离心式喷嘴液膜破碎过程实验

推进技术 ›› 2011, Vol. 32 ›› Issue (4): 539-543.

离心式喷嘴液膜破碎过程实验

刘娟,李清廉,刘卫东,王振国

国防科技大学航天与材料工程学院,湖南长沙 410073;国防科技大学航天与材料工程学院,湖南长沙 410073;国防科技大学航天与材料工程学院,湖南长沙 410073;国防科技大学航天与材料工程学院,湖南长沙 410073

发布日期:2021-08-15
作者简介:刘娟(1983—),女,博士生,研究领域为液体燃料喷雾与燃烧。E-mail:janny_liu123@163.com
基金资助:
国家自然科学基金项目(10802095)。

Experiment on liquid sheet breakup process of pressure swirl injector

Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究离心式喷嘴出口液膜破碎以及雾化锥角变化规律,对直径2.5~6 mm之间6个不同直径、不同几何特性参数的离心式喷嘴运用高速阴影设备进行实验,喷注压降从0.1~3 MPa,每次实验间隔0.2 MPa。通过实验,得到液膜破碎长度、液膜锥角随喷注压降、喷孔直径以及几何特性参数的变化规律。随着喷注压降的增加,液膜破碎长度减小,液膜锥角增大,该种类型喷嘴破碎长度在40 mm左右,液膜锥角不大于60°；随着几何特性参数A值增加,同一喷注压降下的液膜破碎长度增大,液膜锥角增加；将液膜锥角实验结果与Abromvich,Lefebvre等理论公式进行了比较,在常用的喷嘴特性参数范围内,液膜锥角的变化趋势与理论公式相吻合,但实验值远小于公式计算值。

关键词: 离心式喷嘴;高速阴影;破碎长度;液膜锥角

Abstract: To investigate the liquid sheet breakup length and cone angle of pressure-swirl injectors, 6 ones with different diameters and geometric parameters A are presented. High-speed shadowgraph was used to capture the breakup process. Pressure drop is among 0.1~3 MPa, and injector diameters are among 2.5~6 mm. With pressure drop increasing, breakup length minishes to about 40 mm and cone angle is enlarged to below 60°. with central post diameter increasing, breakup length shortens and cone angle increases. With geometric parameter A increasing, both breakup length and cone angle increase. The experimental results of cone angle are far less than formula when compared with Abromvich and Lefebvre theory, but it has the same trend with theory formula as A ranges from 3~5. 

Key words: Swirl injector；High-speed shadowgraph；Breakup length；Cone angle

刘娟,李清廉,刘卫东,王振国. 离心式喷嘴液膜破碎过程实验[J]. 推进技术, 2011, 32(4): 539-543.

参考文献

[2] 庄逢辰.液体火箭发动机喷雾燃烧的理论、模型及应用[M].长沙:国防科学技术大学出版社,1995:32-36.
[3] Kalitan D M, Salgues D.Experimental liquid rocket swirl coaxial injector study using non-intrusive optical techniques[R].AIAA 2005-4299.
[4] Datta A, So S K.Numerical prediction of air core diameter, coeffcient of discharge and spray cone angle of a swirl spray pressure nozzle[J].International Journal of Heat and Fluid Flow, 2000,(21):412-419.
[5] Balasubramanyam M S, Chen C P.Numerical design studies on internal flow characteristics of LOX/CH₄ swirl injector[R].AIAA 2009-5040.
[6] 田章福,吴继平,陶玉静,等.气液同轴式喷嘴雾化特性的试验[J].国防科技大学学报,2006,28(4):10-13.
[7] Rizk N K, Lefebvre A H.Prediction of velocity coefficient and spray cone angle for simplex swirl atomizers[C].London:Proceedings of the 3rd International Conference on Liquid Atomization and Spray Systems, 1985.
[8] Youngbin Yoon, Jeung In-Seuk.Effects of ambient gas pressure on the breakup of sprays in like doublet and swirl coaxial injectors[C].Istanbul:International Symposium on Energy Conversion Fundamentals,2004.
[9] Liu Juan, Li Qing-lian, Wang Zhen-guo.Observational investigation on the breakup of round liquid jet[C].CHN:13th Annual Conference International on Liquid Atomization and Spray System-Asia, 2009:226-231.
[10] Lefebvre H.Atomization and sprays [M].Boca Raton:CRC Press, 1989:205-217.
[11] 朱宁昌.液体火箭发动机设计(上)[M].北京:宇航出版社,1994:371-375.
[12] Rizk N K, Lefebvre A H.Internal flow characteristics of simplex swirl atomizers[R].AIAA 84-0124.
[13] 周猛.气液同轴式喷注器雾化特性和激光散射测粒技术的研究[D].长沙:国防科技大学, 1991.
[14] 王之任.离心式喷嘴工况理论分析[J].推进技术, 6,7(5):1-8.(WANG Zhi-ren.Theoretical analysis for operating condition of centrifugal injector[J].Journal of Propulsion and Power, 6,7(5):1-8.)
[15] 王国辉,蔡体敏,何国强,等.一种旋流式喷嘴的试验和数值研究[J].推进技术, 2003,24(1):28-32.(WANG Guo-hui, CAI Ti-min, HE Guo-qiang, et al.Experimental and numerical investigation of a swirl atomizer[J].Journal of Propulsion and Power, 2003,24(1):28-32.)