METHOD OF BURNING detonation mode combustor scramjet

摘要

Method organization detonation combustion regime in the combustor scramjet, comprising compression of air in the external and internal shocks arising on fixed and adjustable elements of the fuselage and propulsion system, the fuel supply for the external system jumps to the combustion chamber, forming at its inlet detonation wave, detonation combustion of fuel-air mixture in the combustion chamber, position control of the detonation wave in the combustion chamber in the dependent ing on the Mach number of the flow at combustor inlet by altering the geometrical parameters of the combustion chamber and the chemical composition of the incoming fuel-air mixture and subsequent expansion of the combustion products in the nozzle, characterized in that the fuel-air mixture is generated based on nanodispersed fuel containing carbon nanotubes encapsulated therein hydrogen which is administered prior to the combustion chamber via the fuel injector needle hole toward the oncoming stream, and generate a pulsating combustion zone The present electric field intensity of 20 V / cm.