THREE-COMPONENT LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2015 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: claimed rocket engine comprises turbopump unit with oxidiser pumps and two fuel pumps fitted on turbine shaft and combustion chamber. Combustion chamber has cylindrical part with oxidiser and fuel nozzles and nozzle with propellant main manifold and regenerative cooling system. Turbopump unit and combustion chamber are aligned. Combustion chamber represents a two-zone design. First circular zone comprises circular nozzle unit and top fuel manifold. Second zone comprises central nozzle unit composed of a hollow cylinder provided with axial extra nozzle of second fuel. Turbine is arranged between combustion chamber first and second zones. Said turbine consists of distributor, impeller and straightener having the inner chamber. Central nozzle unit is hollow, its inner chamber being communicated via holes and straightener inner chamber with clearance with second fuel nozzle of regenerative nozzle and combustion chamber second zone. Straightener inner chamber is connected via slotted holes with second zone. Oxidiser pump outlet is communicated via pipeline equipped with oxidiser valves with combustion chamber. First fuel pump outlet is connected via pipeline with top fuel manifold. Second fuel pump outlet is connected via pipeline with the main fuel manifold.

EFFECT: higher specific thrust and reliability.

4 cl, 3 dwg