固体火箭发动机水下超音速射流数值研究

doi:10.3969/j.issn.1000-1093.2019.06.006

摘要/Abstract

摘要： 固体火箭发动机水下点火射流是高温高压条件下复杂的多相流过程，为研究其流场特性与推力特性，选取扩张比分别为3.4和14.0的拉瓦尔喷管模型进行数值模拟。采用计算流体力学方法分析高速燃气超音速射流过程的流场与推力演化过程，揭示高温高压气体与水环境之间的相互作用规律。结果表明：固体火箭发动机水下射流流场结构与推力特性呈周期性变化，根据流场特征可分为颈缩、胀鼓、回击3个阶段；水环境与射流气体之间的相互作用是导致背压振荡的直接原因，同时导致激波运动、动量推力与压差推力的振荡。对比两种扩张比喷管的射流可知，扩张比为14.0的喷管射流形貌与流场结构的周期性变化更明显，扩张比为3.4的喷管背压振荡频率高、周期性特征弱、推力更稳定。

关键词: 固体火箭发动机, 多相流, 超音速射流, 计算流体力学

Abstract: The ignition process of gas jets under water is essentially complex, including multiphase flow and complicated flow structures. The Laval nozzle models with expansion ratios of 3.4 and 14.0 are numerically simulated. The CFD method is applied to study the flow structures and corresponding thrust characteristics of rocket engine and analyze the interaction between the high-speed gas jets and water environment. The results show that the flow structures and thrust characteristics of engine change periodically, and the process can be divided into three stages: necking, bulge and return stroke. The interaction between the water environment and the gas jet is the immediate cause leading to the back pressure oscillation, which also induces the fluctuation of shock waves, momentum thrust and pressure differential thrust. For the nozzles with different expansion ratios, the periodic variation of jets pattern and flow structures for the nozzle with expansion ratio of 14 can be more obviously observed, and the oscillation frequency of back pressure for the nozzle with expansion ratio of 3.4 is higher, accompanied with weak periodic characteristics and more stable thrust characteristics. Key

Key words: solidrocketengine, multiphaseflow, supersonicjet, computationalfluiddynamics

中图分类号:

V435⁺.11

王利利，刘影，李达钦，吴钦，王国玉. 固体火箭发动机水下超音速射流数值研究[J]. 兵工学报, 2019, 40(6): 1161-1170.

WANG Lili，LIU Ying，LI Daqin，WU Qin，WANG Guoyu. Numerical Study of Underwater Supersonic Gas Jets for Solid Rocket Engine[J]. Acta Armamentarii, 2019, 40(6): 1161-1170.

参考文献

［1］张婵, 马卫国. 俄罗斯布拉瓦潜射弹道导弹试验失败原因分析［J］. 飞航导弹, 2014(3):27-30.
ZHANG C, MA W G. Analysis of failure causes of Russian Blava submarine launch ballistic missile test［J］. Aerodynamic Missiles Journal, 2014(3):27-30. (in Chinese)
［2］巫银花, 何常青, 宋勇. 基于熵权法的潜射反舰导弹作战效能灰色关联评估方法［J］. 兵工自动化, 2015，34(2):40-42.
WU Y H, HE C Q, SONG Y. Evaluation method of submarine anti-ship missile effectiveness based on the theory of information entropy and grey system［J］. Ordnance Industry Automation, 2015, 34(2):40-42. (in Chinese)
［3］张有为. 固体火箭发动机水下工作特性的研究［D］. 合肥：中国科学技术大学, 2007.
ZHANG Y W. Research on working characteristics of solid rocket engine in water［D］. Hefei：University of Science and Technology of China, 2007. (in Chinese)
［4］ DURSUN G, AKOSMAN C. Gas-liquid interfacial area and mass transfer coefficient in a co-current down flow contacting column［J］. Journal of Chemical Technology & Biotechnology, 2006, 81(12): 1859-1865.
［5］张小圆，李世鹏，王宁飞. 喷管激波对水下固体火箭发动机不稳定性的影响［C］∥第九届全国流体力学学术会议. 南京: 中国力学学会, 2016.
ZHANG X Y, LI S P, WANG N F. Influence of nozzle shock on the instability of underwater solid rocket engine ［C］∥The 9th National Conference on Fluid Mechanics. Nanjing: The Chinese Society of Theoretical and Applied Mechanics, 2016. (in Chinese)
［6］ ABATE G, SHYY W. Dynamic structure of confined shocks undergoing sudden expansion［J］. Progress in Aerospace Sciences, 2002, 38(1):23-42.
［7］ IRIE T, YASUNOBU T, KASHIMURA H, et al. Characteristics of the Mach disk in the underexpanded jet in which the back pressure continuously changes with time［J］. Journal of Thermal Science, 2003, 12(2):132-137.
［8］王柏懿, 戴振卿, 戚隆溪, 等. 水下超声速气体射流回击现象的实验研究［J］. 力学学报, 2007, 39(2):267-272.
WANG B Y, DAI Z Q, QI L X, et al. Experimental study on back-attack phenomenon in underwater supersonic gas jets［J］. Chinese Journal of Theoretical and Applied Mechanics, 2007, 39(2): 267-272. (in Chinese)
［9］ SHI H H, WANG B Y, DAI Z Q. Research on the mechanics of underwater supersonic gas jets［J］. Science China (Physics, Mechanics & Astronomy), 2010, 53(3):527-535.

