Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing

1. A turbojet, comprising:

a fixed structure;

a fan rotor fixed to a drive shaft supported in a first configuration by a first bearing and a second bearing, located downstream from the first bearing in a gas flow direction, and supported in a second configuration by the second bearing; and

means for enabling an axis of the second bearing to be displaced with respect to an axis of the fixed structure of the turbojet in the second configuration, wherein

the first bearing is mounted on the fixed structure of the turbojet through a device that enables the first bearing to be decoupled from the fixed structure, and

the second bearing is mounted on the fixed structure through a bearing support part including a link acting as a ball joint.

2. The turbojet according to claim 1 , wherein

the second bearing includes an outer bearing ring in the bearing support part, and

an outer surface of the outer bearing ring is spherical and matches a spherical internal housing in the bearing support part.

3. The turbojet according to claim 1 , further comprising:

means for enabling radial displacement of the second bearing with respect to the fixed structure of the turbojet in the second configuration.

4. The turbojet according to claim 3 , wherein the means for enabling radial displacement includes shear screws for attachment of the bearing support part to the fixed structure of the turbojet.

5. The turbojet according to claim 1 , wherein

the second bearing includes an inner ring, an outer rings and rollers mounted between the inner ring and the outer ring, and

the inner ring is configured to be longitudinally displaced with respect to the outer ring.

6. The turbojet according to claim 1 , further comprising:

means for forming axial retention of the fan rotor in cooperation with the fixed structure.

7. The turbojet according to claim 6 , further comprising:

a structural flange onto which the second bearing is fixed,

wherein the means for forming axial retention of the fan rotor includes a retaining disk mounted on the drive shaft configured to cooperate with a disk acting as a stop disk for the structural flange for axial retention of the fan rotor arid a longitudinal sleeve of the flange to form a spare bearing.

8. The turbojet according to claim 6 , wherein the means for forming axial retention of the fan rotor is configured to transmit axial forces directly to the drive shaft.

9. The turbojet according to claim 7 , wherein

the second bearing includes an inner ring, an outer ring, and rollers mounted between the inner ring and the outer ring, and

the retaining disk includes radial teeth bearing axially on teeth of the drive shaft and blocked in rotation by longitudinal teeth in the inner ring of the second bearing.

10. The turbojet according to claim 1 , wherein

the drive shaft is a low pressure rotor, and

the second bearing is configured to support the low pressure rotor.

11. A turbojet, comprising:

a fixed structure;

a drive shaft coupled to the fixed structure;

a fan rotor fixed to the drive shaft;

a first bearing configured to couple the fixed structure and the drive shaft; and

a second bearing located downstream from the first bearing in a gas flow direction, the second bearing configured to couple the fixed structure and the drive shaft,

wherein an outer surface of the second bearing is coupled to an inner surface of the fixed structure such that an axis of the second bearing is configured to be displaced with respect to an axis of the fixed structure.

12. The turbojet according to claim 11 , wherein

the fixed structure includes a bearing support part,

the second bearing includes an outer bearing ring, and

an outer surface of the outer bearing ring is spherical and contacts a spherical internal housing in the bearing support part.

13. The turbojet according to claim 12 , wherein

the bearing support part is coupled to another portion of the fixed structure via shear screws, and

the shear screws are configured to enable radial displacement of the second bearing with respect to the fixed structure of the turbojet.

14. The turbojet according to claim 11 , wherein

the second bearing includes an inner ring, an outer ring, and rollers mounted between the inner ring and the outer ring, and

the inner ring is configured to be longitudinally displaced with respect to the outer ring.

15. The turbojet according to claim 11 , wherein the fixed structure includes a sleeve configured to axially retain the fan rotor after the fan rotor is decoupled from the drive shaft.

16. The turbojet according to claim 15 , further comprising:

a retaining disk mounted on the drive shaft,

wherein, after the fan rotor is decoupled, the retaining disk is configured to contact the sleeve to axially retention the fan rotor.

17. The turbojet according to claim 16 , wherein the retaining disk is configured to transmit axial forces directly to the drive shaft.

18. The turbojet according to claim 16 , wherein

the second bearing includes an inner ring, an outer ring, and rollers mounted between the inner ring and the outer ring, and

the retaining disk includes radial teeth bearing axially against teeth of the drive shaft and blocked in rotation by longitudinal teeth in the inner ring of the second bearing.

19. The turbojet according to claim 11 , wherein

the drive shaft is a low pressure rotor, and

the second bearing is configured to support the low pressure rotor.