液体横向射流在气膜作用下的破碎过程

张彬; 成鹏; 李清廉; 陈慧源; 李晨阳

doi:10.7498/aps.70.20201384

摘要

为了研究液体横向射流在气膜作用下的破碎过程, 采用背景光成像技术及VOF TO DPM方法进行了实验研究和仿真研究, 模拟介质为水和空气. 研究结果表明, 液体射流在气膜作用下主要存在两种破碎过程: 柱状破碎和表面破碎. Rayleigh-Taylor (R-T)不稳定性产生的表面波是液体射流发生柱状破碎的主要原因, 气流穿透表面波的波谷导致射流柱破碎, 破碎后的液丝沿流向逐渐发展呈带状分布. Kelvin-Helmholtz (K-H)不稳定性产生的表面波是液体射流发生表面破碎的主要原因, 液丝和液滴从射流表面剥离. 局部动量比对液体横向射流的破碎过程具有重要影响, 当局部动量比较低时, 液体射流的破碎由K-H不稳定性主导; 随着局部动量比的增大液体射流的破碎逐渐由R-T不稳定性主导. 液体射流的破碎长度及穿透深度均随局部动量比的增大而增大.

关键词:

液体射流 /
破碎过程 /
表面波 /
气膜

Abstract

In order to study the breakup process of liquid jet in gas film, the backlit photography technique and the VOF TO DPM method are used for experimental and simulation research respectively. Water and air are used as simulant media. Grid adaptive technology is used to refine the gas-liquid interface grid and improve the capture accuracy of the gas-liquid interface. The results show that there are two main breakup processes of liquid jet in gas film: column breakup and surface breakup. The local high-pressure zone in front of the liquid jet makes the jet have a large normal velocity gradient, which causes R-T instability. The surface wave that is generated by the R-T instability is mainly responsible for the liquid column breakup. When the thin liquid film reaches a column breakup point, the airflow penetrating the trough of the surface wave causes the jet column to break. The tangential velocity gradient is generated when the gas film bypasses the liquid jet surface, which causes K-H instability. The K-H surface waves cause ligaments and droplets to strip from the surface of the liquid jet. The local momentum ratio has an important influence on the breakup process of the liquid jet in gas film. When the local momentum ratio is low, the breakup of liquid jet is dominated by the K-H instability. As the local momentum ratio increases, the breakup of liquid jet is gradually dominated by R-T instability. The local momentum ratio plays an important role in the distribution range of the liquid jet in gas film. When the local momentum ratio is low, the ligaments and droplets caused by the liquid jet are mainly distributed within the range of gas film. As the local momentum ratio increases, part of the ligaments and droplets escape from the range of the gas film. The liquid jet penetrates the gas film when the local momentum ratio is greater than 0.74. The breakup length and the penetration depth are both affected by the local momentum ratio. The breakup length increases with the local momentum ratio increasing. The penetration depth also increases with the local momentum ratio, and the penetration depth increases significantly when the liquid jet penetrates the gas film.

Keywords:

作者及机构信息

国防科技大学空天科学学院, 高超声速冲压发动机技术重点实验室, 长沙　410073

通信作者: 成鹏, imchengpeng@yeah.net ; 李清廉, peakdreamer@163.com ;

基金项目: 国家自然科学基金(批准号: 11472303, 11402298)、国家自然科学基金青年科学基金(批准号: 11902351)和国家重点基础研究发展计划(批准号: 613239)资助的课题

Authors and contacts

Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

Corresponding author: Cheng Peng, imchengpeng@yeah.net ; Li Qing-Lian, peakdreamer@163.com ;

Funds: Project supported by the National Natural Science Foundation of China (Grant Nos. 11472303, 11402298), the Young Scientists Fund of the National Natural Science Foundation of China (Grant No. 11902351), and the National Basic Research Program of China (Grant No. 613239)

