低温液体火箭发动机自然循环预冷研究  

Investigation on natural circulation precooling for cryogenic liquid rocket engine

作　　者：程向华[1] 陈二锋 厉彦忠[3] 

机构地区：[1]西安航天动力试验技术研究所,西安710100 [2]北京宇航系统工程研究所,北京100076 [3]西安交通大学能源与动力工程学院,西安710049

出　　处：《火箭推进》2012年第5期1-6,36,共7页Journal of Rocket Propulsion

基　　金：国家863项目(2007AA705305)

摘　　要：液体火箭发动机自然循环预冷涉及复杂的流型转换及传热过程,并且受到很多因素的影响。采用一维均相平衡态流体数学模型,通过离散化方法分析了稳态时预冷管路中流体各参数的分布,研究了回流口位置、气枕压力及液体过冷度对液体发动机预冷性能的影响规律。计算结果表明,回流位置位于下封头以上4～6 m范围内为相对最佳,增大气枕压力和液体过冷度均对发动机预冷效果具有抑制作用。The circulation precooling process of liquid rocket engine is involved with the compli- cated flow regimes transform and heat transfer that are affected by many factors. The one-dimensional homogeneous balance fluid dynamic model was adopted to analyze the distribution of various param- eters of cryogenic propulsion in the precooling pipeline under steady state by discretized method, and investigate the effects of return location, ullage pressure and liquid condensate depression on rocket engine precooling. The results indicate the relative optimal location of return inlet is within 4 m-6 m above the bottom spherical cap, and the engine precooling performance is restained by increase of the ullage pressure and liquid condensate depression.

关 键 词：自然循环预冷 回流 过冷度 截面含气率 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]