HYDROGEN-OXYGEN LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises combustion chamber, system of nozzle regenerative cooling by propellant, and two turbo pump units. Besides, it has oxidiser and propellant turbo pump units. Note here that all turbo pumps units have main turbine and pumps. Additionally, it comprises, at least, one extra propellant turbo pump unit. Pumps of all turbo pump units are connected in series by "П"-like and straight pipelines. Main turbines of propellant turbo pump units are also connected in series. Note also that oxidiser and propellant turbo pump units have gas generators integrated therewith. Combustion chamber may have head, cylindrical part, nozzle, three top manifolds atop nozzle and one bottom manifold at nozzle bottom. Oxidiser turbo pump unit first main turbine outlet is communicated via gas duct with combustion chamber head while propellant pump outlet is communicated with propellant turbo pump unit propellant pump inlet. Propellant pump outlet of the last extra propellant turbo pump unit is communicated with bottom manifold. Third top manifold outlet is communicated with propellant gas generator while outlet of second main turbine of propellant turbo pump unit is communicated with third main turbine inlet. Outlet of the last turbo pump unit main turbine is communicated with first top manifold. Proposed engine may be equipped with onboard computer while igniters may be arranged on combustion chamber and gas generators electrically connected with said computer. Engine may also include central hinge arranged on second propellant pipeline on combustion chamber longitudinal axis. Said hinge may be either cylindrical or spherical. All turbo pumps units incorporate shafts and rpm transducers and axial force transducers.

EFFECT: increased pressure in combustion chamber, higher reliability.

7 cl, 18 dwg