文章全文 : translate this paragraph

参考文献

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[34]	Xiao F, Wang Z G, Sun M B, Liu N, Yang X 2017 Proc. Combust. Inst. 36 2417 Google Scholar
[35]	梁刚涛, 郭亚丽, 沈胜强 2013 物理学报 62 024705 Google Scholar Liang G T, Guo Y L, Shen S Q 2013 Acta Phys. Sin. 62 024705 Google Scholar
[36]	Li X Y, Soteriou M C, Arienti M, Sussman M M 2011 Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition Orlando, Florida, January 4–7, 2011 p99
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[38]	Chu W, Li X Q, Tong Y H, Reng Y J 2020 Acta Astronaut. 175 204 Google Scholar
[39]	Liu N, Wang Z G, Sun M B, Deiterding R, Wang H B 2019 Aerosp. Sci. Technol. 91 456 Google Scholar
[40]	Li P B, Wang Z G, Sun M B, Wang H B 2017 Acta Astronaut. 134 333 Google Scholar
[41]	李佩波, 王振国, 孙明波, 汪洪波 2016 宇航学报 37 209 Google Scholar Li P B, Wang Z G, Sun M B, Wang H B 2016 J. Astronaut. 37 209 Google Scholar
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施引文献

图 1 (a) 针栓喷注器; (b)针栓喷注单元

Fig. 1. (a) Pintle injector; (b) pintle injector element.

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图 2 实验系统示意图

Fig. 2. Schematic diagram of the experimental setup.

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图 3 计算域

Fig. 3. Computational domain.

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图 4 自适应加密后的网格

Fig. 4. Mesh after adaptive.

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图 5 (a) 仿真结果; (b) 实验结果; (c) 破碎图像对比; (d)不稳定波长对比

Fig. 5. (a) Simulation; (b) experiment; (c)comparison of breakup process; (d) comparison of unstable wavelength.

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图 6 (a) 压力云图; (b) 速度云图

Fig. 6. (a) Contour of pressure; (b) contour of velocity.

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图 7 R-T不稳定波的发展过程　(a) t₀; (b) t₀ + 0.12 ms; (c) t₀ + 0.24 ms; (d) t₀ + 0.36 ms

Fig. 7. The development of unsteady wave: (a) t₀; (b) t₀ + 0.12 ms; (c) t₀ + 0.24 ms; (d) t₀ + 0.36 ms.

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图 8 (a)射流近壁面的流线图; (b) 射流近壁面的速度矢量图

Fig. 8. (a) Streamline diagram of jet near the wall; (b) velocity vector diagram of jet near the wall.

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图 9 气流穿透射流表面波波谷　(a)仿真; (b)实验

Fig. 9. The gas penetrate the trough of surface wave: (a) Simulation; (b) experiment.

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图 10 射流迎风面的液滴剥离

Fig. 10. Droplet striped from the windward surface of the jet.

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图 11 射流横截面变形过程

Fig. 11. Deformation process of jet cross section

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图 12 射流横截面(Y = 1.0D)的速度矢量图

Fig. 12. Velocity vector diagram of jet cross section (Y = 1.0D)

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图 13 流场流线图

Fig. 13. Streamline of flow field.

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图 14 液体射流破碎过程示意图

Fig. 14. Schematic diagram of liquid jet breaking process.

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图 15 不同LMR下的射流破碎过程　(a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74; (d) LMR = 0.97; (e) LMR = 1.23; (f) LMR = 1.52

Fig. 15. Breakup process of liquid jet under different LMR: (a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74; (d) LMR = 0.97; (e) LMR = 1.23; (f) LMR = 1.52.

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图 16 不稳定波波长随LMR变化

Fig. 16. Unsteady wavelength vs. LMR.

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图 17 射流近壁面的压力云图　(a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74

Fig. 17. Pressure contour of jet near the wall: (a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74.

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图 18 气膜迹线图　(a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74; (d) LMR = 0.97; (e) LMR = 1.23; (f) LMR = 1.52

Fig. 18. Streamline of gas film: (a) LMR = 0.38; (b) LMR = 0.55; (c) LMR = 0.74; (d) LMR = 0.97; (e) LMR = 1.23; (f) LMR = 1.52

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图 19 (a) 破碎长度随时间变化(LMR = 1.23); (b) 破碎长度随LMR变化

Fig. 19. (a) Breakup length with flow time (LMR = 1.23); (b) breakup length with different LMR

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图 20 (a) 穿透深度随LMR变化; (b) 展向扩张角随LMR变化

Fig. 20. (a) Penetration depth vs. LMR; (b) spray spread angle vs. LMR.

