Device for distributing oil from a rolling bearing for an aircraft turbine engine
Device for distributing oil from a rolling bearing ( 8 ) for an aircraft turbine engine, comprising: —a rolling bearing ( 8 ), —a body ( 5 ) for distributing oil, which body is configured to be mounted on a turbine engine shaft ( 4 ), said body comprising: i) a first outer cylindrical surface ( 5 a ) for mounting the inner ring ( 12 ) of the bearing, ii) a ring-shaped scoop ( 11 ) for recovering oil, iii) a ring-shaped track ( 26 ) of a dynamic seal ( 22 ), iv) a circuit ( 7 ) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop ( 11 a ) which supplies a first portion ( 7 x ) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop ( 11 b ) for recovering oil, which scoop supplies a second portion ( 7 y ) of the circuit with a view to lubricating the bearing.
1. An oil distribution device of a rolling bearing for an aircraft turbine engine, comprising:
a rolling bearing comprising two rings, respectively internal and external,
an oil distribution body configured to be mounted on a turbine engine shaft, this body comprising:
i) a first external cylindrical surface for mounting the internal ring of the bearing,
ii) an annular oil recovery scoop,
iii) an annular track of a dynamic seal,
iv) a circuit for lubricating said bearing and cooling the track, this circuit being formed in the body,
wherein the annular scoop constitutes a first scoop which supplies a first portion of said circuit for cooling the track, and in that the body comprises a second annular oil recovery scoop which supplies a second portion of said circuit for lubricating the bearing.
2. The device of claim 1 , wherein the first scoop has a smaller diameter than the second scoop.
3. The device according to claim 1 , wherein the scoops are generally L-shaped in axial cross-section and each comprise a cylindrical portion, one end of which is connected to an annular flange, the cylindrical portions extending around each other and the annular flanges being axially offset from each other.
4. The device according to claim 1 , wherein the first portion of the circuit comprises at least a first channel extending in the body between the first scoop and said track.
5. The device according to claim 1 , wherein the second portion of the circuit comprises at least one second channel extending in the body between the second scoop and ducts for supplying oil to the bearing.
6. The device according to claim 4 , wherein the first portion comprises a second channel of annular shape and in which longitudinal ribs are located, and the second portion comprises independent first longitudinal channels spaced around a longitudinal axis of the body.
7. The device according to claim 1 , wherein the scoops are formed in one piece with the body and its track.
8. The device according to claim 1 , wherein the first scoop is formed in one piece with said track, the second scoop being carried by a nut screwed onto the first scoop.
9. The device according to claim 1 , wherein said body comprises:
claw teeth configured to cooperatively engage with complementary claw teeth of said shaft, and/or
an annular abutment configured to cooperate by axial abutment with a corresponding cylindrical shoulder of said shaft.
10. The device according to claim 8 , wherein said nut bears on the internal ring of the bearing.
11. A turbine engine, comprising at least one device according to claim 1 .