Volume 35 Issue 12
Dec.  2020
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Article Navigation >  Journal of Aerospace Power  > 2020  >  35(12): 2593-2601
YE Jiawei, ZHANG Shunping, YU Xin. Flame structure in supersonic combustion chamber based on 500 Hz OH-PLIF technology,[J]. Journal of Aerospace Power, 2020, 35(12): 2593-2601. doi: 10.13224/j.cnki.jasp.2020.12.013
Citation: YE Jiawei, ZHANG Shunping, YU Xin. Flame structure in supersonic combustion chamber based on 500 Hz OH-PLIF technology,[J]. Journal of Aerospace Power, 2020, 35(12): 2593-2601. doi: 10.13224/j.cnki.jasp.2020.12.013
shu

Flame structure in supersonic combustion chamber based on 500 Hz OH-PLIF technology,

doi: 10.13224/j.cnki.jasp.2020.12.013
  • 1.

    College of Aerospace Science and Engine,National University of Defense Technology,Changsha 410073,China

  • 2.

    Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China

  • 3.

    Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China

  • 4.

    National Key Laboratory of Science and Technology on Tunable Lase,School of Astronautics,Harbin Institute of Technology,Harbin 150001,China

  • Received Date: 2020-04-25
  • Publish Date: 2020-12-28
    Abstract
  • 500 Hz high-speed OH-PLIF technology was used for the research of the flame structure in supersonic combustion chamber, which was characterized by short time-lag and high turbulence in cavity chamber. Combining the pressure of the wall surface, the ignition, stabilization and extinguishing of the flame were studied. The results showed that ignition occurred when the hydrogen equivalents were 0.1 and 0.3. PLIF camera got the image in 2 ms under the spark. A detonation combustion existed in the cavity of the equivalent ratio of 0.1, and the flame was slower to reach stable state in the cavity (about 65 ms). In the process of stabilization of the flame, the equivalent 0.3 was in an incomplete combustion state, the burning area was closer to the wall, the burning position and nuclear position of the fire were greatly changed at the equivalent 0.3. At the equivalent of 0.1, the flame was transmitted from the middle of the cavity to the front edge of the cavity with a process of a briefly increased flame. Flame extinguished at the front edge of the cavity. However the equivalent 0.3 was slightly weaker, which was eventually extinguished between the front edge of the cavity and the position of hydrogen injection.

     

