Abstract
Results of studying kerosene combustion in a pseudoshock with varied temperature and velocity in a supersonic ramjet combustor model are presented. Thermodynamic estimates show that either a supersonic or transonic flow can be retained over the combustor duct at parameters corresponding to the Mach number at the engine entrance M0 ≈ 4.5. The possibility of the pseudoshock regime in the constant-section part of the combustor is experimentally studied in the case where the Mach number behind the inlet (at the combustor entrance) is M\(_c\) \(>\) 1. Conditions of initiation and evolution of this combustion mode under a pulsed-periodic action on the flow are determined.
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Translated from Fizika Goreniya i Vzryva, 2021, Vol. 57, No. 6, pp. 3-7.https://doi.org/10.15372/FGV20210601.
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Tretyakov, P.K., Tupikin, A.V. & Zudov, V.N. Kerosene Combustion in a Pseudoshock with Varied Conditions at the Supersonic Ramjet Combustor Model. Combust Explos Shock Waves 57, 635–639 (2021). https://doi.org/10.1134/S0010508221060010
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DOI: https://doi.org/10.1134/S0010508221060010