SETTING OF DETONATION COMBUSTION IN COMBUSTION CHAMBER OF HYPERSONIC RAMJET Russian patent published in 2014 - IPC F02K7/12 

FIELD: engines and pumps.

SUBSTANCE: proposed process comprises air compression in system of external and internal shock waves originating at fuselage and engine fixed and controlled elements, fuel feed beyond external system of shock waves upstream of combustion chamber and generation of detonation wave at its inlet. Detonation combustion of fuel-air mix is performed in combustion chamber at control over detonation wave therein subject to flow. Mach number at combustion chamber inlet by measurement of its geometrical parameters and chemical composition of fed fuel-air mix. Combustion products are expanded in the nozzle. Fuel-air mix is created on the basis of nano-dispersed fuel including carbon nanotubes with hydrogen encapsulated therein and forced via needle injectors upstream of combustion chamber opposite oncoming flow. Pulsating electric field of intensity over 20 V/cm is generated in combustion zone.

EFFECT: higher combustion rate, better combustion and engine efficiency.

1 dwg