液体火箭发动机中气液同轴直流式喷嘴研究综述

doi:10.7527/S1000-6893.2018.22221

综述

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液体火箭发动机中气液同轴直流式喷嘴研究综述

康忠涛¹, 李向东¹, 毛雄兵¹, 李清廉²

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

收稿日期:2018-04-18 修回日期:2018-05-14 出版日期:2018-09-15 发布日期:2018-06-20
通讯作者: 康忠涛 E-mail:kangzhongtao@cardc.cn
基金资助:
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）

Review on gas liquid shear coaxial injector in liquid rocket engine

KANG Zhongtao¹, LI Xiangdong¹, MAO Xiongbing¹, LI Qinglian²

1. Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Received:2018-04-18 Revised:2018-05-14 Online:2018-09-15 Published:2018-06-20
Supported by:
Program for New Century Excellent Talents in University(NCET-13-0156); National Natural Science Foundation of China(11472303, 11402298); National Basic Research Program of China(613239)

摘要/Abstract

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。

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

Abstract: 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.

Key words: liquid rocket engine, gas liquid shear coaxial injector, atomization, combustion characteristics, combustion instability

中图分类号:

V233.2⁺4

康忠涛, 李向东, 毛雄兵, 李清廉. 液体火箭发动机中气液同轴直流式喷嘴研究综述[J]. 航空学报, 2018, 39(9): 22221-022221.

KANG Zhongtao, LI Xiangdong, MAO Xiongbing, LI Qinglian. Review on gas liquid shear coaxial injector in liquid rocket engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(9): 22221-022221.

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液体火箭发动机中气液同轴直流式喷嘴研究综述

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