摘要
液体火箭发动机的循环预冷是复杂的传热过程并且受到很多因素的影响,回流口位置则是影响管路预冷效果的重要因素。为了研究不同回流位置对液体火箭发动机预冷效果的影响,文中采用一维均相平衡态流体模型,通过离散化方法分析了不同回流位置时循环预冷过程中泵体温度的变化规律及预冷管路中流体各参数的分布趋势,得出回流上升管出口最佳位置。
The circulation precooling of liquid rocket engine is a complicated heat transfer process. It is influenced by many factors, among which the return flow location is very important to the purpose of preeooling. To investigate the effect of different return flow locations on the precooling of rocket engine, the one-dimensional homogeneous balance fluid dynamic model was set up. The change of pump body temperature in precooling process and the distributions of various parameters of cryogenic propulsion in the loop under steady state were analyzed using discretized method. The computational results were compared for the different return flow locations and the optimal point is found.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2008年第6期646-650,共5页
Journal of Propulsion Technology
基金
高等学校博士学科点专项科研基金(20060698021)
长江学者和创新团队发展计划(IRT0746)
关键词
循环预冷回路^+
回流
液氧贮箱
截面含气率
Circulation precooling loop ＋
Return flow
Liquid oxygen tank
Void fraction
