低温预冷管路流动及传热非稳态特性研究#  

Investigation on unsteady characteristics of flow and heat transfer in cryogenic precooling pipe

作　　者：程向华[1] 薛会建[1] 李宏刚 厉彦忠[2,3] CHENG Xianghua;XUE Huijian;LI Honggang;LI Yanzhong(Xi’an Aerospace Propulsion Test Technology Institute, Xi’an 710100, China;School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China;State Key Laboratory of Technologies in Space Cryogenic Propellant, Beijing 100028, China)

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100 [2]西安交通大学能源与动力工程学院,陕西西安710049 [3]航天低温推进剂技术国家重点实验室,北京100028

出　　处：《火箭推进》2018年第6期53-56,共4页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51376142)

摘　　要：低温液体火箭发动机及管路循环预冷过程涉及复杂的流型转换及传热过程,直接影响发动机及其管路的预冷效果。为准确分析低温介质加注充填过程中循环预冷管路内部的流动及传热特性,建立了一维均相平衡态流体流动及传热数学模型,通过离散化方法分析了非稳态过程液氢预冷循环管路中流体各参数的分布,获得了低温介质充填过程管路传热变化规律及其影响因素。The circulation precooling of cryogenic liquid rocket engine and pipeline involves complicate flow regimes transform and heat transfer process,which affects the precooling effect of the rocket engine and its pipeline distinctly.In order to accurately analyze the flow regimes transform and heat transfer mechanism in the precooling loop during the filling process of cryogenic medium,a one-dimensional mathematical model of fluid dynamic and heat transfer in homogeneous equilibrium state was established.Under the unsteady state,the distribution of fluid parameters in the pipeline of liquid hydrogen precooling cycle was analyzed by using the discretized method.The heat transfer law and its influence factors of cryogenic liquid filling were obtained.The numerical results provide a theoretical basis for studying the precooling performance and optimizing the adiabatic design of pipe.

关 键 词：非稳态 循环预冷 截面含气率 膜态沸腾 

分 类 号：V434.3-34[航空宇航科学与技术—航空宇航推进理论与工程]