System for lubricating an aeronautical engine

The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at leas...

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Bibliographische Detailangaben
Hauptverfasser:	De Wergifosse, Huguette, Pora, Loic
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CRANKCASE VENTILATING ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING LIGHTING LUBRICATING INTERNAL COMBUSTION ENGINES LUBRICATING OF MACHINES OR ENGINES IN GENERAL MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).