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The Effect of Fuel Injection Location on Supersonic Hydrogen Combustion in a Cavity-Based Model Scramjet Combustor

Author

Listed:
  • Eunju Jeong

    (Department of Aerospace Engineering, Seoul National University, Seoul 08826, Korea)

  • Sean O’Byrne

    (School of Aerospace and Mechanical Engineering, University of New South Wales, Australian Defence Force Academy, Canberra, ACT 2600, Australia)

  • In-Seuck Jeung

    (Department of Aerospace Engineering & Institute of Advanced Aerospace Technology, Seoul National University, Seoul 08826, Korea)

  • A. F. P. Houwing

    (Department of Physics, Faculty of Science, The Australian National University, Canberra, ACT 0200, Australia)

Abstract

Supersonic combustion experiments were performed using three different hydrogen fuel-injection configurations in a cavity-based model scramjet combustor with various global fuel–air equivalence ratios. The configurations tested were angled injection at 15° to the flow direction upstream of the cavity, parallel injection from the front step, and upstream injection from the rear ramp. Planar laser-induced fluorescence of the hydroxyl radical and time-resolved pressure measurements were used to investigate the flow characteristics. Angled injection generated a weak bow shock in front of the injector and recirculation zone to maintain the combustion as the equivalence ratio increased. Parallel and upstream injections both showed similar flame structure over the cavity at low equivalence ratio. Upstream injection enhanced the fuel diffusion and enabled ignition with a shorter delay length than with parallel injection. The presence of a flame near the cavity was determined while varying the fuel injection location, the equivalence ratio, and total enthalpy of the air flow. The flame characteristics agreed with the correlation plot for the stable flame limit of non-premixed conditions. The pressure increase in the cavity for reacting flow compared to non-reacting flow was almost identical for all three configurations. More than 300 mm downstream of the duct entrance, averaged pressure ratios at low global equivalence ratio were similar for all three injection configurations.

Suggested Citation

  • Eunju Jeong & Sean O’Byrne & In-Seuck Jeung & A. F. P. Houwing, 2020. "The Effect of Fuel Injection Location on Supersonic Hydrogen Combustion in a Cavity-Based Model Scramjet Combustor," Energies, MDPI, vol. 13(1), pages 1-16, January.
    • Handle: RePEc:gam:jeners:v:13:y:2020:i:1:p:193-:d:304086
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    Citations

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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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