LIQUID-PROPELLANT ROCKET ENGINE TURBO PUMP UNIT HYDROSTATIC BEARING PNEUMOHYDRAULIC FEED SYSTEM Russian patent published in 2008 - IPC F02K9/48 F01D25/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to control and adjustment systems of liquid-propellant rocket engines, to be exact, to subsystems incorporated with the said systems and designed to control separate elements of the liquid-propellant rocket engine. The aforesaid feed system controls the turbo pump unit made up of a turbine, one or two pumps incorporating plain bearings, primarily, hydrostatic bearings with their inlets communicating hydraulically with high-pressure spaces and outlets communicating with low-pressure spaces of the aforesaid pumps, the bearings being lubricated by fuel components pumped over by the said pumps. Note, that the bearings of every pump communicate additionally via a valve train incorporating a pressurised fuel components feed devices allowing the bearings to run in starting up and shutting down. Note, also, that the pressurised fuel component devices are filled at a time with priming the pumps.

EFFECT: longer life of the turbo pump unit.

3 cl, 1 dwg