Abstract: An assembly for a gas turbine includes a hollow central shaft which is guided in rotation by at least one bearing, the assembly further including a device for lubricating said at least one bearing, the device including a hollow lubricant delivery tube which is arranged fixedly in the central shaft and is configured to deliver lubricant to the at least one bearing, the lubricant delivery tube having a first section with a first diameter and a second section with a second diameter which is greater than the first diameter, the second section including a plurality of radial channels connecting the inside of the lubricant delivery tube and leading radially to the outside of the lubricant delivery tube towards a radially inner wall of the central shaft so as to form a lubricant film between said second section of the lubricant delivery tube and said radially inner wall of the central shaft.

Abstract: An assembly for a gas turbine includes a hollow central shaft which is guided in rotation by at least one bearing, the assembly further including a device for lubricating said at least one bearing, the device including a hollow lubricant delivery tube which is arranged fixedly in the central shaft and is configured to deliver lubricant to the at least one bearing, the lubricant delivery tube having a first section with a first diameter and a second section with a second diameter which is greater than the first diameter, the second section including a plurality of radial channels connecting the inside of the lubricant delivery tube and leading radially to the outside of the lubricant delivery tube towards a radially inner wall of the central shaft so as to form a lubricant film between said second section of the lubricant delivery tube and said radially inner wall of the central shaft.

Abstract: Rolling-element bearing for a turbomachine of an aircraft, comprising an inner ring (3) defining a first raceway (112), and an outer ring (4) defining a second raceway (124), characterized in that the bearing has at least one loop circuit (21, 22) for forced recirculation of lubricant, this loop circuit comprising a first recirculation circuit (21) comprising at least one lubricant inlet (1200) located on the second raceway (124), and connected by at least one duct (120, 166) created in the outer ring (4) to at least one lubricant outlet (1661) which discharges into a second recirculation circuit (22) of the loop circuit (21, 22), this second recirculation circuit (22) comprising at least one duct (152, 1134, 1136; 1135, 1136) created in the inner ring (3).

Abstract: Rolling-element bearing for a turbomachine of an aircraft, comprising an inner ring (3) defining a first raceway (112), and an outer ring (4) defining a second raceway (124), characterized in that the bearing has at least one loop circuit (21, 22) for forced recirculation of lubricant, this loop circuit comprising a first recirculation circuit (21) comprising at least one lubricant inlet (1200) located on the second raceway (124), and connected by at least one duct (120, 166) created in the outer ring (4) to at least one lubricant outlet (1661) which discharges into a second recirculation circuit (22) of the loop circuit (21, 22), this second recirculation circuit (22) comprising at least one duct (152, 1134, 1136; 1135, 1136) created in the inner ring (3).