Volume 37 Issue 2
Feb.  2022
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Article Navigation >  Journal of Aerospace Power  > 2022  >  37(2): 424-432
LIU Yazhou, LI Ping, CHEN Hongyu, YANG Jianwen, CHEN Yidan. Design of dual-bell nozzles with different extension pressure distributions[J]. Journal of Aerospace Power, 2022, 37(2): 424-432. doi: 10.13224/j.cnki.jasp.20210096
Citation: LIU Yazhou, LI Ping, CHEN Hongyu, YANG Jianwen, CHEN Yidan. Design of dual-bell nozzles with different extension pressure distributions[J]. Journal of Aerospace Power, 2022, 37(2): 424-432. doi: 10.13224/j.cnki.jasp.20210096
shu

Design of dual-bell nozzles with different extension pressure distributions

doi: 10.13224/j.cnki.jasp.20210096
  • 1.

    Science and Technology on Liquid Rocket Engine Laboratory，Xi'an Aerospace Propulsion Institute，Xi'an 710100，China

  • 2.

    Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi'an 710100，China

  • Received Date: 2021-03-06
  • Publish Date: 2022-02-28
    Abstract
  • For dual-bell nozzles with different extension pressure distribution，the method of characteristics was used to design the maximum thrust，constant pressure distribution，and positive gradient pressure distribution's extended contours.Then design methods were verified by simulation，and the operating processes of dual-bell nozzles with different extension pressure distributions were investigated.Results showed that，extended contours with specific pressure distributions could be designed by the maximum thrust and reverse design method with wall pressure known.Modes transition time of dual-bell nozzles with extensions positive gradient pressure distribution was less than engine start-up，but time of models with extensions negative gradient pressure and constant pressure distribution was longer.Compared with the maximum thrust contour，dual-bell nozzles with extension positive gradient pressure distribution had some performance loss.When extension pressure rising value was 0.001 5 time combustion chamber pressure，the average specific impulse dropped by 0.44%.

     

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    • References(20)
  • [1]
    王治军，常新龙，田干，等.液体火箭发动机推力室设计[M].北京：国防工业出版社，2014.
    [2]
    刘昌国，邱金莲，陈明亮.液体火箭发动机复合材料喷管延伸段研究进展[J].火箭推进，2019，45（4）:1-8.
    [3]
    ?STLUND J，KLINGMANN B M.Supersonic flow separation with application to rocket engine nozzles[J].Applied Mechanics Reviews，2005，58（3）:143-177.
    [4]
    JOHN J S.Rocket engine nozzle side load transient analysis methodology:a practical approach[R].AIAA-2005-1860，2005.
    [5]
    STARK R，GENIN C.Scaling effects on side load generation in subscale rocket nozzles[R].AIAA-2016-4669，2016.
    [6]
    WATANABE Y，SAKAZUME N，YONEZAWA K.LE-7A engine nozzle flow separation phenomenon and the possibility of RSS suppression by the step inside the nozzle[R].AIAA-2004-4014，2004.
    [7]
    王拴虎.双钟形喷管流场分析及设计方法[J].火箭推进，2002，28（2）:39-43.
    [8]
    STARK R，GéNIN C，CCHNEIDER D.Ariane 5 performance optimization using dual-bell nozzle extension[J].Journal of Spacecraft and Rockets，2016，53（4）:743-750.
    [9]
    NASUTI F，ONOFRI M，MARTELLI E.Role of wall shape on the transition in axisymmetric dual-bell nozzles[J].Journal of Propulsion and Power，2005，21（2）:243-250.
    [10]
    KBAB H，SELLAM M，HAMITOUCHE T，et al.Design and performance evaluation of a dual bell nozzle[J].Acta Astronautica，2017，130（1）:52-59.
    [11]
    张卫红，石文靓，郑孟伟.一种双钟型喷管液氧/甲烷发动机系统方案[J].火箭推进，2013，39（3）:9-14.
    [12]
    MIYAZAWA M，TAKEUCHI S，TAKAHASHI M.Flight performance of dual-bell nozzles[R].AIAA-2002-686，2002.
    [13]
    王一白，覃粒子，刘宇，等.高度补偿喷管的氢氧热试研究[J].航空动力学报，2007，22（2）:316-322.
    [14]
    GéNIN C，STARK R.Side loads in subscale dual bell nozzles[J].Journal of Propulsion and Power，2011，27（4）:828-837.
    [15]
    VERMA M，ARYA N，DE A.Investigation of flow characteristics inside a dual bell nozzle with and without film cooling[J].Aerospace Science and Technology，2020，99（4）:1-14.
    [16]
    PROSHCHANKA D，YONEZAWA K，KOGA H，et al.Control of operation mode transition in dual-bell nozzles with film cooling[J].Journal of Propulsion and Power，2012，28（3）:517-529.
    [17]
    GéNIN C，STARK R，SCHNEIDER D.Transitional behavior of dual bell nozzles:contour optimization[R].AIAA-2013-3841，2013.
    [18]
    GéNIN C，STARK R.Experimental study on flow transition in dual bell nozzles[J].Journal of Propulsion and Power，2010，26（3）:497-502.
    [19]
    RAO G V R.Exhaust nozzle contour for optimum thrust[J].Journal of Jet Propulsion，1958，28（6）:377-382.
    [20]
    SCHNEIDER D，GéNIN C.Numerical investigation of flow transition behavior in cold flow dual-bell rocket nozzles[J].Journal of Propulsion and Power，2016，32（5）:1212-1219.
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