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

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises annular chamber with mixing head including case, oxidiser feed unit, fuel feed unit, nozzles made up of several inclined sleeves to form annular chambers for feeding gas fuel and liquid oxidiser arranged in mixing head along concentric circles to communicate chambers of said units with combustion chamber, plate nozzle of external expansion, shaped center body with annular critical throat, control units and supply units including turbo pump unit with turbine arranged inside said shaped center body. Shaped center body consists of several parts. Note here that one part of shaped center body may make radial axially symmetric rotation about lengthwise axis of said body and is articulated with feed units. Vanes are arranged on its outer surface to facilitate its rotation. 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 oxidiser annular chambers formed by said coaxially arranged sleeves.

EFFECT: higher specific thrust pulse, simplified design.

3 dwg