航天推进技术研究院主办
[1]谢远,聂万胜,高玉超,等.环境压力对气液针栓式喷嘴雾化特性的影响[J].火箭推进,2023,49(03):15-25.
XIE Yuan,NIE Wansheng,GAO Yuchao,et al.Effect of ambient pressureon the atomization characteristics of gas-liquid pintle injector[J].Journal of Rocket Propulsion,2023,49(03):15-25.
点击复制
XIE Yuan,NIE Wansheng,GAO Yuchao,et al.Effect of ambient pressureon the atomization characteristics of gas-liquid pintle injector[J].Journal of Rocket Propulsion,2023,49(03):15-25.
环境压力对气液针栓式喷嘴雾化特性的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年03期
页码:
15-25
栏目:
目次
出版日期:
2023-06-25
- Title:
- Effect of ambient pressureon the atomization characteristics of gas-liquid pintle injector
- 文章编号:
- 1672-9374(2023)03-0015-11
- Keywords:
- gas-liquid pintle injector; ambient pressure; spray cone angle; reflux zone; droplets size
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 气液针栓式喷嘴在变推力液体火箭中有重要应用。采取实验与数值计算结合的方法系统研究了不同环境压力下的针栓式喷嘴的液膜破碎过程、喷雾锥角、回流区分布、压力和液滴粒径分布等雾化特性,揭示了环境压力影响液膜破碎的3个因素:气流冲击、环境气体密度和环境压力对液膜挤压作用。结果表明:喷雾锥角会随环境压力增加而增大,但该趋势会随压力的增加而逐渐放缓。喷雾整体形态呈现锥形,喷雾中心区域存在低压回流区,回流区的液滴数目较少,但液滴粒径比较均匀。液滴主要分布在气液作用面,下游的液滴粒径较大,外部的液滴粒径比内部的大。液体火箭在启动的瞬间,燃烧室压力变化剧烈,可能导致喷雾锥角发生大幅变化,引起推进剂空间分布不均匀,对燃烧性能产生影响,因此要避免或减小较差雾化效果的燃烧室设计压力区间。
- Abstract:
- Gas-liquid pintle injector has important application in variable thrust liquid rocket. In order to study the influence of ambient pressure on the atomization characteristics of gas-liquid pintle injector, the atomization characteristics of the injector under different ambient pressures, such as the liquid film breaking process, spray cone angle, reflux zone distribution, pressure distribution and droplet size, were systematically studied by experiments and numerical computation. Three factors affecting liquid film breakage were revealed:airflow impact, ambient gas density and the effect of ambient pressure on liquid film extrusion. The results show that the spray cone angle increases with the increase of ambient pressure, but the increasing trend of spray cone angle decreases gradually. The overall shape of the spray is conical, and there is a low-pressure reflux area in the center of the spray. The number of droplets in the reflux area is small, but the particle size of droplets is relatively uniform. The droplets are mainly distributed on the gas-liquid interaction surface, and the particle size of the droplets downstream is larger, while the particle size of the droplets outside is larger than that of the droplets inside. At the moment when liquid rocket starts, the combustor pressure changes dramatically, which may lead to a large change in spray cone angle, resulting in uneven spatial distribution of propellant and affecting combustion performance. Therefore, it is necessary to avoid or reduce the design pressure interval of combustor with poor atomization.
参考文献/References:
[1] 张蒙正,张玫.航天运载器重复使用液体动力若干问题探讨[J].火箭推进,2019,45(4):9-15.
ZHANG M Z,ZHANG M.Discussion on some problems of reusable liquid-propellant engine[J].Journal of Rocket Propulsion,2019,45(4):9-15.
[2] DRESSLER G.Summary of deep throttling rocket engines with emphasis on Apollo LMDE[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2006.
[3] 谢远,聂万胜,姜传金,等.针栓式喷嘴喷雾燃烧特性研究进展[J].推进技术,2022,43(7):47-65.
[4] CASIANO M,HULKA J,YANG V.Liquid-propellant rocket engine throttling:A comprehensive review[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2009.
[5] DRESSLER G,BAUER J.TRW pintle engine heritage and performance characteristics[C]//36th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2015.
[6] 方昕昕,沈赤兵.液氧/甲烷小推力发动机及其变推力技术研究进展[J].飞航导弹,2015(4):88-95.
[7] 王凯,雷凡培,杨岸龙,等.针栓式喷注单元膜束撞击雾化混合过程数值模拟[J].航空学报,2020,41(9):123802.
[8] 方昕昕,沈赤兵,成鹏,等.针栓式喷注器雾化特性试验[J].航空动力学报,2017,32(8):1853-1860.
[9] SON M,YU K,KOO J,et al.Effects of momentum ratio and Weber number on spray half angles of liquid controlled pintle injector[J].Journal of Thermal Science,2015,24(1):37-43.
[10] RADHAKRISHNAN K,SON M,LEE K,et al.Effect of injection conditions on mixing performance of pintle injector for liquid rocket engines[J].Acta Astronautica,2018,150:105-116.
[11] KIM D,DESJARDINS O,HERRMANN M,et al.The primary breakup of a round liquid jet by a coaxial flow of gas[C]//20th Annual Conference on Liquid Atomization and Spray Systems.Chicago,Illinois:ILASS,2007.
[12] CHADHA S,JEFFERSON-LOVEDAY R,HUSSAIN T.A high-fidelity simulation of the primary breakup within suspension high velocity oxy fuel thermal spray using a coupled volume of fluid and discrete phase model[J].International Journal of Multiphase Flow,2020,133:103445.
[13] GAMERTSFELDER J,KHARE P,BRAVO L.Investigation of atomization behaviors of liquid monopropellants in pintle injectors[C]//ASME Turbo Expo 2020:Turbomachinery Technical Conference and Exposition.New York:ASME,2020.
[14] 陈仓.燃油喷雾图像宏观特性参数测量算法优化及Matlab/GUI程序实现[D].西安:长安大学,2018.
[15] 曾青华,范慧杰,王岳,等.基于主动轮廓方法提取雾化锥角[J].航空动力学报,2014,29(2):284-289.
[16] 张磊.界面不稳定性的数值模拟[D].合肥:中国科学技术大学,2003.
[17] HE X H,LIU Z L,YUAN Z Y,et al.Study on wake field and noise of underwater solid rocket engine[J].Journal of Vibroengineering,2021,23(8):1856-1869.
[18] CHEN W,ZHANG L F.Coupled VOF and DPM models to analyze the motion of bubbles in a continuous casting strand[C]//7th International Conference on Modelling and Simulation of Metallurgical Processes in Steelmaking.Qingdao:[s.n.],2017.
[19] 兰治科,李勇,苏光辉,等.连续液相碎化过程数值模拟研究[J].当代化工研究,2021(10):4-6.
[20] ZHOU R,SHEN C B,JIN X.Numerical study on the morphology of a liquid-liquid pintle injector element primary breakup spray[J].Journal of Zhejiang University-SCIENCE A,2020,21(8):684-694.
备注/Memo
收稿日期:2022-04-18; 修回日期:2022-05-14
基金项目:国家自然科学基金项目(12002386)
作者简介:谢远(1997—),硕士,研究领域为液体火箭喷雾燃烧。通信作者:仝毅恒(1987—),博士,讲师,研究领域为液体火箭喷雾燃烧。
更新日期/Last Update:
1900-01-01