocket engine
Turbine pump
Temperature calculation
Lumped-method
