液体火箭发动机液膜冷却研究综述  

Review on liquid film cooling of liquid rocket engine

作　　者：唐亮 李平 周立新 TANG Liang;LI Ping;ZHOU Lixin(Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所液体火箭发动机技术重点实验室

出　　处：《火箭推进》2020年第1期1-12,共12页Journal of Rocket Propulsion

基　　金：国家装备预研联合基金(6141B06240601)

摘　　要：液膜冷却是液体火箭发动机的一种重要的冷却方式,具有冷却结构简单、冷却能力强等优点,一般与其他冷却方式结合,实现对发动机的冷却。液膜冷却对发动机的热防护可靠性和发动机比冲均有重要的影响。通过追踪国内外液膜冷却研究现状,从液膜的形成、中心气流对液膜的夹带作用、液膜冷却分析模型以及液膜冷却对发动机性能的影响等方面,梳理了液膜冷却的研究文献,总结了当前研究中存在的不足,并从冷却剂注入结构、中心气流对液膜夹带特性、液体火箭发动机液膜冷却计算方法和推力室冷却结构/技术方案等方面提出研究展望。Liquid film cooling is an important cooling method for liquid rocket engine.It has the advantages of simple cooling structure and strong cooling capacity.It is generally combined with other cooling methods to achieve the engine cooling.Liquid film cooling has a significant impact on the thermal protection reliability and specific impulse of the liquid rocket engine.In this paper,the research literature on liquid film cooling is reviewed from the aspects of liquid film formation,liquid entrainment,liquid film cooling analysis model and the effect on engine performance.The shortcomings in the current researches are summarized,and the research prospects are proposed from the aspects of the coolant injection structure,the entrainment characteristics of liquid film by the central airflow,the calculation method of liquid film cooling in liquid rocket engine,and the new structure/technical solution of thrust chamber.

关 键 词：液体火箭发动机 液膜冷却 液膜夹带 传热 

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]