Volume 36 Issue 4
Apr.  2021
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ZHANG Botao, LI Wenlong, LI Ping. Spray angle model of gas-liquid pintle injector unit[J]. Journal of Aerospace Power, 2021, 36(4): 839-850. doi: 10.13224/j.cnki.jasp.2021.04.016
Citation: ZHANG Botao, LI Wenlong, LI Ping. Spray angle model of gas-liquid pintle injector unit[J]. Journal of Aerospace Power, 2021, 36(4): 839-850. doi: 10.13224/j.cnki.jasp.2021.04.016

Spray angle model of gas-liquid pintle injector unit

doi: 10.13224/j.cnki.jasp.2021.04.016
  • Received Date: 2020-06-10
  • Publish Date: 2021-04-28
  • In order to accurately predict the spray angle of pintle injector unit, the theoretical model of spray angle of liquid jet impinging on gas sheet was established based on momentum conservation. The deformation factor was obtained by experimental results. Moreover, the influence of structure parameters and operation parameters on spray angle was analyzed. The results showed that the local momentum ratio had the greatest influence on the spray angle, and other structure parameters and operation parameters further determined the spray angle by influencing the local momentum ratio. As the local momentum ratio increased, the deformation of the liquid jet decreased. The effective momentum ratio was less than the geometric momentum ratio due to liquid jet deformation. According to the experimental results, the value of the deformation factor was given in sections. When the local momentum ratio ranged from 0 to 3, the recommended value of the deformation factor was 0.61. When the local momentum ratio ranged from 3 to 4.5, the recommended value of the deformation factor was 0.70.When the local momentum ratio ranged from 4.5 to 7.2, the recommended value of the deformation factor was 0.75. The theoretical predicted value of the deformation factor was in good agreement with the experimental results. This model can provide a reference for the theoretical research and engineering design of gas-liquid pintle injector.

     

