LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2015 - IPC F02K9/48 F02K9/95 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises control system with on-board computer, turbo pump unit and gas generator connected via gas duct with chamber and igniters at combustion chamber and gas generator. Spark plugs are arranged at combustion chamber and gas generator. Electrical generator is fitted on turbo pump unit shaft. Activator of gas generating mix is arranged inside aforesaid gas duct. Compressed air cylinder is connected to starting turbine. Gas generating mix activator can include two electrodes connected by HV conductors with HV unit connected with electrical generator. This engine can comprise central swivel made at gas duct on chamber axis. Central swivel can be shaped to cylinder. Central swivel can be shaped to sphere. This engine can incorporate turbo pump unit shaft rpm transducer connected with on-board computer.

EFFECT: higher specific thrust and reiterated starting.

11 cl, 17 dwg