LIQUID-PROPELLANT ROCKET ENGINE CHAMBER Russian patent published in 2012 - IPC F02K9/62 F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: proposed chamber has mixing head including case, oxidiser feed unit, fuel feed unit, nozzles made up of several coaxial sleeves that make annular cavities for feeding gas fuel and oxidiser. Nozzles are arranged in mixing head along concentric circles to connect inner spaces of units with combustion chamber inner space. Annular ledge is made on every said sleeve with grooves perpendicular to mixing element axis to feed fuel inside annular fuel chamber and parallel grooves to feed oxidiser in annular oxidiser chamber. Fuel feed annular chambers are closed by spacer plates on combustion chamber side. Said space plates have openings to feed fuel into combustion chamber. Sleeve face walls are provided with channels communicating oxidiser chamber with oxidiser annular chambers formed by sleeves arranged coaxially.

EFFECT: higher completeness of fuel combustion.

3 dwg