METHOD OF ORGANIZATION OF DETONATION COMBUSTION CHAMBER OF SUPERSONIC RAMJET ENGINE Russian patent published in 2006 - IPC F02K7/10 

FIELD: aircraft engineering.

SUBSTANCE: proposed method of organization of detonation combustion in ramjet engine of supersonic and/or hypersonic aircraft includes delivery of fuel-air-gas mixture into engine combustion chamber, generation of internal shock waves in passage part of combustion chamber formed by adjustable members of combustion chamber, for instance, system consisting of two symmetrical wedges, detonation combustion of mixture in combustion chamber with subsequent expansion of detonation products in nozzle. System of symmetrical incident shock waves is created in passage part of combustion chamber. Owing to interaction of said waves, in central part of cross section of combustion chamber overcompressed detonation wave -mach stem is formed with possibility of adjustment of its size and location in passage part of combustion chamber where detonation combustion of mixture takes place with formation of high temperature area of detonation products behind. Simultaneously, incident reflected shock waves are formed between Mach stem and walls of chamber without burning process, with temperature of gas mixture after them considerably lower than temperature in area of detonation products. Size of Mach stem and its position in longitudinal direction of combustion chamber and its stationary position are set by changing geometrical parameters of adjusting members of combustion chamber depending on Mach number of flow at inlet of combustion chamber and chemical composition of delivered fuel-air mixture.

EFFECT: simplified design of combustion chamber, and fuel feed system, improved performance characteristics of aircraft.

3 dwg