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Numerical modeling of supersonic-flow deceleration in a two-dimensional duct in combustion of wall tangential hydrogen jets

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Combustion, Explosion and Shock Waves Aims and scope

Abstract

Results are presented of a numerical modeling of the ignition and combustion of underexpanded turbulent hydrogen jets injected into supersonic air flow (M=2.63) along the walls of a two-dimensional duct. Calculations were performed by numerical integration of reduced Navier-Stokes equations using the method of global iterations. The kinetic mechanism of hydrogen combustion in air involved 13 reactions. In the calculations the duct height was varied. In a fairly narrow duct, the static pressure increased with flow deceleration to subsonic velocities due to ignition and combustion. The influence of combustion on the pressure distribution in the transverse direction is ambiguous. Initially, combustion increases the pressure nonuniformity (a new oblique shock wave occurs), while, downstream, the pressure profile is flattened out due to the appearance of a subsonic layer near the flame front.

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Authors and Affiliations

  1. Zhukovskii Central Aerohydrodynamic Institute, 140160, Zhukovskii

    O. M. Kolesnikov

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  1. O. M. Kolesnikov
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Translated from Fizika Goreniya i Vzryva, Vol. 32, No. 4, pp. 47–54, July–August, 1996.

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Kolesnikov, O.M. Numerical modeling of supersonic-flow deceleration in a two-dimensional duct in combustion of wall tangential hydrogen jets. Combust Explos Shock Waves 32, 399–405 (1996). https://doi.org/10.1007/BF01998486

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  • DOI: https://doi.org/10.1007/BF01998486

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