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表 1 气膜工况参数

Table 1. Parameters of gas film.

总压/
MPa 静压/
MPa 质量流量/
(kg·s^–1) 速度/
(m·s^–1) 温
度/K 膜厚/
mm

0.2 0.1 0.02 315.4 300 3

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表 2 液体射流工况参数

Table 2. Parameters of liquid jets.

密度/
(kg·m³) 速度/
(m·s^–1) 孔径/
mm 局部动量
比LMR

998.2 12.5, 15.0, 17.5,
20.0, 22.5, 25.0 1.3 0.38, 0.55, 0.74,
0.97, 1.23, 1.52

下载: 导出CSV

[1]	岳春国, 李进贤, 侯晓, 冯喜平, 杨姝君 2009 中国科学: 技术科学 39 464 Google Scholar Yue C G, Li J X, Hou X, Feng X P, Yang S J 2009 Sci. Sin.: Tech. 39 464 Google Scholar
[2]	张雪松 2017 卫星与网络 6 40 Google Scholar Zhang X S 2017 Satell. Network 6 40 Google Scholar
[3]	Heister S D 2011 Handbook of Atomization and Sprays: Theory and Applications (New York: Springer Science Business Media) pp647−655
[4]	Son M, Radhakrishnan K, Yoon Y, Koo J 2017 Acta Astronaut. 135 139 Google Scholar
[5]	Dressler G A, Bauer J M 2000 36th AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit Huntsville, Alabama, July 16–19, 2000 p2000
[6]	Ninish S, Vaidyanathan A, Nandakumar K 2018 Exp. Therm. Fluid Sci. 97 324 Google Scholar
[7]	方昕昕, 沈赤兵, 张新桥 2016 航空动力学报 31 3004 Google Scholar Fang X X, Shen C B, Zhang X Q 2016 J. Aerosp. Power 31 3004 Google Scholar
[8]	方昕昕, 沈赤兵 2017 航空动力学报 32 2291 Google Scholar Fang X X, Shen C B 2017 J. Aerosp. Power 32 2291 Google Scholar
[9]	Son M, Yu K, Radhakrishnan K, Shin B, Koo J 2016 J. Therm. Sci. 25 90 Google Scholar
[10]	刘昌波 2014 博士学位论文(西安: 西安航天动力研究所) Liu C B 2014 Ph. D. Dissertation (Xi’an: Xi’an Aerospace Propulsion Institute) (in Chinese)
[11]	Yates C L 1971 Proceedings of the 7 th Propulsion Joint Specialist Conference Salt Lake City, June 14–18, 1971 p724
[12]	Kush E A, Schetz J A 1973 AIAA J. 11 1223 Google Scholar
[13]	Schetz J A, Kush E A, Joshi P B 1980 AIAA J. 18 774 Google Scholar
[14]	陈亮, 乐嘉陵, 宋文艳, 杨顺华, 曹娜 2011 实验流体力学 25 29 Google Scholar Cheng L, Le J L, Song W Y, Yang S H, Cao N 2011 J. Exp. Fluid Mech. 25 29 Google Scholar
[15]	曹娜, 徐青, 曹亮, 雷岚, 韩长材, 马继明, 杜继业 2013 现代应用物理 4 323 Google Scholar Cao N, Xu Q, Cao L, Lei L, Han C C, Ma J M, Du J Y 2013 Mod. Appl. Phys. 4 323 Google Scholar
[16]	Yang S H, Le J L 2006 Proceedings of the 12th Chinese National Symposium on Shock’Waves Luoyang, July 24, 2006 p70
[17]	徐胜利, Archer R D, Milton B E, 岳朋涛 2000 中国科学:技术科学 30 179 Google Scholar Xu S L, Archer R D, Milton B E, Yue P T 2000 Sci. Sin.: Tech. 30 179 Google Scholar
[18]	刘楠 2019 博士学位论文 (长沙: 国防科技大学) Liu N 2019 Ph. D. Dissertation (Changsha: National University of Defense Technology) (in Chinese)
[19]	Xiao F, Wang Z G, Sun M B, Liang J H, Liu N 2016 Int. J. Multiph. Flow 87 229 Google Scholar
