Volume 39 Issue 6
Jun.  2024
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ZHOU Zhitan, LI Yiqing, JIANG Ping, et al. Effect of secondary combustion on the multi-nozzle rocket base thermal environment[J]. Journal of Aerospace Power, 2024, 39(6):20210694 doi: 10.13224/j.cnki.jasp.20210694
Citation: ZHOU Zhitan, LI Yiqing, JIANG Ping, et al. Effect of secondary combustion on the multi-nozzle rocket base thermal environment[J]. Journal of Aerospace Power, 2024, 39(6):20210694 doi: 10.13224/j.cnki.jasp.20210694

Effect of secondary combustion on the multi-nozzle rocket base thermal environment

doi: 10.13224/j.cnki.jasp.20210694
  • Received Date: 2021-12-06
    Available Online: 2024-01-23
  • During rocket launching, the secondary combustions between the fuel-rich exhaust gas and the oxygen of air were made, leading to a temperature rise. Based on three-dimensional compressible Navier-Stokes equation, hybrid RANS/LES turbulence model, DOM model, and finite-rate chemical kinetics, the reaction model of multi-nozzle rocket was established. And the validity of model was verified by comparing with the wind tunnel experimental data. Then, a comparison study between reaction and frozen flows of two-/four-nozzle rockets was developed. The results showed that the secondary combustion mainly occurred in the mixed layer. With the increase of the flight altitudes, the increase of the peak temperature caused by afterburning decreased, while the maximum was 10.16% and the minimum was 0.86%. At the same height, the afterburning effect was strengthened with increasing distance from nozzle exit. Comparing with two-nozzle rocket, the afterburning had less effect on the four-nozzle rocket base thermal environment. In addition, the peak heat flux of the rocket base increased first and then decreased with height.

     

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  • [1]
    罗天培,刘瑞敏,李茂,等. 基于DPM的试验台导流槽喷水冷却数值研究[J]. 航空动力学报,2018,33(2): 497-507. LUO Tianpei,LIU Ruimin,LI Mao,et al. Numerical investigations of water-spray cooling effect on test stand’s deflector based on DPM[J]. Journal of Aerospace Power,2018,33(2): 497-507. (in Chinese

    LUO Tianpei, LIU Ruimin, LI Mao, et al. Numerical investigations of water-spray cooling effect on test stand’s deflector based on DPM[J]. Journal of Aerospace Power, 2018, 33(2): 497-507. (in Chinese)
    [2]
    FRY D,MADZUNKOV S,SIMCIC J,et al. Application of scaling methods to foster ground development of active shielding concepts for space exploration[J]. Acta Astronautica,2021,178: 296-307. doi: 10.1016/j.actaastro.2020.08.038
    [3]
    ZHOU Zhitan,LIANG Xiaoyang,ZHAO Changfang,et al. Investigations of base thermal environment on four-nozzle liquid launch vehicle at high altitude[J]. Journal of Spacecraft and Rockets,2020,57(1): 49-57. doi: 10.2514/1.A34492
    [4]
    闫指江,沈丹,吴彦森,等. 多喷管运载火箭底部热环境研究[J]. 导弹与航天运载技术,2021(1): 105-109,114. YAN Zhijiang,SHEN Dan,WU Yansen,et al. Research on the base heating environment of a multi-nozzle heavy launch vehicle[J]. Missiles and Space Vehicles,2021(1): 105-109,114. (in Chinese

    YAN Zhijiang, SHEN Dan, WU Yansen, et al. Research on the base heating environment of a multi-nozzle heavy launch vehicle[J]. Missiles and Space Vehicles, 2021(1): 105-109, 114. (in Chinese)
    [5]
    张涛,孙冰. 某探测器上火箭发动机热防护仿真与设计[J]. 航空动力学报,2010,25(6): 1407-1411. ZHANG Tao,SUN Bing. Simulation and design of thermal protection of rocket motor in certain detector[J]. Journal of Aerospace Power,2010,25(6): 1407-1411. (in Chinese

