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

FIELD: engines and pumps.

SUBSTANCE: invention relates to liquid propellant rocket engines. Proposed engine comprises chamber with mixing head accommodating injectors made up of several coaxially arranged sleeved to make annular chambers for feeding gas fuel and liquid oxidiser and communicating fuel component feed units with combustion chamber. Engine comprises also gas generator, turbo pump unit, feed and adjustment assemblies. 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. All aforesaid sleeves are arranged closely to each other on the side opposite combustion zone. Note here that sleeve face walls are provided with channels to communicated oxidiser chamber with oxidizer annular chambers formed by said coaxially arranged sleeves.

EFFECT: higher completeness of fuel combustion.

3 dwg