[20]	Xiao F, Sun M B 2019 Atom. Sprays 28 975 Google Scholar
[21]	李春, 沈赤兵, 李清廉, 朱元昊 2019 国防科技大学学报 41 73 Google Scholar Li C, Shen C B, Li Q L, Zhu Y H 2019 J. Natl. Univ. Def. Technol. 41 73 Google Scholar
[22]	Cheng P, Li Q L, Chen H Y 2019 Acta Astronaut. 154 61 Google Scholar
[23]	Chen H Y, Li Q L, Cheng P 2019 Acta Astronaut. 162 424 Google Scholar
[24]	吴里银, 王振国, 李清廉, 李春 2016 物理学报 65 094701 Google Scholar Wu L Y, Wang Z G, Li Q L, Li C 2016 Acta Phys. Sin. 65 094701 Google Scholar
[25]	Wu L Y, Wang Z G, Li Q L, Li C 2016 J. Vis. 19 337 Google Scholar
[26]	Lin K C, Kirkendall K A, Kennedy P J, Jackson T A 1999 Proceedings of the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit Los Angeles, California, June 20–24, 1999 p2374
[27]	Sallam K A, Aalburg C, Faeth G M, Lin K C, Carter C D, Jackson T A 2004 Proceedings of the 42nd AIAA Aerospace Sciences Meeting and Exhibit Reno, Nevada, January 5–8, 2004 p970
[28]	Sallam K A, Aalburg C, Faeth G M 2004 AIAA J. 42 2529 Google Scholar
[29]	Richards J R, Lenhoff A M, Beris A N 1994 Phys. Fluids 6 2640 Google Scholar
[30]	Srinivasan V, Salazar A J, Saito K 2011 Appl. Math. Model. 35 3710 Google Scholar
[31]	Herrmann M 2011 Proc. Combust. Inst. 33 2079 Google Scholar
[32]	Desjardins O, Pitsch H 2009 J. Comput. Phys. 228 1658 Google Scholar
[33]	高亚军, 姜汉桥, 李俊键, 赵玉云, 胡锦川, 常元昊 2017 物理学报 66 024702 Google Scholar Gao Y J, Jiang H Q, Li J J, Zhao Y Y, Hu J C, Chang Y H 2017 Acta Phys. Sin. 66 024702 Google Scholar
[34]	Xiao F, Wang Z G, Sun M B, Liu N, Yang X 2017 Proc. Combust. Inst. 36 2417 Google Scholar
[35]	梁刚涛, 郭亚丽, 沈胜强 2013 物理学报 62 024705 Google Scholar Liang G T, Guo Y L, Shen S Q 2013 Acta Phys. Sin. 62 024705 Google Scholar
[36]	Li X Y, Soteriou M C, Arienti M, Sussman M M 2011 Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition Orlando, Florida, January 4–7, 2011 p99
[37]	Fontes D H, Vilela V, Souza Meira L D, Souza F J 2019 Int. J. Multiph. Flow 114 98 Google Scholar
[38]	Chu W, Li X Q, Tong Y H, Reng Y J 2020 Acta Astronaut. 175 204 Google Scholar
[39]	Liu N, Wang Z G, Sun M B, Deiterding R, Wang H B 2019 Aerosp. Sci. Technol. 91 456 Google Scholar
[40]	Li P B, Wang Z G, Sun M B, Wang H B 2017 Acta Astronaut. 134 333 Google Scholar
[41]	李佩波, 王振国, 孙明波, 汪洪波 2016 宇航学报 37 209 Google Scholar Li P B, Wang Z G, Sun M B, Wang H B 2016 J. Astronaut. 37 209 Google Scholar
[42]	成鹏 2018 博士学位论文 (长沙: 国防科技大学) Cheng P 2018 Ph. D. Dissertation (Changsha: National University of Defense Technology) (in Chinese)
[43]	Wu P K, Kirkendall K A, Fuller R P, Nejad A S 1997 J. Propul. Power 13 64 Google Scholar

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