FUEL NOZZLE OF LIQUID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2004 - IPC

FIELD: rocketry.

SUBSTANCE: proposed fuel nozzle of combustion chamber of liquid propellant rocket engine includes tubular housing and blind tube coaxially secured inside housing. At least one inlet hole is made in pylon. Channel of blind tube is formed from side of its outlet by blind axial channel, and from side of inlet, by inlet hole in pylon. Main axial channel of tubular housing from outlet side can be made with stepped widening to which through holes made tangentially relative to nozzle axis are directed. Branch pipe can be made inside tubular housing in place of stepped widening coaxially between tubular housing and blind tube. Ring end face pocket can be formed between branch pipe and tubular housing pointed by its open side to housing outlet. From side of outlet, said fuel nozzle can be furnished with head and between said head and tubular housing head regenerative cooling duct is made. Duct outlet is located on outlet end of nozzle and inlet, on opposite end of head. Channel of blind tube from side of inlet is separated from head regenerative cooling duct.

EFFECT: provision of effective preparation of mixture in combustion chambers of liquid propellant rocket engines, reduced length of fire space of combustion chamber without reducing specific thrust pulse.

10 cl, 13 dwg