Patent ID: 6226980
Filing Date: 2001-05-08
Classification: F02K

Abstract:
A liquid-propellant rocket engine with turbine gas afterburning comprising:a combustion chamber, inside which a mixing head for a working mixture is mounted and in which ignition injectors are provided;booster prepumps--a fuel booster pump and an oxidizer booster pump, mounted at an engine inlet;a turbopump unit comprising a turbine, a single-stage oxidizer pump and a two-stage fuel pump, which are made as centrifugal inclined Archimedian screw pumps and inlet main lines of which are connected to said booster prepumps respectively, an outlet of the first stage of the two-stage fuel pump is connected through a throttle sequentially to cooling passages of said chamber and through a start cut-off valve further to the mixing head of said combustion chamber;a gas generator mixing head with injectors of which through an oxidizer start/cut-off valve is connected to an outlet of said oxidizer turbopump unit and through a thrust regulator is connected to an outlet of the second stage of the two-stage fuel pump of said turbopump unit, an outlet of the gas generator is connected to an inlet into said turbine of the turbopump unit, and through a gas feed line is connected to an inlet of said mixing head of the combustion chamber;a programmable start and ignition device made with a starting tank with fuel, the tank being connected through a first check valve to said thrust regulator controlled by an electric drive, a first ampoule with starting fuel, an outlet of which through a start/cut-off valve is connected to injectors of said mixing head of the gas generator, wherein said starting tank is connected through a second check valve, a second ampoule with starting fuel and a jet to ignition injectors of the combustion chamber, and through a fill check valve is connected to a main fuel feed line to an input of the fuel pump.