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Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 2: 184 - 192

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.008

Research on the Cooling Effect of Water Injection in the Flame Deflector During the Launch Process of Carrier Rockets

  • SHEN Bohan ,
  • JIANG Yi ,
  • WANG Xinyu ,
  • SONG Shize
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  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2025-02-27

  Online published: 2025-05-15

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Abstract

During the hot launch process of a carrier rocket, the high-temperature and high-pressure gas generated by the rocket engine will cause significant high-temperature erosion on flame division trough. In order to achieve the thermal protection of the division trough during launch of a rocket, the variation of the flow field during water injection onto the surface of a single-sided division trough was analyzed based on the computational fluid dynamics (CFD) method with coupled mixture multiphase flow model and Lee model for different water injection velocities for a rocket with two booster stages. The results show that spraying water into the division trough effectively suppresses the phenomenon of gas splashing, significantly reduces the distribution area of the high-temperature zone on the surface of the division trough, and provides good protection for the division trough. When the water spraying speed is low, it will cause oscillation of the maximum temperature on the surface of the division trough. As the water spraying speed increases, the degree of oscillation of the maximum temperature on the surface of the division trough gradually weakens until it disappears. As the water spraying speed increases, the maximum temperature on the surface of the division trough decreases, and the maximum vaporization rate also increases. Spraying water onto the gas jet will change the shape of the flow field. Different spraying positions will result in different distributions of physical parameters along the axis of the gas jet. Directly impacting the gas jet with the water jet will have a better cooling effect. This conclusion can provide some reference for the launch process of carrier rockets.

Key words： gas jet; gas-liquid two-phase flow; flame deflector; cooling of water injection

Cite this article

SHEN Bohan , JIANG Yi , WANG Xinyu , SONG Shize . Research on the Cooling Effect of Water Injection in the Flame Deflector During the Launch Process of Carrier Rockets[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(2) : 184 -192 . DOI: 10.15892/j.cnki.djzdxb.2025.02.008

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References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
姜毅, 蒲鹏宇, 程李东, 等. 燃气射流动力学[M]. 北京: 北京理工大学出版社, 2021:112-113.

JIANG Y, PU P Y, CHENG L D, et al. Gas jet dynamics[M]. Beijing: Beijing Institute of Technology Press, 2021:112-113.

[2]
谭大成. 弹射内弹道学[M]. 北京: 北京理工大学出版社, 2015:1-5.

TAN D C. Interior ballistics of catapules[M]. Beijing: Beijing Institute of Technology Press, 2015:1-5.

[3]
王成德. 车载垂直热发射导弹燃气流场坪影响研究[D]. 北京: 北京理工大学, 2016.

WANG C D. The study on the influence of jet flow on open-field ground of vehicle-mounted vertical thermal launched missile[D]. Beijing: Beijing Institute of Technology, 2016.

[4]
邢成龙, 乐贵高, 沈林, 等. 导流槽构型对火箭起飞时流场和声场的影响[J]. 航空动力学报, 2020, 35(3):589-596.

XING C L, YUE G G, SHEN L, et al. Influence of jet deflector configuration on flow field and acoustics field of launch vehicle at lift-off[J]. Journal of Aerospace Power, 2020, 35(3): 589-596.

[5]
GEERY E, GREENWOOD R. Water injection for rapid cooling of a flow of rocket exhaust gases[C]//AIAA.5th Propulsion Joint Specialist, June 9-13, 1969, Colorado Springs, Colorado. Reston: AIAA, 1969: 514.

[6]
MILLER M J, KOO J H. Effect of water to ablative performance under solid rocket exhaust environment[C]//AIAA.29th Joint Propulsion Conference and Exhibit, June 28-30, 1993, Monterey, California. Reston: AIAA, 1993: 2475.

[7]
BRUCE T V, NILI B, OSHIN P, et al. Multiphase modeling of water injection on flame deflector[C]//AIAA.21st AIAA Computational Fluid Dynamics Conference, June 24-27, 2013, San Diego, California. Reston: AIAA, 2013: 2592.

[8]
张曼曼, 姜毅, 史少岩, 等. 喷水系统对W形地下空间热发射流场的影响[J]. 兵工学报, 2023, 44(4):1158-1170.

ZHANG M M, JIANG Y, SHI S Y, et al. Influence on flow field of hot launch in a W-shaped underground space by water injection[J]. Acta Armamentarii, 2023, 44(4): 1158-1170.

DOI

[9]
周帆, 姜毅, 郝继光. 火箭发动机尾焰流场注水降温效果初探[J]. 推进技术, 2012, 33(2): 249-252.

