基于DPM的试验台导流槽喷水冷却数值研究
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摘要
采用计算流体动力学(CFD)技术,对某型运载火箭动力系统试验时导流槽的热环境进行了分析。计算采用氢氧(H-O)单步燃烧反应模型,标准k-ε湍流模型获得燃烧流场,并采用离散相模型(DPM)模拟了试验台的喷水降噪系统和导流槽底部喷水冷却系统。随后,用经过校验的模型对某型号发动机试验台导流槽的设计参数进行了对比研究。结果表明:试验台的喷水降噪系统及导流槽底部的喷水冷却系统均对导流槽底部有冷却效果,两者同时工作时对导流槽底部的冷却有叠加增强效果;导流槽深度加大时或者喷水量加大时会对底部热环境的改善同样有增强作用。
Numerical investigations of a large launch vehicle's stage test were conducted by computational fluid dynamics(CFD)technique.The uni-step hydrogen-oxygen(H-O)reaction model and standard k-turbulence model were employed to obtain the flow field,and discrete phase model(DPM)was used to simulate the water-spray system of test stand.Subsequently,the design parameters of a test stand were studied and compared.Results showed that DPM could simulate the water-spray system effectively,both of the noise suppressor system and water cooling system could improve the heat circumstance of flame-deflector,offering an enhanced effect when working together.The similar enhanced effect would be offered with the increase of the depth of deflector or the amount of water.
Numerical investigations of a large launch vehicle's stage test were conducted by computational fluid dynamics(CFD)technique.The uni-step hydrogen-oxygen(H-O)reaction model and standard k-turbulence model were employed to obtain the flow field,and discrete phase model(DPM)was used to simulate the water-spray system of test stand.Subsequently,the design parameters of a test stand were studied and compared.Results showed that DPM could simulate the water-spray system effectively,both of the noise suppressor system and water cooling system could improve the heat circumstance of flame-deflector,offering an enhanced effect when working together.The similar enhanced effect would be offered with the increase of the depth of deflector or the amount of water.
引文
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[18]甘晓华.航空燃气轮机燃油喷嘴技术[M].北京:国防工业出版社,2006.
[2]DANIEL C A,VINEET A.Computational plume modeling of conceptual ARES vehicle stage tests[R].AIAA-2007-5708,2007.
[3]STRUTZENBERG L,WEST J S.TaurusⅡstage test simulations:using large-scale CFD simulations to provide critical insight into plume induced environments during design[R].Huntsville,Alabama,USA:the 8th Modeling and Simulation Subcommittee/6th Liquid Propulsion Subcommittee/5th Spacecraft Propulsion Subcommittee Joint Meeting,2011.
[4]HARRIS M F,BRUSE T V.Modeling of heat transfer and ablation of refractory material due to rocket plume impingement[R].Pasadena,CA,USA:thermal and Fluids Analysis Workshop,2012.
[5]LIEVER M P,RADKE J,STRUTZENBERG L,et al.CFD modeling of plume induced environments for space shuttle liftoff debris transport analysis[R].Huntsville,Alabama,USA:the 2nd Workshop on Lunar and Martian Plume Effects and Mitigation,2011.
[6]BLOTZER M J,WOODS J L.Modeling potential carbon monoxide exposure due to operation of a major rocket engine altitude test facility using computational fluid dynamics[R].Toronto,Canada:American Industrial Hygiene Conference and Exposition,2009.
[7]DANIEL C,ALLGOOD J L,WOODS J S,et al.Computational analyses in support of sub-scale diffuser testing for the A-3Facility:Part 3aero-acoustic analyses and experimental validation[R].AIAA-2009-5206,2009.
[8]SEIJI T,KOTA F,RYOJI T,et al.Numerical study on acoustic radiation for designing launch-pad of advanced solid rocket[R].AIAA-2009-328,2009.
[9]刘利宏,周旭,张志成.火箭发动机射流动力学仿真研究[J].中国制造业信息化,2008(12):62-65.LIU Lihong,ZHOU Xu,ZHANG Zhicheng.Numerical analysis of rocket engine's impingement[J].China Manufacturing Informatization,2008(12):62-65.(in Chinese)
[10]周帆,姜毅,郝继光.火箭发动机尾焰流场注水降温效果初探[J].推进技术,2012,33(2):249-252.ZHOU Fan,JIANG Yi,HAO Jiguang.Exploring on cooling effect of water injection on rocket motor exhaust[J].Journal of Propulsion Technology,2012,33(2):249-252.(in Chinese)
[11]刘利宏,张志成,周旭.航天发射场导流槽综合性能评价指标体系研究[J].载人航天,2014,20(3):233-237.LIU Lihong,ZHANG Zhicheng,ZHOU Xu.Research on global performance design method of blast deflector in rocket launch site[J].Manned Spaceflight,2014,20(3):233-237.(in Chinese)
[12]李茂,陈春富,朱子勇.架空钢板对火箭发动机试车中地面热载的影响[J].导弹与航天运载技术,2013,2(2):41-45.LI Mao,CHEN Chunfu,ZHU Ziyong.Effects of aerial steel plate on the ground heat load in rocket engine test runs[J].Missiles and Space Vehicles,2013,2(2):41-45.(in Chinese)
[13]李茂,王占林.氢氧火箭发动机射流仿真试验台热防护[J].载人航天,2014,20(5):421-426.LI Mao,WANG Zhanlin.Thermal protection and plume simulation for hydrogen/oxygen rocket engine test stage[J].Manned Spaceflight,2014,20(5):421-426.(in Chinese)
[14]李茂,陈世哲,陈春富.火箭发动机地面水平试车尾流温度场仿真分析[J].火箭推进,2012,38(6):29-34.LI Mao,CHEN Shizhe,CHEN Chunfu.Simulation analysis on wake flow temperature field of rocket engine in horizontal ground test[J].Journal of Rocket Propulsion,2012,38(6):29-34.(in Chinese)
[15]李明,唐豪,张超,等.一种新型涡轮叶间燃烧室的数值模拟[J].航空动力学报,2012,27(1):55-62.LI Ming,TANG Hao,ZHANG Chao,et al.Numerical simulation of a novel turbine inter-vane burner[J].Journal of Aerospace Power,2012,27(1):55-62.(in Chinese)
[16]罗天培,孙德,李景龙,等.某大型运载火箭动力系统试验的数值模拟[J].载人航天,2016,22(2):156-159.LUO Tianpei,SUN De,LI Jinglong,et al.Numerical simulation of a large launch vehicle's stage test[J].Manned Spaceflight,2016,22(2):156-159.(in Chinese)
[17]罗天培,卜玉,李茂,等.某型运载火箭一子级动力系统试验尾流辐射场的数值模拟[J].导弹与航天运载技术,2016(4):67-71.LUO Tianpei,BU Yu,LI Mao,et al.Numerical investigations of tail radiation fields of a launch vehicle first stage test[J].Missles and Space Vehicles,2016(4):67-71.(in Chinese)
[18]甘晓华.航空燃气轮机燃油喷嘴技术[M].北京:国防工业出版社,2006.