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[1]石 璞,朱国强,李进贤,等.液体火箭发动机针栓喷注器雾化燃烧技术研究进展[J].火箭推进,2020,46(04):1-13.
　SHI Pu,ZHU Guoqiang,LI Jinxian,et al.Advances in atomized combustion technology research of pintle injector for liquid rocket engines[J].Journal of Rocket Propulsion,2020,46(04):1-13.
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液体火箭发动机针栓喷注器雾化燃烧技术研究进展

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 46 期数: 2020年04期 页码: 1-13 栏目: 专论与综述 出版日期: 2020-08-18
Title:
Advances in atomized combustion technology research of pintle injector for liquid rocket engines
文章编号:
1672-9374(2020)04-0001-13
作者:
石 璞1; 朱国强1; 李进贤1; 侯 晓2
(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)
Author(s):
SHI Pu1; ZHU Guoqiang1; LI Jinxian1; HOU Xiao2
(1.Science and Technology on Combustion, Internal Flow and Thermo-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China; 2.China Aerospace Science and Technology Corporation, Beijing 100048, China)
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
Keywords:
pintle injector;  liquid rocket engine;  thrust control;  spray performance;  combustion performance
分类号:
V434
文献标志码:
A
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。
Abstract:
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.

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备注/Memo

收稿日期:2019-12-30; 修回日期:2020-03-25
基金项目:液体火箭发动机技术重点实验室基金(HTKJ2020KL011002)
作者简介:石璞(1995—),男,博士,研究领域为火箭发动机设计

更新日期/Last Update: 2020-07-30