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Effects of Additional Cavity Floor Injection on the Ignition and Combustion Processes in a Mach 2 Supersonic Flow

Author

Listed:
  • Fan Li

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

  • Mingbo Sun

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

  • Zun Cai

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

  • Yong Chen

    (College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

  • Yongchao Sun

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

  • Fei Li

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

  • Jiajian Zhu

    (Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)

Abstract

Effects of additional cavity floor injection on the ethylene ignition and combustion processes in a cavity-based scramjet combustor are investigated experimentally in a Mach 2.0 supersonic flow using flame luminosity and CH* (CH radical) spontaneous emission methods and static pressure measurements. Numerical calculation is performed to study the non-reacting flow-field structures prior to ignition. Two injection schemes, including the cavity upstream injection scheme and the combined injection scheme with an additional cavity floor injection, are compared to study the effects of the additional cavity floor injection on the ignition and combustion processes. It is found that there exists an equivalence ratio upper limit for maintaining stable combustion for the cavity upstream injection scheme. As the equivalence ratio further increases, the fuel jet penetration is improved accordingly, and thus, the interaction between the fuel jet and the cavity is weakened, which can lead to the ignition failure and flame blowout during combustion. On the contrary, although the combined injection scheme has a minor effect on combustion enhancement at the same global equivalence ratio, it can also provide a more favorable flow-field environment that enables more successful ignitions and better flame stabilizations. For the combined injection scheme, as the equivalence ratio increases, the initial flame propagations are observed to perform different routines during the ignition process, and the major combustion reaction zone tends to move further downstream the cavity shear layer. It is concluded that the advantages of the combined injection scheme with an additional cavity floor injection are more significant when the equivalence ratio is higher, as well as that the interaction between the fuel jet and the cavity becomes weaker.

Suggested Citation

  • Fan Li & Mingbo Sun & Zun Cai & Yong Chen & Yongchao Sun & Fei Li & Jiajian Zhu, 2020. "Effects of Additional Cavity Floor Injection on the Ignition and Combustion Processes in a Mach 2 Supersonic Flow," Energies, MDPI, vol. 13(18), pages 1-17, September.
    • Handle: RePEc:gam:jeners:v:13:y:2020:i:18:p:4801-:d:413417
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    References listed on IDEAS

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    1. Chaolong Li & Zhixun Xia & Likun Ma & Xiang Zhao & Binbin Chen, 2019. "Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity," Energies, MDPI, vol. 12(7), pages 1-17, March.
    2. Tao Cui & Yang Ou, 2019. "Modeling of Scramjet Combustors Based on Model Migration and Process Similarity," Energies, MDPI, vol. 12(13), pages 1-12, June.
    3. Stephen M. Neill & Apostolos Pesyridis, 2017. "Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight," Energies, MDPI, vol. 10(11), pages 1-22, November.
    4. Chae-Hyoung Kim & In-Seuck Jeung, 2019. "Forced Combustion Characteristics Related to Different Injection Locations in Unheated Supersonic Flow," Energies, MDPI, vol. 12(9), pages 1-13, May.
    5. Devendra Sen & Apostolos Pesyridis & Andrew Lenton, 2018. "A Scramjet Compression System for Hypersonic Air Transportation Vehicle Combined Cycle Engines," Energies, MDPI, vol. 11(6), pages 1-32, June.
    6. Jincheng Zhang & Zhenguo Wang & Mingbo Sun & Hongbo Wang & Chaoyang Liu & Jiangfei Yu, 2020. "Effect of the Backward Facing Step on a Transverse Jet in Supersonic Crossflow," Energies, MDPI, vol. 13(16), pages 1-19, August.
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    Cited by:

    1. Byeong-Jo Hwang & Seongki Min, 2023. "Numerical Investigation of the Effect of Supersonic Air Temperature on the Mixing Characteristics of Liquid Fuel," Energies, MDPI, vol. 16(1), pages 1-17, January.
    2. Wenxiong Xi & Mengyao Xu & Chaoyang Liu & Jian Liu & Bengt Sunden, 2022. "Generation and Propagation Characteristics of an Auto-Ignition Flame Kernel Caused by the Oblique Shock in a Supersonic Flow Regime," Energies, MDPI, vol. 15(9), pages 1-14, May.

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