Volume 36 Issue 11
Nov.  2021
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WANG Yan, FANG Jie, YANG Jinhui, CAI Guobiao. Simulation study on combustion flow in low-pressure condition of hydrogen-oxygen torch ignitor[J]. Journal of Aerospace Power, 2021, 36(11): 2344-2352. doi: 10.13224/j.cnki.jasp.20200552
Citation: WANG Yan, FANG Jie, YANG Jinhui, CAI Guobiao. Simulation study on combustion flow in low-pressure condition of hydrogen-oxygen torch ignitor[J]. Journal of Aerospace Power, 2021, 36(11): 2344-2352. doi: 10.13224/j.cnki.jasp.20200552

Simulation study on combustion flow in low-pressure condition of hydrogen-oxygen torch ignitor

doi: 10.13224/j.cnki.jasp.20200552
  • Received Date: 2020-12-24
  • Publish Date: 2021-11-28
  • The effects of hydrogen-oxygen injection interval and droplet mean diameter on the combustion flow of the low-temperature liquid hydrogen and liquid oxygen torch electric ignitor in low-pressure condition were investigated by numerical simulation.Discrete phase model(DPM) and 16-step,6 species hydrogen-oxygen chemical reaction mechanism were applied for the analysis.Considering the turbulent combustion effect,the eddy dissipation concept combustion model was utilized for simulation calculation.The temperature results obtained by simulation were in good agreement with those obtained by experiment,and the deviations of pressure were within 5%,thereby verifying the accuracy of the numerical models.As the results shown,under low-pressure condition,when the hydrogen-oxygen injection interval increased,the ignitor head inner wall temperature increased,the chamber pressure decreased,and the combustion length decreased.The larger liquid hydrogen droplets diameter resulted in the longer combustion length and higher head inner wall temperature,besides,the pressure in the ignitor chamber was slightly reduced.The diameter of liquid oxygen droplets had little effect on combustion flow of the ignitor.

     

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  • [1]
    REPAS G A. Hydrogen-oxygen torch ignitor[R].NASA TM-106493,1994.
    [2]
    LIANG P Y.Modeling of SSME fuel preburner ASI[R].NASA N92-32259,1992.
    [3]
    OECHSLEIN W.Status of the Vinci combustion chamber vacuum ignition tests[R].AIAA-2004-3531,2004.
    [4]
    HENSEL C,WIEDMANN D,OECHSLEIN W,et al.Ignition aspects of the Vinci thrust chamber[R].AIAA-2002-4008,2002.
    [5]
    HENDERSON J,FOUST R.RL10-Three decades of H2/O2 space engine evolution,capabilities for the future[R].AIAA 91-3622,1991.
    [6]
    吴宏斌.国外氢氧火箭发动机的火药点火器和电点火器[J].导弹与航天运载技术,1994(5):32-42,76.
    [7]
    朱森元.氢氧火箭发动机及其低温技术[M].北京:国防工业出版社,1995.
    [8]
    ANOOP A,ASSIZ M P,MANU M J.Optimization of length of mixing zone in GH2-GO2 based torch igniter,applying numerical techniques[J].Applied Mechanics and Materials,2014,592/593/594:1692-1696.
    [9]
    孙纪国,王剑虹.低温富燃火炬点火器研究[J].导弹与航天运载技术,1999(6):3-5.
    [10]
    孙纪国,王珏.高混合比火炬式电点火器试验研究[J].推进技术,2000,21(1):34-36.
    [11]
    俞南嘉,蔡国飙,张国舟,等.富氧预燃室初步试验研究[J].宇航学报,2006,27(5):834-838.
    [12]
    郭田莉,孙慧娟.氢氧火炬式电点火系统研究[J].战术导弹技术,2015(3):55-59.
    [13]
    郭田莉,孙慧娟.火炬式电点火系统点火能量的正交试验研究[J].导弹与航天运载技术,2016(2):90-93,96.
    [14]
    杨进慧,王朝晖,左安军,等.氢氧火炬式电点火器燃烧流动分析[J].导弹与航天运载技术,2019,368(3):45-48.
    [15]
    王振国.液体火箭发动机燃烧过程建模与数值仿真[M].北京:国防工业出版社,2012.
    [16]
    蔡国飙.液体火箭发动机气气燃烧及气气喷注器技术[M].北京:国防工业出版社,2012.
    [17]
    聂万胜,丰松江.液体火箭发动机燃烧动力学模型与数值计算[M].北京:国防工业出版社,2011.
    [18]
    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:国防科技大学出版社,1995.
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