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    • References(23)
  • [1]
    BOECK L R,KELLENBERGER M,RAINSFORD G,et al.Simultaneous OH-PLIF and schlieren imaging of flame acceleration in an obstacle-laden channel［J］.Proceedings of the Combustion Institute,2017,36(2):2807-2814.
    [2]
    MOIZ A A,CUNG K D,LEE S Y.Simultaneous schlieren-PLIF studies for ignition and soot luminosity visualization with close-coupled high pressure double injections of n-dodecane［J］.Journal of Energy Resources Technology,2016,139(1):012207.1-012207.12.
    [3]
    SKEEN S A,MANIN J,PICKETT L M.Simultaneous formaldehyde PLIF and high-speed schlieren imaging for ignition visualization in high-pressure spray flames［J］.Proceedings of the Combustion Institute,2015,35(3):3167-3174.
    [4]
    李麦亮,周进,耿辉,等.平面激光诱导荧光技术在超声速燃烧中的应用［J］.推进技术,2004,25(4):381-384. LI Mailiang,ZHOU Jin,GENG Hui,et al.Application of planar laser-induced fluorescence in supersonic combustion［J］.Journal of Propulsion Technology,2004,25(4):381-384.(in Chinese)
    [5]
    ROBERTS M J,LAI W W,GROSHENS T J,et al.Nanofiber waveguides and photophysics of an organic dye［J］.Journal of Nanophotonics,2015,9(1):1934-2608.
    [6]
    姜玉刚.高性能固体染料激光介质研制及可调谐激光输出特性研究［D］.哈尔滨:哈尔滨工业大学,2011. JIANG Yugang.Preparation of high performance solid dye laser medium and study on tunable laser output characteristics［D］.Harbin:Harbin Institute of Technology,2011.(in Chinese)
    [7]
    MILLER J D,PELTIER S J,SLIPCHENKO M N,et al.Investigation of transient ignition processes in a model scramjet pilot cavity using simultaneous 100 kHz formaldehyde planar laser-induced fluorescence and CH* chemiluminescence imaging［J］.Proceedings of the Combustion Institute,2017,36(2):2865-2872.
    [8]
    HAMMACK S D,LEE T,HSU K Y,et al.High-repetition-rate OH planar laser-induced fluorescence of a cavity flameholder［J］.Journal of Propulsion and Power,2013,29(5):1248-1251.
    [9]
    田野.空气节流技术在超声速燃烧点火与稳焰中的应用研究［D］.四川 绵阳:中国空气动力研究与发展中心,2016. TIAN Ye.Application of air throttling technology in supersonic combustion ignition and flame stabilization［D］.Mianyang Sichuan:China Aerodynamics Research and Development Center,2016.(in Chinese)
    [10]
    乐嘉陵,刘伟雄,贺伟,等.脉冲燃烧风洞及其在火箭和超燃发动机研究中的应用［J］.实验流体力学,2005,19(1):1-10. LE Jialing,LIU Weixiong,HE Wei,et al.Pulse combustion wind tunnel and its application in rocket and scramjet research［J］.Experimental Fluid Dynamics,2005,19(1):1-10.(in Chinese)
    [11]
    邓维鑫,乐嘉陵,杨顺华,等.M3条件下乙烯燃料超燃冲压发动机空气节流点火试验［J］.推进技术,2013,34(9):1240-1247. DENG Weixin,LE Jialing,YANG Shunhua,et al.Air throttling ignition test of ethylene fueled scramjet under M3 condition［J］.Propulsion Technology,2013,34(9):1240-1247.(in Chinese)
    [12]
    DENG Weixin,LE Jialing,YANG Shunhua,et al.Ethylene fueled scramjet combustion experiments［J］.Modern Applied Science,2013,7(5):51-59.(in Chinese)
    [13]
    邓维鑫,乐嘉陵,杨顺华,等.注油方式对超燃冲压发动机燃烧性能的影响［J］.航空动力学报,2013,28(7):1449-1457. DENG Weixin,LE Jialing,YANG Shunhua,et al.Effect of oil injection mode on combustion performance of scramjet［J］.Journal of Aerospace Power,2013,28(7):1449-1457.(in Chinese)
    [14]
    赵衡阳.气体和粉尘爆炸原理［M］.北京:北京理工大学出版社,1996.
    [15]
    白丽荣.内置障碍物受限空间易燃气体爆燃过程数值仿真［D］.哈尔滨:哈尔滨工业大学,2014. BAI Lirong.Numerical simulation of flammable gas deflagration process in confined space with built-in obstacles［D］.Harbin:Harbin Institute of Technology,2014.(in Chinese)
    [16]
    李晨阳,吴里银,李春,等.超声速气流中凹腔对液体射流穿透深度的影响［J］.航空动力学报,2018,33(1):232-238. LI Chenyang,WU Liyin,LI Chun,et al.Influence of cavity on penetration depth of liquid jet in supersonic flow［J］.Journal of Aerospace Power,2018,33(1):232-238.(in Chinese)
    [17]
    林宇震,李林,张弛,等.液体射流喷入横向气流混合特性研究进展［J］.航空学报,2014,35(1):46-57. LIN Yuzhen,LI Lin,ZHANG Chi,et al.Research progress on mixing characteristics of liquid jet injection cross flow［J］.Acta Aeronautica Sinica,2014,35(1):46-57.(in Chinese)
    [18]
    DAGAUT P,CATHONNET M.The ignition,oxidation,and combustion of kerosene:A review of experimental and modeling［J］.Progress in Energy and Combustion Science,2006,32(1):48-92.
    [19]
    VASU S S,DAVIDSON D F,HANSON R K.Jet fuel ignition delay times:shock tube experiments over wide conditions and surrogate model predictions［J］.Combustion and Flame,2008,152(1/2):125-143.
    [20]
    DEAN A J,PENYAZKOV O G,SEVRUK K L,et al.Autoignition of surrogate fuels at elevated temperatures and pressures［J］.Proceedings of the Combustion Institute,2007,31(2):2481-2488.
    [21]
    DOWDY D R,SMITH D B,TAYLOR S C,et al.The use of expanding spherical flames to determine burning velocities and stretch effects in hydrogen/air mixtures［J］.Symposium on Combustion,1991,23(1):325-332.
    [22]
    AUNG K T,HASSAN M I,FAETH G M.Effects of pressure and nitrogen dilution on flame/stretch interactions of laminar premixed H2/O2/N2 flames［J］.1998,112(1/2):1-15.
    [23]
    BRADLEY D,LAWES M,LIU K,et al.Laminar burning velocities of lean hydrogen-air mixtures at pressures up to 1.0 MPa［J］.Combustion and Flame,2007,149(1/2):162-172.
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