液体火箭发动机针栓喷注器雾化燃烧技术研究进展  

Advances in atomized combustion technology research of pintleinjector for liquid rocket engines

作　　者：石璞 朱国强[1] 李进贤[1] 侯晓 SHI Pu;ZHU Guoqiang;LI Jinxian;HOU Xiao(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China;China Aerospace Science and Technology Corporation,Beijing 100048,China)

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072 [2]中国航天科技集团有限公司,北京100048

出　　处：《火箭推进》2020年第4期1-13,共13页Journal of Rocket Propulsion

基　　金：液体火箭发动机技术重点实验室基金(HTKJ2020KL011002)。

摘　　要：针栓喷注器具有结构简单、可靠性高、燃烧稳定,可实现深度节流、面关机、机构可按比例缩放、成本低等显著优点,以其为基础的推力调节技术是一种实现液体火箭发动机变推力方案的有效途径,得到了广泛的应用。基于国内外针栓喷注器及针栓式发动机技术的发展现状和应用实例,着重从喷注器雾化性能和发动机燃烧流动问题2个方面进行了分析,在此基础上提出了对喷注器及发动机技术研究方向和研究重点的建议。Pintle injector has the advantages of simple structure,high reliability,stable combustion,deep throttling,face-off capability,scalablity and low cost.Throttling technology based on pintle injector is an effective method to realize thrust regulation of liquid rocket engine,which has been widely used.Based on the development and application of pintle injector and corresponding engine technology,analysis and summary of atomization performance of pintle injector,combustion performance of pintle engine were conducted.On the basis of this,some opinions and suggestions on the research direction and emphasis of pintle injector and corresponding engine technology were proposed.

关 键 词：针栓喷注器 液体火箭发动机 推力调节 雾化性能 燃烧性能 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]