LIQUID PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2007 - IPC F02K9/46 

FIELD: rocketry; engines.

SUBSTANCE: invention relates to liquid propellant rocket engine operating according to generatorless circuit. Liquid propellant rocket engine contains chamber, turbopump set to deliver propellant components (fuel and oxidizer) into mixing head of combustion chamber, control and regulation sets, and pipelines. According to invention, engine of first design version is furnished additionally with turbopump set to deliver third auxiliary component. Outlet space of pump is connected with cooling chamber duct, output of cooling duct is connected with blade space of turbines of auxiliary and main turbopump set, and through special nozzles with ambient medium or supersonic part of nozzle to create additional thrust. According to second design version, working medium of auxiliary component is directed into space of mixing head of combustion chamber. According to third design version, before-turbine part of auxiliary component, after getting out of duct of cooling chamber, is connected through restrictor with combustion chamber, and other part is directed through special nozzle into ambient medium or into supersonic part of nozzle of main chamber. Invention provides engine operating on hydrocarbon fuel with high value of specific thrust impulse (close of that of engine with after burning of generator gas).

EFFECT: preservation of simple design, low mass characteristics and provision of high reliability.

12 cl, 3 dwg