Turbomachine fan assembly comprising a roller bearing and a double-row ball bearing with oblique contact
AssigneeSafran Aircraft Engines
InventorsFrançois Marie Paul Marlin, Didier Gabriel Bertrand Desombre, Christophe Paul Jacquemard, Laurent Paul François Perrot
Life of this patent
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Abstract
An aircraft propulsion assembly including a fan shaft which is connected to a turbine shaft by means of a reduction gear. The guiding of the fan shaft is carried out by a first bearing including cylindrical rollers and a second beating including two rows of balls with oblique contact.
Claims8
A fan assembly for an aircraft turbomachine, the assembly comprising a fan shaft and first and second bearings configured to guide the fan shaft in rotation about a central axis, wherein the first bearing has cylindrical rollers and the second bearing has a double-row of balls with oblique contact,
- wherein the second bearing comprises first and second rows of balls, and an inner ring and an outer ring each comprising first and second races, the first race of the inner and outer rings receiving the first row of balls, the second race of the inner and outer rings receiving the second row of balls, and
- wherein the fan shaft comprises a first support portion carrying an inner ring of the first bearing, a second support portion carrying an inner ring of the second bearing, a first frustoconical junction portion connecting together the first and second support portions, and a second frustoconical junction portion intended to connect together the second support portion and a reduction gear of the turbomachine, said second support portion having a thickness taken perpendicular to a longitudinal extent thereof that is larger than a thickness of the first frustoconical junction portion taken perpendicular to a longitudinal extent thereof and a thickness of the second frustoconical junction portion taken perpendicular to a longitudinal extent thereof.
Dependencies are inferred from the claim text.