LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engine production and can be used in development of generatorless liquid propellant engines running on cryogenic components, for example oxygen and hydrogen. Liquid propellant engine comprises circular chamber with mixing head, external expansion plate nozzle, shaped central body and circular critical section, gas generator, control and feed units comprising turbopump unit with turbine and fuel component feed pumps arranged in said shaped central body chamber. In compliance with this invention, said shaped central body consists of several parts. Note here that at least one said part is made to effect radial axisymmetric revolution around shaped central body lengthwise axis and is articulated with feed units. Blades are arranged on its outer surface for aforesaid part to rotate. Note also that outlet zone of fixed part, adjoining movable part, has channels communicated with fuel feed system and open to fixed part shaped surface.

EFFECT: higher specific thrust pulse, simplified pneumohydraulic circuit and increased chamber pressure at minimum overall dimensions.

1 dwg