液体火箭发动机中气液同轴直流式喷嘴研究综述  

Review on gas liquid shear coaxial injector in liquid rocket engine

作　　者：康忠涛 李向东[1] 毛雄兵[1] 李清廉[2] KANG Zhongtao;LI Xiangdong;MAC Xiongbing;LI Qinglian(Science and Technology on Scramjet Laboratory,Hypervelocity Aerodynamics Institute,Chine Aerodynamics Research and Development Center,Mianyang 621000,China 2 Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室,绵阳621000 [2]国防科技大学高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《航空学报》2018年第9期1-20,共20页Acta Aeronautica et Astronautica Sinica

基　　金：新世纪优秀人才支持计划(NCET-13-0156);国家自然科学基金(11472303;11402298);国家"973"计划(613239)~~

摘　　要：在双组元液体火箭发动机中,气液同轴直流式喷嘴得到了广泛的应用,这种喷嘴通常由中心的直流式液体喷孔和同轴气体环缝组成。气液同轴直流式喷嘴的工作特性可以分为雾化特性和燃烧特性。其中雾化特性又包括同轴气体作用下射流破碎雾化机理、雾化性能、真实发动机高温高压环境的影响、不稳定燃烧时压力振荡的影响以及自激振荡等;燃烧特性又包括火焰稳定机理、火焰结构以及真实发动机环境的影响等。本文从上述几个方面对气液同轴直流式喷嘴的工作原理进行了综述,以加深对其工作过程的认识。The gas liquid shear coaxial injector is widely used in the bipropellant liquid rocket engine.Commonly,this type of injector consists of a jet orifice in the center and an annular aperture.The operating characteristics of the gas liquid shear coaxial injector can be divided into atomization characteristics and combustion characteristics.The atomization characteristics involves the jet breakup mechanism and the spray characteristics with the coaxial gas flow,effects of high pressure and temperature in real liquid rocket engine,effects of back pressure oscillation when combustion instability occurs,self-pulsation,etc.The combustion characteristics include the mechanism of flame stabilization,flame structure,and effects of high pressure and temperature in the real liquid rocket engine.The present study reviews the aforementioned atomization and combustion characteristics of the gas liquid shear coaxial injector to deepen the understanding of the working process of the gas liquid shear coaxial injector.

关 键 词：液体火箭发动机 气液同轴直流式喷嘴 雾化 燃烧特性 燃烧不稳定 

分 类 号：V233.24[航空宇航科学与技术—航空宇航推进理论与工程]