AIRCRAFT TURBOMACHINE COMPRISING A DEVICE FOR LUBRICATING A BEARING

The invention relates to a turbomachine for an aircraft, comprising:a first rotor comprising a first shaft,a second rotor comprising a second shaft,a mechanical reduction gearing having an epicyclic gear set comprising a sun gear connected to the second shaft, a ring gear connected to the first shaft, and planet gears located between the sun gear and the ring gear and borne by a planet carrier attached to a stator of the turbomachine,rolling element bearings for guiding said first shaft and second shaft in rotation,an annular gutter which extends around the ring gear of the reduction gearing and which is configured to recover oil for lubricating the reduction gearing that is sprayed by centrifugal action out from the ring gear during operation, andan annular bearing support which is attached, with the gutter, to a stator of the turbomachine and which supports at least one of said bearings, characterized in that it also comprises:at least one device for conveying oil recovered by said gutter, which device is borne by said annular support and extends as far as said at least one bearing in order to lubricate the latter.