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 plate nozzle, circular combustion chamber with mixing head arranged axisymmetric inside said nozzle, and fuel and oxidiser feed manifolds. Note here that said combustion chamber has shaped inner wall and is arranged along the chamber lengthwise axis. Said combustion chamber accommodates cooling cylinder with its one end face communicated with mixing head and another communicated with nozzle central part to form circular critical section together with chamber shaped inner wall. In compliance with this invention, combustion chamber inner wall 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. Note also that circular combustion chamber accommodates liquid propellant rocket engine with Laval nozzle, which is arranged axisymmetric behind of mixing head to swing in mutually perpendicular planes. Note that engine nozzle space opens towards plate nozzle space.

EFFECT: higher specific thrust pulse and simplified control over thrust vector.

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