液体火箭发动机同轴离心式喷嘴非定常雾化特性研究进展  

Research progress on unsteady atomization characteristics of coaxial injectors in liquid rocket engine

作　　者：仝毅恒 庄逢辰 TONG Yiheng;ZHUANG Fengchen(Department of Aerospace Science and Technology,Space Engineering University,Beijing,101416,China)

机构地区：[1]航天工程大学宇航科学与技术系,北京101416

出　　处：《航天工程大学学报》2024年第1期36-47,共12页

摘　　要：在以液体燃料为推进剂的火箭发动机中,不稳定燃烧问题是长期困扰科研人员的关键难题之一。不稳定燃烧发生时,燃烧室内的压力产生周期性振荡,其必然会对推进剂喷注雾化过程产生显著影响;同时,液体推进剂的周期性脉动也是诱发不稳定燃烧的重要原因。目前,液体火箭发动机不稳定燃烧和液体推进剂喷注雾化的周期性振荡之间的耦合机制尚未明确。介绍了液体火箭发动机非定常振荡背压下的液膜破碎过程,以及定常背压下喷雾自激振荡雾化特性研究进展,提出了本领域未来研究需要重点关注的方向,期望对液体火箭发动机不稳定燃烧研究有一定指导作用。In rocket engines using liquid fuel as propellant,the problem of combustion instability is one of the key problems that have plagued researchers for a long time.When combustion instability occurs,the pressure in the combustion chamber oscillates periodically,which will inevitably have a significant impact on the propellant injection and atomization process.At the same time,the periodic pulsation of liquid propellant is also an important reason for inducing combustion instability.At present,the coupling mechanism between the combustion instability of liquid rocket engines and the periodic oscillation of liquid propellant injection and atomization has not been clarified.The research progress on the liquid film breakup process and atomization characteristics under oscillating back-pressure in liquid rocket engines are reviewed.The future research in this field is proposed.The paper might give some hints about combustion instability in liquid rocket engines.

关 键 词：雾化 背压振荡 液膜破碎 振荡喷雾 自激振荡 

分 类 号：TN951[电子电信—信号与信息处理]