涡流冷却推力室流场特征与性能仿真

李恭楠; 俞南嘉; 路强

doi:10.13224/j.cnki.jasp.2014.02.022

涡流冷却推力室流场特征与性能仿真

doi: 10.13224/j.cnki.jasp.2014.02.022

北京航空航天大学宇航学院, 北京 100191

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出版历程
- 收稿日期: 2012-12-21
- 刊出日期: 2014-02-28

Simulation of flow characteristics and performance of vortex cooling thrust chamber

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对2000N气氢/气氧涡流冷却推力室，采用三维全尺寸计算模型开展了仿真研究，得到了流场速度分布特点，验证了涡流冷却推力室内具有双向涡旋结构，内外涡流分界面约占涡流冷却推力室圆柱段半径的86%，燃烧区域约占涡流冷却推力室圆柱段半径的70%.分析表明：外层涡流主要受来流速度与涡流冷却推力室几何参数影响，内层涡流在黏性、燃烧等作用下室压、密度稳定.侧壁温度平均为388K，比冲效率达92%以上，仿真结果与试验对比一致.
- 涡流冷却 /
- 流场特征 /
- 推力室性能 /
- 数值仿真 /
- 双涡旋结构
Abstract: Numerical simulation of 3-D full-size model was conducted for 2000N gas hydrogen/gas oxygen vortex cooling thrust chamber.Velocity distribution characteristics of the flow field were obtained,and existence of the bidirectional vortex structure was verified.The interface of inner and outer vortexes accounted for 86% of the thrust chamber cylinder radius,and the combustion zone took up 70% of the thrust chamber cylinder radius.Analysis showed that the outer vortex cooling layer was mainly influenced by incoming stream velocity and geometric parameters of thrust chamber. The pressure and density of the inner vortex maintained stable due to the viscosity and combustion.The average temperature of the thrust chamber sidewall was 388K.The specific efficiency was above 92%.The results of computation were consistent with the experiment results.
- vortex cooling /
- flow characteristics /
- thrust chamber performance /
- numerical simulation /
- dual vortex structure

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参考文献(15)

[1]	Chiavertini M J, Malecki M J, Sauer J A, et al.Vortex combustion chamber development for future liquid rocket engine applications[R].AIAA 2002-4149, 2002.
[2]	Chiaverini M J, Malecki M J, Sauer J A, et al.Vortex thrust chamber testing and analysis for O₂/H₂ propulsion applications[R].AIAA 2003-4473, 2003.
[3]	Chiavertini M J, Sauer J A, Munson S M, et al.Laboratory characterization of vortex-cooled thrust chamber for methane/O₂ and H₂/O₂[R].AIAA 2005-4131, 2005.
[4]	Munson S M, Saucer J A, Rocholl J D, et al.Development of a low-cost vortex-cooled thrust chamber using hybrid fabrication techniques[R].AIAA 2011-5835, 2011.
[5]	Knuth W H, Gramer D J, Chiaverini M J, et al.Preliminary CFD analysis of the vortex hybrid rocket chamber and nozzle flow field[R].AIAA 98-3351, 1998.
[6]	孙得川, 白荣博, 刘上.涡流冷壁推力室传热模型分析计算[J].计算机仿真, 2011, 28(4):87-91. SUN Dechuan, BAI Rongbo, LIU Shang.A heat transfer model for vortex cool-wall rocket engine chamber[J].Computer Simulation, 2011, 28(4):87-91.(in Chinese)
[7]	唐飞, 李家文, 常克宇.涡流冷却推力室中涡流结构的分析与优化[J].推进技术, 2010, 31(2):165-169. TANG Fei, LI Jiawen, CHANG Keyu.Analysis and optimization of vortex-cooled combustion chamber[J].Journal of Propulsion Technology, 2010, 31(2):165-169.(in Chinese)
[8]	Fang D Q, Majdalani J, Chiaverini M J, et al.Simulation of the cold-wall swirl-driven combustion chamber[R].AIAA 2003-5055, 2003.
[9]	孙得川, 杨建文, 白荣博.气氧/甲烷涡流冷壁燃烧室流场与壁面耦合传热分析[J].推进技术, 2011, 32(3):401-406. SUN Dechuan, YANG Jianwen, BAI Rongbo.Heat transfer analysis for a GOx/CH₄ vortex cold-wall combustor[J].Journal of Propulsion Technology, 2011, 32(3):401-406.(in Chinese)
[10]	Fang D Q, Majdalani J, Chiaverini M J.Hot flow model of the vortex cold wall liquid rocket[R].AIAA 2004-3676, 2004.
[11]	吴东波, 李家文, 常克宇.GH₂/GO₂涡流冷却推力室设计与数值计算[J].火箭推进, 2010, 36(5):17-22. WU Dongbo, LI Jiawen, CHANG Keyu.Design and numerical calculation of GH₂/GO₂ vortex-cooled combustion chamber[J].Journal of Rocket Propulsion, 2010, 36(5):17-22.(in Chinese)
[12]	Vyas A B, Majdalani J, Chiaverini M J.The bidirectional vortex:Part 1 an exact inviscid solution[R].AIAA 2003-5052, 2003.
[13]	Vyas A B, Majdalani J, Chiaverini M J.The bidirectional vortex:Part 2 viscous core corrections[R].AIAA 2003-5053, 2003.
[14]	Vyas A B, Majdalani J, Chiaverini M J.The bidirectional vortex:Part 3 multiple solutions[R].AIAA 2003-5054, 2003.
[15]	李家文, 唐飞, 俞南嘉.推力室涡流冷却技术试验研究[J].推进技术, 2012, 33(6):956-960. LI Jiawen, TANG Fei, YU Nanjia.Experimental study on vortex-cooled thrust chamber[J].Journal of Propulsion Technology, 2012, 33(6):956-960.(in Chinese)