Control of detonation combustion in a high-velocity gas mixture flow

Within the framework of a detailed kinetic mechanism of chemical interaction, we study detonation combustion of a stoichiometric hydrogen–air mixture flowing at a supersonic velocity into a plane symmetric channel with narrowing cross section (constriction). The goal of the study is to determine conditions that guarantee the formation of a thrust-producing flow with a stabilized detonation wave in the channel. With a view to increasing the efficiency of detonation combustion of the gas mixture, we analyze the effect of variations of the inflow Mach number, the concentration of inert particles added to the combustible mixture flowing into the channel, and the geometric parameters of the channel on the position of a stabilized detonation wave in the flow. We also study the possibility of formation without energy expenditure of a thrust-producing flow with a stabilized detonation wave in a channel with narrowing cross section.