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US 11,867,076 B2Granted
System for lubricating an aeronautical engine
AssigneeSafran Aircraft Engines
InventorsLoic Pora, Huguette De Wergifosse
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AssigneeSafran Aircraft Engines
InventorsLoic Pora, Huguette De Wergifosse
Estimating the term…
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).
A system for lubricating an aeronautical engine and a reduction gearbox associated with the aeronautical engine, the system comprising a lubricating oil reservoir feeding at least a first oil supply pump supplying a first lubrication circuit of the reduction gearbox opening into at least one lubrication enclosure of the reduction gearbox and in parallel a second lubrication circuit of the aeronautical engine opening into lubrication enclosures of the aeronautical engine, recirculation pumps at the exit of the aeronautical engine and of the reduction gearbox returning the oil to the oil reservoir, wherein the second circuit comprises a variable-section jet pump supplied at least by said at least one first supply pump bypassing the first circuit, a second driven supply pump being integrated into the second circuit downstream of the variable-section jet pump, a part of a flow rate in the first circuit being collected by the variable-section jet pump to supply the second circuit.
An assembly of an electronic control unit and a system for lubricating an aeronautical engine and a reduction gearbox associated with the aeronautical engine, wherein the system is according to any of the preceding claims, the electronic control unit incorporating means for calculating a respective oil flow rate in the second circuit to the aeronautical engine and in the first circuit to the reduction gearbox,
Dependencies are inferred from the claim text.