液体火箭发动机自然循环回路预冷非稳态数学模型  

Unsteady Mathematic Models of Natural Circulation Loop Precooling of Liquid Rocket Engine

作　　者：陈二锋[1] 厉彦忠[1] 程向华[1] 余锋[1] 

机构地区：[1]西安交通大学能源与动力工程学院,西安710049

出　　处：《西安交通大学学报》2008年第9期1127-1131,共5页Journal of Xi'an Jiaotong University

基　　金：教育部高等学校博士学科点专项科研基金资助项目(20060698021);长江学者和创新团队发展计划资助项目(IRT0746)

摘　　要：针对液体火箭发动机自然循环回路预冷过程中的非稳态流动与传热问题,构建了一组涵盖主要传热工况的管壁与低温流体间的传热模型,耦合了循环回路的释热方程和低温流体间的流动传热方程,并采用二分法迭代求解自然循环回路预冷过程中的非稳态循环流量,建立了液体火箭发动机自然循环回路预冷的一维非稳态均相流动数学模型.与已有传热模型相比,在膜态沸腾阶段引入了反环状流膜态沸腾模型和弥散流膜态沸腾模型,保证了膜态沸腾从全液相到全气相过渡过程中物理意义上的逻辑自洽性,并以输送管为例,验证了液体火箭发动机自然循环回路预冷模型的有效性.The heat transfer models between the pipe wall and the cryogenic liquid were established to investigate the unsteady flow and heat transfer process of a natural circulation loop precooling of a liquid rocket engine. The models couple the heat release equation of the circulation loop and the flow and heat transfer equations of the cryogenic liquid. Moreover, the one-dimensional unsteady homogenous flow mathematic models were set up and solved with the bisection method to obtain the unsteady flow rate of the natural circulation loop. Unlike the existing precooling models, both the inverted annular model and the dispersed model are adopted in the prediction of filming boiling, which ensures the logicality integrity of the transition from full liquid region to full gas region. In addition, the unsteady precooling models of the natural circulation loop of a liquid rocket engine were validated by the calculation of a supply pipe.

关 键 词：液体火箭发动机 自然循环 回路预冷 膜态沸腾 

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]