敞口式离心喷嘴液膜动态填充及打开过程研究

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1352-1358.

敞口式离心喷嘴液膜动态填充及打开过程研究

陈晨^1,2,杨样²,高宏力¹,杨顺华²,晏至辉²

西南交通大学机械工程学院，四川成都 610031; 中国空气动力研究与发展中心高超中心，四川绵阳 621000,中国空气动力研究与发展中心高超中心，四川绵阳 621000,西南交通大学机械工程学院，四川成都 610031,中国空气动力研究与发展中心高超中心，四川绵阳 621000,中国空气动力研究与发展中心高超中心，四川绵阳 621000

发布日期:2021-08-15
作者简介:陈晨，男，博士生，研究领域为喷雾燃烧。 E-mail: 472914230@163.com 通讯作者:高宏力，男，博士，研究领域为喷雾燃烧。

Investigation on Dynamic Filling and Opening Process of Liquid Film in Open-End Swirl Injector

School of Mechanical Engineering，Southwest Jiaotong University，Chengdu 610031，China; Air-breathing Hypersonic Technology Research Center， China Aerodynamics Research and Development Center，Mianyang 621000，China,Air-breathing Hypersonic Technology Research Center， China Aerodynamics Research and Development Center，Mianyang 621000，China,School of Mechanical Engineering，Southwest Jiaotong University，Chengdu 610031，China,Air-breathing Hypersonic Technology Research Center， China Aerodynamics Research and Development Center，Mianyang 621000，China and Air-breathing Hypersonic Technology Research Center， China Aerodynamics Research and Development Center，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了揭示敞口式离心喷嘴液膜填充及打开过程，采用两相界面追踪方法VOF(volume of fluid)模拟了喷嘴内部及近喷口区域流动过程，计算得到的喷雾角和试验结果偏差不超过2%。计算结果表明:喷嘴内部填充过程中，自切向孔下游至喷嘴出口液膜厚度缓慢增加，在喷嘴出口处液膜厚度大幅度降低，呈非线性发展；相应地，切向孔截面空心涡经历了正方形-花瓣形-圆形的演化历程；喷口边缘处表面张力占主导，此时液膜较厚，因此液膜刚流出喷嘴时并没有立刻打开，而后变薄、失稳、脱落、破碎并部分聚合，随着时间推移，喷嘴出口液膜形态依次经历了铅笔形、洋葱形、郁金香形和完全发展形四种形态，与稳态下喷注压降改变时喷雾形态变化相一致。

关键词: 离心喷嘴；液膜厚度；空心涡；数值模拟

Abstract: In order to deeply understand the dynamic filling and opening process of the liquid film in an open-end swirl injector，a numerical simulation of the internal and external flow process of the nozzle was carried out using the VOF(Volume of fluid)interface tracking method. The relative error of spray angle between the numerical simulation and experiment were less than 2%. During the filling process，the liquid film thickness in the injector shows a nonlinear tendency in general. The liquid film thickness increases from the tangential inlet to the exit while it decreases sharply at the exit of the injector. Correspondingly the vortex shape in the tangential inlet surface derives from square to petal and then circle. As the surface tension dominates at the injector exit，the liquid film is rather thick so it does not open as soon as it leaves. On the one hand，the thick liquid film experiences thinning，instability，shedding，breaking and coalescing during the opening process. On the other hand，the liquid film at the outlet of the injector experiences distorted pencil shaped stage，onion shaped stage，tulip shaped stage and fully developed stage in turn，which are consistent with the spray pattern at steady state under different injection pressure drop.

Key words: Swirl injector；Liquid film thickness；Air core；Numerical simulation

陈晨,杨样,高宏力,杨顺华,晏至辉. 敞口式离心喷嘴液膜动态填充及打开过程研究[J]. 推进技术, 2017, 38(6): 1352-1358.

CHEN Chen^1,2,YANG Yang²,GAO Hong-li¹,YANG Shun-hua²,YAN Zhi-hui². Investigation on Dynamic Filling and Opening Process of Liquid Film in Open-End Swirl Injector[J]. Journal of Propulsion Technology, 2017, 38(6): 1352-1358.