    ZHANG Tao, SUN Bing. Simulation and design of thermal protection of rocket motor in certain detector[J]. Journal of Aerospace Power, 2010, 25(6): 1407-1411. (in Chinese)
    [6]
    周志坛,丁逸夫,乐贵高,等. 高空飞行环境中液体运载火箭底部热环境研究[J]. 宇航学报,2019,40(5): 577-584. ZHOU Zhitan,DING Yifu,LE Guigao,et al. Studies on thermal environment of liquid launch vehicle tail compartmentat high altitude[J]. Journal of Astronautics,2019,40(5): 577-584. (in Chinese

    ZHOU Zhitan, DING Yifu, LE Guigao, et al. Studies on thermal environment of liquid launch vehicle tail compartmentat high altitude[J]. Journal of Astronautics, 2019, 40(5): 577-584. (in Chinese)
    [7]
    谢政,谢建,常正阳,等. 火箭发射燃气流二次燃烧数值研究[J]. 宇航学报,2017,38(5): 542-549. XIE Zheng,XIE Jian,CHANG Zhengyang,et al. Numerical research on jet secondary combustion of rocket launch[J]. Journal of Astronautics,2017,38(5): 542-549. (in Chinese

    XIE Zheng, XIE Jian, CHANG Zhengyang, et al. Numerical research on jet secondary combustion of rocket launch[J]. Journal of Astronautics, 2017, 38(5): 542-549. (in Chinese)
    [8]
    ZHUKOV V P. The impact of methane oxidation kinetics on a rocket nozzle flow[J]. Acta Astronautica,2019,161: 524-530. doi: 10.1016/j.actaastro.2019.01.001
    [9]
    GONZÁLEZ D R,WALLMAN P,SANFORD M,et al. Characterization of rocket-plume fluid-dynamic environment using numerical and experimental approaches[J]. Journal of Spacecraft and Rockets,2013,50(3): 527-539. doi: 10.2514/1.A32319
    [10]
    BAO Xingdong,YU Xilong,WANG Zhenhua,et al. Numerical investigation on flow and radiation characteristics of solid rocket motor plume near the ground[J]. Procedia Computer Science,2020,174: 645-650. doi: 10.1016/j.procs.2020.06.137
    [11]
    PERGAMENT H S,JENSEN D E. Influence of chemical kinetic and turbulent transport coefficients on afterburning rocket plumes[J]. Journal of Spacecraft and Rockets,1971,8(6): 643-649. doi: 10.2514/3.59705
    [12]
    RAO R,SINHA K,CANDLER G,et al. Numerical simulations of Atlas II rocket motor plumes: AIAA 1999-2258[R]. Reston,Virigina: AIAA,1999.
    [13]
    CANDLER G,RAO R,SINHA K. Simulations of Atlas-II rocket motor plumes: AIAA 2001-354 [R]. Reston,Virigina: AIAA,2001.
    [14]
    POUBEAU A,PAOLI R,CARIOLLE D. Evaluation of afterburning chemistry in solid-rocket motor jets using an off-line model[J]. Journal of Spacecraft and Rockets,2016,53(2): 380-388. doi: 10.2514/1.A33311
    [15]
    乔野,聂万胜,丰松江,等. 复燃对氢氧火箭发动机尾焰流场及辐射特性影响数值研究[J]. 导弹与航天运载技术,2016(2): 22-25,71. QIAO Ye,NIE Wansheng,FENG Songjiang,et al. Numerical research on influence exerted by afterburning on flow field and radiation characteristics of LH2/LOX rocket engine[J]. Missiles and Space Vehicles,2016(2): 22-25,71. (in Chinese

