液滴发生器工作过程的动力学特性

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1343-1351.

液滴发生器工作过程的动力学特性

徐云飞,陈鹏飞,孙策,洪流,杨岸龙,汪广旭

西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100,西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100

发布日期:2021-08-15
作者简介:徐云飞，男，硕士，工程师，研究领域为发动机喷雾技术与系统动力学仿真。
基金资助:
国家自然科学基金(11502186；51506157)。

Dynamic Characteristics of Droplet Generator Operation Process

Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China,Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China,Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China,Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China,Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China and Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute， Xi’an 710100，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究喷孔位置对液滴发生器均匀液滴生成稳定性的影响，发展了液滴发生器工作过程的动力学特性计算模型，给出了基于声学理论的集液腔压力响应空间分布函数。考虑到部分小孔径、大长径比直流喷嘴的工作特点，在传统集中参数模型的基础上，建立了分布参数模型。随后，分析了Rayleigh模式下射流表面波色散关系的影响因素。结果表明，在特定的激励频率区间内，喷注面会产生近似圆环形状的波节结构，并随着频率的改变沿径向移动，因此液滴发生器的喷孔位置设计应当考虑喷注面的压力分布特性。与集中参数模型类似，喷嘴分布参数模型计算出的脉动流量也是随着激励频率的提高而减小，但滞后相位角保持约90°不变。分布参数与集中参数模型的适用界限要根据射流表面波的色散关系以及喷嘴长径比共同确定。

关键词: 液滴发生器；压力分布特性；分布参数模型；动态特性

Abstract: In order to study the effects of injection position on mono-dispersed droplet generation stability，a dynamic model for droplet generator operation process was developed. Pressure response distribution function in the fluid cavity was proposed according to acoustic theory. Considering the characteristics of jet injector with small diameter and large length to diameter ratio，the distribution parameter model was presented based on the conventional lumped parameter model. Then，the factors influencing on the dispersion relation of jet surface wave in Rayleigh regime were analyzed. Results show that a near-circular nodal line is generated on the injection plate in a certain range of excitation frequency，and it moves along the radial direction while oscillation frequency changes. So characteristics of pressure distribution on the injection plate should be taken into consideration during injector position design of droplet generator. Flow oscillation calculated by the distribution parameter model decreases with the increase of excitation frequency，which is similar to the lumped parameter model results. But the lagging phase angle keeps about 90°. The applicable boundaries between two injector models are jointly determinated by the length to diameter ratio of jet injector as well as the dispersion relation of surface wave.

Key words: Droplet generator；Pressure distribution characteristics；Distribution parameter model；Dynamic characteristics

徐云飞,陈鹏飞,孙策,洪流,杨岸龙,汪广旭. 液滴发生器工作过程的动力学特性[J]. 推进技术, 2017, 38(6): 1343-1351.

XU Yun-fei,CHEN Peng-fei,SUN Ce,HONG Liu,YANG An-long,WANG Guang-xu. Dynamic Characteristics of Droplet Generator Operation Process[J]. Journal of Propulsion Technology, 2017, 38(6): 1343-1351.

参考文献

[1] 侯曾祺, 胡金刚. 航天器热控制技术—原理及其应用[M]. 北京:中国科学技术出版社, 2007.
[2] Muntz E P, Orme M, Farnham T, et al. Liquid Droplet Generation[R]. NASA-CR-182246, 1989.
[3] Chaudhard K C, Redekopp L G. The Nonlinear Capillary Instability of a Liquid Jet, Part 1: Theory [J]. Journal of Fluid Mechanics, 1980, 96(2): 257-274.
[4] Dixon M. Droplet Velocity Dispersion Device[C]. Reno: 23rd Aerospace Sciences Meeting, 1985.
[5] Joslyn T B, Ketsdever A D. Liquid Droplet Thrusters to Provide Constant Momentum Exchange between Formation Flying Spacecraft[R]. AFRL-RZ-ED-TP-2010-099.
[6] Joslyn T B, Ketsdever A D. Constant Momentum Exchange between Microspacecraft Using Liquid Droplet Thrusters[R]. AFRL- RZ-ED-TP-2010-288.
[7] Totani T, Itami M, Nagata H, et al. Performance of Droplet Generator and Droplet Collector in Liquid Droplet Radiator under Microgravity[J]. Microgravity Science and Technology, 2002, 13(2): 42-45.
[8] Totani T, Kodama T, Nagata H, et al. Thermal Design of Liquid Droplet Radiator for Space Solar-Power System[J]. Journal of Spacecraft and Rockets, 2005, 42(3): 493-499.
[9] 刘文巍, 黄云, 李水清. 适用于稳态蒸发和燃烧的定频率单液滴发生器研究[J]. 工程热物理学报, 2013, 34(8): 1570-1573.
[10] 魏胜, 漆小波, 张占文, 等. 液滴发生器系统中流速及振荡频率的确定[J]. 强激光与粒子束, 2011, 23(7): 1925-1928.
[11] 盛明伟, 陈维山, 刘军考, 等. 航天控制力矩陀螺的润滑系统研究[J]. 航空动力学报, 2011, 26(1): 228-233.
[12] 郁朋. 高粘度压电微喷装置实验研究[D]. 哈尔滨:哈尔滨工业大学, 2011.
[13] 冷月. 面向航天器主动润滑的压电微喷装置研究[D]. 哈尔滨:哈尔滨工业大学, 2012.
[14] 李锴. 基于压电微喷的嵌入式轴承润滑装置的研究[D]. 哈尔滨:哈尔滨工业大学, 2014.
[15] 叶磊. 基于谐振驱动的压电微喷装置的研究[D]. 哈尔滨:哈尔滨工业大学, 2015.
[16] 徐云飞, 陈鹏飞, 范立华, 等. 液滴发生器均匀液滴生成过程的动态特性[J]. 宇航学报, 2015, 36(9): 1049-1055.
[17] 刘上, 刘红军, 孙宏明, 等. 液体火箭发动机中频耦合振荡初步研究[J]. 推进技术, 2013, 34(1): 101-108. (LIU Shang, LIU Hong-jun, SUN Hong-ming. Preliminary Study of Medium Frequency Coupled Oscillation in Liquid Rocket Engine[J]. Journal of Propulsion Technology, 2013, 34(1): 101-108.)
[18] 蔡亦刚. 流体传输管道动力学[M]. 杭州:浙江大学出版社, 1990.
[19] Lefebvre A H. Atomization and Sprays[M]. USA: Hemisphere Publishing Corporation, 1989.
[20] 刘上, 刘红军, 陈宏玉. 液体离心喷嘴动力学特性理论分析[J]. 火箭推进, 2012, 38(3): 1-11.　　　　　　　　　　　　　*　收稿日期:2016-03-06；修订日期:2016-05-16。基金项目:国家自然科学基金(11502186；51506157)。作者简介:徐云飞,男,硕士,工程师,研究领域为发动机喷雾技术与系统动力学仿真。E-mail: xiaorongxy@163.com(编辑:张荣莉)