Device for centering and guiding a shaft of an aircraft turbine engine
A device for centering and guiding a shaft of an aircraft turbine engines. The device includes an outer ring of a rolling bearing, the ring extending about a main axis and having orifices arranged around the axis axis; an annular bearing support extending about the main axis and at least partially about the ring, the support having orifices and openings arranged about the axis; and a series of studs for linking the ring to the support, the studs being distributed about the main axis and having elongation axes substantially parallel to the main axis, the body of each of the studs passing through one of the openings. Some of the studs, have bodies that pass with a first positive clearance and a second virtually zero clearance through the first openings, the first and second clearances being configured so that the device has different displacement amplitudes.
1. A device for centering and guiding an aircraft turbine engine shaft, this device comprising:
an outer ring of a rolling bearing, this ring extending about a main axis and comprising orifices arranged about this axis and oriented parallel to this axis,
an annular bearing support extending around the main axis and at least partly around the ring, this support comprising orifices and openings arranged around this axis and oriented parallel to this axis, and
a series of studs for connecting the ring to the support, these studs being distributed around the main axis and having axes of elongation substantially parallel to the main axis, each of these studs comprising a body comprising a first longitudinal end engaged in one of the orifices of the ring and a second longitudinal end engaged in one of the orifices of the support, the body of each of said studs passing through one of the openings of the support,
wherein some of said studs, referred to as first studs, have their bodies passing through first openings with a first positive clearance and a second clearance of almost zero, said first clearance being oriented in at least a first direction radial with respect to said axis of elongation, and said second clearance being oriented in at least one second direction radial with respect to said axis of elongation, different from the first direction, said first and second clearances being configured so that the device has different amplitudes of displacement in at least two directions perpendicular to said main axis.
2. The device according to claim 1 , wherein said first and second directions are perpendicular to each other.
3. The device according to claim 1 , wherein said first direction and said second direction are oriented tangentially or normally with respect to a circumference centred on said main axis.
4. The device according to claim 1 , wherein other studs, referred to as second studs, have their bodies passing through second openings with a third clearance oriented in the second direction, said third clearance being different from, preferably substantially greater than, the first and second clearances of the first studs in the first openings.
5. The device according to claim 4 , wherein said first studs alternate with said second studs around said axis.
6. The device according to claim 4 , wherein the first openings are oblong or elliptical in cross-section and the second openings are circular in cross-section.
7. The device according to the preceding claim 6 , wherein said first openings are oriented so that they have an elongated shape in the same direction.
8. The device according to claim 1 , wherein said bodies are generally cylindrical in cross-section.
9. The device according to claim 1 , wherein the openings are provided in an annular wall of the support.
10. The device according to claim 1 , wherein the outer ring comprises an outer cylindrical surface defining with an inner cylindrical surface of the support an annular space for forming a damping oil film.
11. An aircraft turbine engine, comprising at least one device according to claim 1 .