    QIAO Ye, NIE Wansheng, FENG Songjiang, et al. Numerical research on influence exerted by afterburning on flow field and radiation characteristics of LH2/LOX rocket engine[J]. Missiles and Space Vehicles, 2016(2): 22-25, 71. (in Chinese)
    [16]
    李霞,刘建国,王俊,等. 固体火箭发动机喷焰复燃及其对红外辐射的影响[J]. 红外与激光工程,2018,47(9): 0904003. LI Xia,LIU Jianguo,WANG Jun,et al. Afterburning and infrared radiation effects of exhaust plumes for solid rocket motors[J]. Infrared and Laser Engineering,2018,47(9): 0904003. (in Chinese doi: 10.3788/IRLA201847.0904003

    LI Xia, LIU Jianguo, WANG Jun, et al. Afterburning and infrared radiation effects of exhaust plumes for solid rocket motors[J]. Infrared and Laser Engineering, 2018, 47(9): 0904003. (in Chinese) doi: 10.3788/IRLA201847.0904003
    [17]
    ZHOU Zhitan,LE Guigao,ZHANG Liangjun. Numerical studies of afterburning on impingement flowfield of the four-engine rockets[J]. Journal of Spacecraft and Rockets,2020,57(6): 1284-1294. doi: 10.2514/1.A34672
    [18]
    任泓帆,朱定强. 液体火箭发动机尾焰复燃对红外辐射特性的影响[J]. 推进技术,2018,39(6): 1227-1233. REN Hongfan,ZHU Dingqiang. Effects of afterburning on infrared radiation characteristics of liquid rocket exhaust plume[J]. Journal of Propulsion Technology,2018,39(6): 1227-1233. (in Chinese

    REN Hongfan, ZHU Dingqiang. Effects of afterburning on infrared radiation characteristics of liquid rocket exhaust plume[J]. Journal of Propulsion Technology, 2018, 39(6): 1227-1233. (in Chinese)
    [19]
    杨桦,姜毅,陶倩楠,等. 复燃现象对导流器排导流场影响数值分析[J]. 固体火箭技术,2020,43(3): 393-399. YANG Hua,JIANG Yi,TAO Qiannan,et al. Numerical analysis of afterburning’s influence on division flow field with deflector[J]. Journal of Solid Rocket Technology,2020,43(3): 393-399. (in Chinese

    YANG Hua, JIANG Yi, TAO Qiannan, et al. Numerical analysis of afterburning’s influence on division flow field with deflector[J]. Journal of Solid Rocket Technology, 2020, 43(3): 393-399. (in Chinese)
    [20]
    SAKAMI M,CHARETTE A,LE DEZ V. Radiative heat transfer in three-dimensional enclosures of complex geometry by using the discrete-ordinates method[J]. Journal of Quantitative Spectroscopy and Radiative Transfer,1998,59(1/2): 117-136.
    [21]
    FREY A E,T’IEN J S. A theory of flame spread over a solid fuel including finite-rate chemical kinetics[J]. Combustion and Flame,1979,36: 263-289. doi: 10.1016/0010-2180(79)90064-6
    [22]
    TSANG W,HAMPSON R F. Chemical kinetic data base for combustion chemistry: Part I methane and related compounds[J]. Journal of Physical and Chemical Reference Data,1986,15(3): 1087-1279. doi: 10.1063/1.555759
    [23]
    VARGA T,OLM C,NAGY T,et al. Development of a joint hydrogen and syngas combustion mechanism based on an optimization approach[J]. International Journal of Chemical Kinetics,2016,48(8): 407-422. doi: 10.1002/kin.21006
    [24]
    MEHTA M,CANABAL F,TASHAKKOR S B,et al. Numerical base heating sensitivity study for a four-rocket engine core configuration[J]. Journal of Spacecraft and Rockets,2013,50(3): 509-526. doi: 10.2514/1.A32287
    [25]
    HAN D,MUNGAL M G. Direct measurement of entrainment in reacting/nonreacting turbulent jets[J]. Combustion and Flame,2001,124(3): 370-386. doi: 10.1016/S0010-2180(00)00211-X
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