［10］施红辉, 王柏懿, 戚隆溪, 等. 水下超音速气体射流［C］∥第七届全国水动力学学术会议暨第十九届全国水动力学研讨会. 哈尔滨: 中国力学学会, 2005.
SHI H H, WANG B Y, QI L X, et al. A submerged supersonic gas jet. ［C］∥The 7th National Congress on Hydrodynamics and the 19th National Hydrodynamics Symposium. Harbin: The Chinese Society of Theoretical and Applied Mechanics, 2005. (in Chinese)
［11］施红辉, 王柏懿, 戴振卿. 水下超声速气体射流胀鼓和回击的关联性研究［J］. 力学学报, 2010, 42(6):1206-1210.
SHI H H, WANG B Y, DAI Z Q, et al. Experiments on the relationship between bulging and back-attack of submerged supersonic gas jets［J］. Chinese Journal of Theoretical and Applied Mechanics, 2010, 42(6):1206-1210. (in Chinese)
［12］ FRONZEO M, KINZEL M P. An investigation of compressible gas jets submerged into water［C］∥The 46th AIAA Fluid Dynamics Conference. Washington, DC, US: American Institute of Aeronautics and Astronautics Inc.， 2016.
［13］ LI W C, MENG Z M, SUN Z N, et al. Investigations on the penetration length of steam-air mixture jets injected horizontally and vertically in quiescent water［J］. International Journal of Heat & Mass Transfer, 2018, 122(7): 89-98.
［14］李婷婷, 胡俊, 曹雪洁,等. 环形喷管水下气体射流夹断过程［J］. 化工学报, 2017, 68(12): 4565-4575.
LI T T, HU J, CAO X J, et al. Pinch-off process of underwater annular-nozzled gas jet［J］. Chemical Industry and Engineering Journal, 2017, 68(12): 4565-4575. (in Chinese)
［15］ WILSON K J , GUTMARK E , SCHADOW K C, et al. Supersonic submerged heated jets［C］∥28th Joint Propulsion Conference and Exhibit. Nashville, TN, US:AIAA, 1992.
［16］王宝寿, 许晟, 易淑群, 等. 水下推力矢量特性试验研究［J］. 船舶力学, 2000,4(5):9-15.
WANG B S, XU S, YI S Q, et al. Test studies of underwater thrust vector control performance［J］. Journal of Ship Mecha-nics, 2000,4(5):9-15. (in Chinese)
［17］ JOHANSEN S T, WU J Y, WEI S. Filter-based unsteady RANS computations［J］. International Journal of Heat & Fluid Flow, 2004, 25(1):10-21.
［18］陈启林. 水下燃气射流数值仿真与试验研究［D］. 北京：北京理工大学, 2016.
CHEN Q L. The numerical simulation and experimental research on underwater gas jet［D］. Beijing:Beijing Institute of Technology, 2016. (in Chinese)

第40卷第6期
2019 年6月兵工学报ACTA
ARMAMENTARIIVol.40No.6Jun.2019

[1]	汪泰霖, 王野, 张富毅, 陈慧岩, 王国玉. 水陆两栖车矢量喷口装置设计与仿真[J]. 兵工学报, 2022, 43(4): 826-850.
[2]	顾兴鹏，李军伟，乔文生，武胜，韩磊，汪琪，王宁飞. 固相颗粒在C1xb固体火箭发动机中的运动规律[J]. 兵工学报, 2022, 43(3): 489-502.
[3]	朱毅飞, 林德福, 莫雳, 叶建川. 四旋翼无人机旋翼对机身非定常气动干扰特性[J]. 兵工学报, 2022, 43(2): 410-422.
[4]	官典, 李世鹏, 刘筑, 王宁飞. 横向过载对固体火箭发动机推进剂点火建压过程的影响[J]. 兵工学报, 2021, 42(9): 1877-1887.
[5]	周柏航，陶如意，王浩，阮文俊. 带侵蚀燃烧效应的阶梯多根装药火箭发动机三维内流场特性[J]. 兵工学报, 2021, 42(8): 1604-1612.
[6]	高峰，张泽. 含装药缺陷的固体火箭发动机性能评估综述[J]. 兵工学报, 2021, 42(8): 1789-1802.
[7]	马宝印，李军伟，张海龙，赵桂琦，张智慧，席运志，王宁飞. 阻尼环对固体火箭发动机热声振荡的影响[J]. 兵工学报, 2021, 42(5): 930-943.
[8]	席运志，王宁飞，李军伟，张智慧. 基于旋转阀的固体火箭发动机燃烧室压强振荡特性[J]. 兵工学报, 2021, 42(1): 33-44.
[9]	刘双, 何广华, 王威, 高云. 附体对分层流中潜艇水动力特性的影响[J]. 兵工学报, 2021, 42(1): 108-117.
[10]	徐路程，郝雪颖，肖凯涛，宋伟伟，陈春生. 爆炸型烟幕弹遮蔽效能仿真研究[J]. 兵工学报, 2020, 41(7): 1299-1306.
[11]	钟阳，王良明，吴映锋. 基于计算流体力学与刚体动力学耦合的高速旋转弹丸弹道计算方法[J]. 兵工学报, 2020, 41(6): 1085-1095.
[12]	权辉，谢建，李良，张力. 火箭发射场坪排焰道口射流研究[J]. 兵工学报, 2020, 41(6): 1111-1122.
[13]	伍鹏，李高春，韩永恒，赵汝岩，谭洁，刘著卿. 固体火箭发动机矩形粘接试件多角度拉伸过程变形测量与破坏模式[J]. 兵工学报, 2020, 41(11): 2234-2242.
[14]	叶青，余永刚. 星型装药固体火箭发动机烤燃特性[J]. 兵工学报, 2020, 41(10): 1970-1978.
[15]	李阳天，李海滨，韦广梅，翁洁鑫. 基于改进型多项式混沌展开的固体火箭发动机药柱低温点火不确定性量化分析[J]. 兵工学报, 2020, 41(1): 40-48.