参考文献

[1] John J C. The Internal Flow Physics of Swirl Atomizer Nozzles[D]. Manchester: University of Manchester,1996.
[2] Holtzclaw D, Sakman T, Benjamin M A. Investigation of Flow in a Simplex Fuel Nozzle[C]. Seattle: 33rd Joint Propulsion Conference and Exhibit, 1997.
[3] Jeng S, Jog M, Benjamin M. Computational and Experimental Study of Liquid Sheet Emanating from Simplex Fuel Nozzle[J]. AIAA Journal, 1998, 36(2): 201-207.
[4] 张永良. 离心喷嘴雾化特性实验研究和数值模拟[D]. 安徽:中国科学院大学, 2013.
[5] 刘娟. 旋转锥形液膜破碎过程实验与仿真研究[D]. 长沙:国防科技大学, 2012.
[6] 岳明. 锥形液膜初始破碎雾化过程和机理研究[D]. 北京:北京航空航天大学, 2003.
[7] 刘娟, 李清廉, 王振国, 等. 基于VOF方法模拟离心式喷嘴内部流动过程[J]. 航空动力学报, 2011, 26(9): 1986-1994.
[8] 张永良, 王宝瑞, 孔文俊, 等. 离心喷嘴实验与流场结构的数值模拟[J]. 工程热物理学报, 2013, 34(4): 760-764.
[9] 陈晓东, 刘宇, 杨威迦. 液体离心喷嘴中的静态表面波[J]. 推进技术, 2010, 31(1): 42-46. (CHEN Xiao-dong, LIU Yu, YANG Wei-jia, et al. Stationary Surface Wave in Liquid Swirl Injector[J]. Journal of Propulsion Technology, 2010, 31(1): 42-46. )
[10] 周立新, 张会强, 雷凡培, 等. 离心式喷嘴内流场特性的数值模拟[J]. 推进技术, 2002, 32(6): 480-484. (ZHOU Li-xin, ZHANG Hui-qiang, LEI Fan-pei, et al. Numerical Simulation of Internal Flow Fileld of Swirl Nozzle[J]. Journal of Propulsion Technology, 2002, 23(6): 480-484.)
[11] 陈晓东, 刘宇, 杨威迦. 背压对液体离心喷嘴喷雾锥的影响[J]. 推进技术, 2010, 31(5): 539-543. (CHEN Xiao-dong, LIU Yu, YANG Wei-jia, et al. Effects of Backpressure on Spray Cone of Liquid Swirl Injector[J]. Journal of Propulsion Technology, 2010, 31(5): 539-543.)
[12] Mandal A, Jog M A, Xue J, et al. Flow of Power-Law Fluids in Simplex Atomizers[J]. International Journal of Heat and Fluid Flow, 2008, 29(5): 1494-1503.
[13] Xue J, Jog M A, Jeng S M. Effect of Geometric Parameters on Simplex Atomizer Performance[J]. AIAA Journal, 2004, 42(12): 2408-2415.
[14] 刘娟, 孙明波, 李清廉, 等. 基于 VOF 方法分析离心式喷嘴结构参数对性能影响[J]. 航空动力学报, 2011, 26(12): 2826-2833.
[15] 刘娟, 李清廉, 刘卫东, 等. 离心式喷嘴液膜破碎过程实验[J]. 推进技术, 2011, 32(4): 539-543. (LIU Juan, LI Qing-lian, LIU Wei-dong, et al. Experiment on Liquid Sheet Breakup Process of Pressure Swirl Injector[J]. Journal of Propulsion Technology, 2011, 32(4): 539-543.)
[16] Suyari M, Lefebvre A H. Film Thickness Measurements in a Simplex Swirl Atomizer[J]. Journal of Propulsion and Power, 1986, 2(6): 528-533.
[17] Rizk N K, Lefebvre A H. Internal Flow Characteristics of Simplex Swirl Atomizers[J]. Journal of Propulsion and Power, 1985, 1(3): 193-199.
[18] Lefebvre A H. Atomization and Sprays[M]. New York: Hemisphere Publishing Corporation, 1989.
[19] Fung M. Experimental and Numerical Study of Spray Characteristics of Nasal Spray Device[D]. Melbourne: RMIT University, 2013.　　　　　　　　　　　　　*　收稿日期:2016-08-08；修订日期:2016-10-25。作者简介:陈晨 ,男,博士生,研究领域为喷雾燃烧。 E-mail: 472914230@163.com通讯作者:高宏力 ,男,博士,研究领域为喷雾燃烧。 E-mail: hongli_gao@home.swjtu.edu.cn(编辑:史亚红)