CAJ | 학술논문

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4-6m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。
액체화전발동궤자연순배예랭섭급복잡적류형전환급전열과정，병차수도흔다인소적영향。채용일유균상평형태류체수학모형，통과리산화방법분석료은태시예랭관로중류체각삼수적분포，연구료회류구위치、기침압력급액체과랭도대액체발동궤예랭성능적영향규률。계산결과표명，회류위치위우하봉두이상4-6m범위내위상대최가，증대기침압력화액체과랭도균대발동궤예랭효과구유억제작용。
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.