ZHOU F, JIANG Y HAO J G. Exploring on cooling effect of aater injection on rocket motor exhaust[J]. Journal of Propulsion Technology, 2012, 33(2): 249-252.

[10]
于邵祯, 姜毅, 刘涛, 等. 喷水对车载垂直发射导弹燃气流降温效果研究[J]. 固体火箭技术, 2015, 38(5): 628-634.

YU S Z, JIANG Y, LIU T, et al. Study on the cooling effect of water injection on flame of vertical launch system[J]. Journal of Solid Rocket Technology, 2015, 38(5): 628-634.

[11]
张京力, 姜毅, 张曼曼, 等. 基于导流器喷水的导弹燃气射流降温效果研究[J]. 弹箭与制导学报, 2022, 42(6): 117-124.

DOI

ZHANG J L, JIANG Y, ZHANG M M, et al. Research on cooling effect for missile exhaust gas based on water injection in deflector[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022, 42(6): 117-124.

[12]
张伟, 方维, 王树光, 等. 大型火箭发动机试验导流槽热防护设计[J]. 传感器世界, 2019, 25(2):7-12.

ZHANG W, FANG W, WANG S G, et al. Thermal protection design of flame diversion trough for large rocket engine test[J]. Sensor World, 2019, 25(2): 7-12.

[13]
钱卫忠, 张新玉. 基于喷水降温冷却的舷侧排气系统声学性能分析[J]. 船舶, 2019, 30(3):57-63.

QIAN W Z, ZHANG X Y. Acoustic performance analysis of side exhaust system with water spray cooling[J]. Ship & Boat, 2019, 30(3): 57-63.

[14]
张忠霞, 武齐永, 张伟, 等. 航天发射泵供喷水降温冷却系统的水锤分析及防护措施[J]. 给水排水, 2020, 56(S1):929-932.

ZHANG Z X, WU Q Y, JIANG W, et al. Analysis and protective measures for the hydraulic shock in the water pump cooling system for rocket launching[J]. Water & Wastewater Engineering, 2020, 56(S1): 929-932.

[15]
陆禹铭. 喷水射流预冷对航空发动机进气温度的影响研究[D]. 哈尔滨: 哈尔滨工程大学, 2021.

LU Y M. Investigation on the effect of pre-cooling by water injection on inlet air temperature of aero-engine[D]. Harbin: Harbin Engineering University, 2021.

[16]
张博, 王育鹏, 吴敬涛, 等. 气候实验室发动机尾气小引射比降温排放特性研究[J/OL]. 应用力学学报[2025-03-03]. https://www.cnki.com.cn/Article/CJFDTotal-YYLX20230918003.htm.

ZHANG B, WANG Y P, WU J T, et al. Emission characterization of small entrainment ratio cooling of engine exhaust gas in climate laboratory[J/OL]. Chinese Journal of Applied Mechanics[2025-03-03]. https://www.cnki.com.cn/Article/CJFDTotal-YYLX20230918003.htm.

[17]
MANNINEN M, TAIVASSALO V, KALLIO S. On the mixture model for multiphase flow[EB/OL].(1996-06-11) [2022-02-20]. https://www.mysciencework.com/publication/show/mixture-model-multiphase-flow-a80fb0fd.

[18]
LEE W H. A pressure iteration scheme for two-phase flow modeling[R]. Los Alamos: Los Alamos Scientific Laboratory, 1979.

[19]
姜毅, 周帆, 张学文. 超声速高温冲击射流注水流场实验研究[J]. 实验流体力学, 2011, 25(4):32-36.

JIANG Y, ZHOU F, ZHANG X W. Experimental study on flow field of high temperature supersonic impinging jet injected by water[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4): 32-36.

[20]
张曼曼. 集成式一体化双面导流装置对流降温防热特性及应用研究[D]. 北京: 北京理工大学, 2024

ZHANG M M. Research on convective cooling and thermal protection characteristics and application of an integrated dual-sided deflector system[D]. Beijing: Beijing Institute of Technology, 2024.

[21]
史少岩. 地下井发射过程井内流场环境特性分析及喷水改善方法研究[D]. 北京: 北京理工大学, 2019.

SHI S Y. Research on inner flow field features of underground missile silo during launching and suppression by water injection[D]. Beijing: Beijing Institute of Technology, 2019.

[22]
赵承庆, 姜毅. 气体射流动力学[M]. 北京: 北京理工大学出版社, 1998: 132.

ZHAO C Q, JIANG Y. Gas jet dynamics[M]. Beijing: Beijing Institute of Technology Press, 1998: 132.

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