Kerosene Combustion in a Pseudoshock with Varied Conditions at the Scramjet Combustor Model
P. K. Tretyakov, A. V. Tupikin, V. N. Zudov
Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, 630090 Russia
Keywords: combustor, supersonic combustion ramjet (scramjet), supersonic flow, wave structures, combustion in a pseudoshock
Abstract
Results of studying kerosene combustion in a pseudoshock with varied temperature and velocity at the scramjet 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 М0 » 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 М 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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