Aircraft turbomachine comprising a device for lubricating a bearing

A turbomachine for an aircraft, comprising:

• a first rotor comprising a first shaft,
• a second rotor comprising a second shaft,
• a mechanical epicyclic reduction gear 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 carried by a planet carrier,
• rolling bearings for guiding in rotation said first and second shafts,
• an annular gutter which extends around the ring gear of the reduction gear and which is configured to recover for lubricating the reduction gear which is sprayed by centrifugal action out of the ring gear during operation, and
• an annular bearing support which is fixed with the gutter to a stator of the turbomachine or to another stator of the turbomachine and which supports at least one of said bearings,
• wherein the turbomachine further comprises:
• at least one device for conveying the oil recovered by said gutter, which is carried by said annular support and which extends to said at least one bearing with a view to lubricating the at least one bearing,
• the conveying device comprising:
• a scoop configured to take up the oil recovered by the gutter, the scoop being provided in an annular side wall of the gutter, and
• at least one pipe for conveying the oil taken up by the scoop to said at least one bearing, the pipe extending between a first end connected to the gutter and a second end extending to the bearing.