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  • [1]
    岳春国,李进贤,侯晓,等.变推力液体火箭发动机综述[J].中国科学E辑:技术科学,2009,39(3):464-468. YUE Chunguo,LI Jinxian,HOU Xiao,et al.The research on technology actuality and development of pintle injector variable thrust rocket engine[J].Science in China Series E:Technological Sciences,2009,39(3):464-468.(in Chinese)
    [2]
    DRELLSER G A,BAUER J M.TRW pintle engine heritage and performance characteristics[R].AIAA 2000-3871,2000.
    [3]
    BEDARD M J,MEIER J,ANDERSON W.Student design/build/test of a throttleable LOX/LCH4 thrust chamber[R].AIAA 2012-3883,2012.
    [4]
    MULLER T,DRELLSER G A.TRW 40 klbf LOx/RP-1 low cost pintle engine test results[R].AIAA 2000-3863,2000.
    [5]
    GAVITT K,HARDGROVE J,MULLER T.TRW’s ultra low cost LOx/LH2 booster liquid rocket engine[R].AIAA 1997-2818,1997.
    [6]
    GAVITT K,MULLER T,WONG T.TRW LCPE 650 klbf LOx/LH2 test results[R].AIAA 2000-3853,2000.
    [7]
    GAVITT K,MULLER T.Testing of the 650 klbf LOx/LH2 low cost pintle engine(LCPE)[R].AIAA 2001-3987,2001.
    [8]
    雷娟萍,兰晓辉,章荣军,等.嫦娥三号探测器7 500 N 变推力发动机研制[J].中国科学E辑:技术科学,2014,44(6):569-575. LEI Juanping,LAN Xiaohui,ZHANG Rongjun,et al.The development of 7500 N variable thrust engine for Chang’E-3[J].Science in China Series E:Technological Sciences,2014,44(6):569-575.(in Chinese)
    [9]
    刘昌波,兰晓辉,李福云,等.载人登月舱下降发动机技术研究[J].火箭推进,2011,37(2):8-13. LIU Changbo,LAN Xiaohui,LI Fuyun,et al.Conceptual schemes of China lunar excursion module descent engine[J].Journal of Rocket Propulsion,2011,37(2):8-13.(in Chinese)
    [10]
    王丹,陈宏玉,周晨初.电动泵压式发动机系统方案与性能评估[J].火箭推进,2018,44(2):28-32. WANG Dan,CHEN Hongyu,ZHOU Chenchu.Design of single-component balance for small thrust measurement of attitude control engine[J].Journal of Rocket Propulsion,2018,44(2):28-32.(in Chinese)
    [11]
    沈文金,叶小强.深度变推发动机浮动环工作适应性研究[J].火箭推进,2017,43(5):28-33. SHEN Wenjin,YE Xiaoqiang.Investigation for working adaptability of floating ring seals in deep throttling engines[J].Journal of Rocket Propulsion,2017,43(5):28-33.(in Chinese)
    [12]
    GROMSKI J M,MAJAMAKI A N,CHIANESE S G,et al.Northrop Grumman TR202 LOC/LH2 deep throttling engine technology project status[R].AIAA 2010-6725,2010.
    [13]
    CHENG P,LI Q L,XU S,et al.On the prediction of spray angle of liquid-liquid pintle injectors[J].Acta Astronautica,2017,138:145-151.
    [14]
    成鹏.变推力火箭发动机喷雾燃烧动态过程研究[D].长沙:国防科技大学,2018. CHENG Peng.The dynamics of spray combustion in variable thrust rocket engines[D].Changsha:National University of Defense Technology,2018.(in Chinese)
    [15]
    王凯,雷凡培,张波涛,等.针栓式喷注单元雾化角模型分析研究[J].航空学报,2020,41(10):123622.1-123622.15. WANG Kai,LEI Fanpei,ZHANG Botao,et al.Study on spray angle model of pintle injector element[J].Acta Aeronautica et Astronautica Sinica,2020,41(10):123622.1-123622.15.(in Chinese)
    [16]
    BLAKELY J,FREEBERG J,HOGEE J.Spray cone formulation from pintle-type injector systems in liquid rocket engines[R].AIAA 2019-0152,2019.
    [17]
    SON M,YU K,KOO J,et al.Effect of momentum ration and Weber number on spray half angles of liquid controlled pintle injector[J].Journal of Thermal Science,2015,24(1):37-43.
    [18]
    方昕昕,沈赤兵,张新桥.针栓式喷注器锥形液膜破碎特性试验[J].航空动力学报,2016,31(12):3004-3009. FANG Xinxin,SHEN Chibin,ZHANG Xinqiao.Experiment of breakup characteristics on conical sheets of pintle injectors[J].Journal of Aerospace Power,2016,31(12):3004-3009.(in Chinese)
    [19]
    方昕昕,沈赤兵,张新桥.针栓式喷注器雾化特性试验[J].航空动力学报,2017,32(8):2853-2860. FANG Xinxin,SHEN Chibin,ZHANG Xinqiao.Experiment on atomization characteristics of pintle injectors[J].Journal of Aerospace Power,2017,32(8):2853-2860.(in Chinese)
    [20]
    RADHAKRISHNAN K,SON M,LEE K,et al.Effect of injection conditions on mixing performance of pintle injector for liquid rocket engine[J].Acta Astronautica,2018,150:105-116.
    [21]
    SAKAKI K,KAKUDO H,NAKAYA S,et al.Optical measurements of ethanol/liquid oxygen rocket engine combustor with planar pintle injector[R].AIAA 2015-3845,2015.
    [22]
    SAKAKI K,KAKUDO H,NAKAYA S,et al.Performance evaluation of rocket engine combustors using ethanol/liquid oxygen pintle injector[R].AIAA 2016-5080,2016.
    [23]
    刘日超,乐嘉陵,杨顺华,等.KH-RT 模型在横向来流作用下射流雾化过程的应用[J].推进技术,2017,38(7):1595-1602. LIU Richao,LE Jialing,YANG Shunhua,et al.Application of KH-RT model in process of spray jet breakup in across-flow[J].Journal of Propulsion Technology,2017,38(7):1595-1602.(in Chinese)
    [24]
    PATTERSON M A.Modeling the effects of fuel injection characteristics on diesel combustion and emissions[D].Madison,US:University of Wisconsin-Madison,1994.
    [25]
    PATTERSON M A,REITZ R D.Modeling the effects of fuel spray characteristics on diesel engine combustion and emission[J].Journal of Engines,1998,107(3):27-43.
    [26]
    MENTER F R.Elements and applications of scale-resolving simulation methods in industrial CFD[M].Berlin:Springer,2015:179-195.
    [27]
    MENTER F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
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