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Numerical Investigation of the Effect of Supersonic Air Temperature on the Mixing Characteristics of Liquid Fuel

Author

Listed:
  • Byeong-Jo Hwang

    (Weapon Systems Engineering, University of Science and Technology, Daejeon 34133, Republic of Korea)

  • Seongki Min

    (Weapon Systems Engineering, University of Science and Technology, Daejeon 34133, Republic of Korea
    Aerospace Technology Research Institute, Agency for Defense Development, Daejeon 34186, Republic of Korea)

Abstract

The effect of supersonic air temperature on the mixing characteristics of liquid hydrocarbon fuel injected into three different supersonic airflows elevated in three steps from 373 K to 673 K was investigated numerically. Compressible Reynolds-averaged Navier–Stokes (RANS) equations were solved together with species conservation equation using ANSYS Fluent for two-phase flow simulations including fuel droplet breakup and evaporation. The turbulence model needed to close the RANS equations used the Shear Stress Transport (SST) k-ω model. The Eulerian–Lagrangian model was employed to track fuel droplets in mainstream air, and the Kelvin–Helmholtz and Rayleigh–Taylor (KH-RT) models were used to simulate the droplet breakup process. Numerical solutions were validated using experimental data. The higher the air temperature, the stronger the streamwise vortices downstream of the pylon. When the air temperature was 373 K, the liquid fuel hardly evaporated, but as the air temperature increased, and the mass fraction of the vaporized fuel and the mixing efficiency increased linearly downstream of the pylon. At air temperatures of 523 K and 673 K, the mixing efficiencies were 10% and 51% at the combustor outlet, respectively. The total pressure loss decreased slightly due to droplet evaporation as the temperature increased from 373 K to 673 K.

Suggested Citation

  • 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.
    • Handle: RePEc:gam:jeners:v:16:y:2023:i:1:p:496-:d:1022727
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    References listed on IDEAS

    as
    1. Naresh Relangi & Antonella Ingenito & Suppandipillai Jeyakumar, 2021. "The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor," Energies, MDPI, vol. 14(9), pages 1-13, May.
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    4. A. Antony Athithan & S. Jeyakumar & Norbert Sczygiol & Mariusz Urbanski & A. Hariharasudan, 2021. "The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor," Energies, MDPI, vol. 14(4), pages 1-20, February.
    5. Zhen Li & Hongbin Gu, 2022. "Investigation for Effects of Jet Scale on Flame Stabilization in Scramjet Combustor," Energies, MDPI, vol. 15(10), pages 1-16, May.
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    7. 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.
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