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US 9,752,575 B2Granted
Two stage pump, particularly provided as main pump for supplying an aircraft engine with fuel
AssigneeSnecma
InventorPhilippe Vertenoeuil
Life of this patent
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AssigneeSnecma
InventorPhilippe Vertenoeuil
Estimating the term…
A two stage pump (2′, 4′), where the high pressure stage (4′) is a gear pump (11, 12), comprises a driving of the other stage (2′) by a support shaft (74), mounted in the driven pinion (12), the shaft (74) being driven by the drive shaft (21), by means of a pair of toothed wheels (77, 79) adjacent to the rest of the stage (4′), which can allow different rotation speeds between the two stages (2′, 4′). The support shaft (74) may be supported by stops and hydrodynamic bearings, directly integrated and lubricated in the driven pinion, which make the design lighter and more compact. The shaft (74) and the toothed wheels (77, 79) ingeniously transmit the loads from the stage (2′) to the stage (4′) in such a way as to cancel out the usual hydraulic loads, stemming from pressure, and mechanical, forces stemming from rotational drivings on the driven pinion (12).
Two stage pump including a first pump having a rotating pumping element driven by a support shaft, a second pump including two pumping pinions meshing together, the two pumping pinions including a driving pinion and a driven pinion, a drive shaft of the driving pinion extending along a longitudinal axis, and a transmission connecting the driving pinion to the support shaft, the transmission being contained in the second pump, the support shaft being coaxial to the driven pinion, wherein the support shaft is partially contained in a reaming passing through the driven pinion, and in that it comprises a first bearing supporting the support shaft in the reaming, formed between the support shaft and the driven pinion.
Dependencies are inferred from the claim text.