LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2001 - IPC

FIELD: aeronautical engineering. SUBSTANCE: liquid-propellant rocket engine has combustion chamber with nozzle provided with regenerative cooling passage, oxidizer pump and fuel pump with service oxidizer and fuel mains which are connected with drive turbine. Gas generator inlet is connected to service oxidizer main and is communicated with service fuel main through intermediate line; service fuel line is connected to combustion chamber through regenerative cooling passage. Gas generator outlet is connected with drive turbine inlet whose outlet is connected to combustion chamber through gas duct. Engine is provided with hermetic reservoir having hermetic cavities separated by flexible diaphragm; one cavity contains starting fuel and is connected to igniter injector through shut-off valve; it is connected to gas generator inlet via starting fuel supply line with normally open check valve and shut-off valve fitted in it in succession; other cavity of reservoir is communicated with high-pressure gas source via shut-off valve. Shut-off valve with vent is fitted in oxidizer main before gas generator. Laval nozzle is fitted in gas duct between turbine and combustion chamber. Venturi tube and shut-off vent valve are mounted in regenerative cooling line of nozzle and combustion chamber in way of flow of fuel. Intermediate line supplying fuel to gas generator is connected to starting fuel supply line via normally closed check valve. EFFECT: possibility of performing multiple start of engine working on highly- effective and ecologically pure non-hypergolic propellant: enhanced operational reliability of gas generator and turbo-pump unit in nominal mode irrespective of change in pressure in combustion chamber; enhanced reliability of engine in case of untightness of combustion chamber. 1 dwg