LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2013 - IPC F02K9/52 F02K9/95 

FIELD: engines and pumps.

SUBSTANCE: proposed chamber comprises mixing head including casing, oxidiser feed unit, propellant feed unit, fire bottom, starting fuel feed channel with outlet composed of hollow shaped sleeve. Atomisers are arranged at mixing head units in concentric circles to communicate unit chambers with combustion chamber. Starting fuel feed channel outlet accommodated coaxial hollow spring-loaded axial-displacement sleeve with sealing surface made at its channel inlet. In on position, said extra sleeve interacts with outlet with mating shaped surface on fire bottom inner surface. In another position, its inlet sealing surface interacts with mating sealing element arranged in starting fuel channel.

EFFECT: higher and reliability of ignition system.

5 dwg