Suspension assembly for a turbine engine

1. A suspension system for a turbomachine, comprising a beam intended to be attached to a pylon of an aircraft, and a cylindrical part articulated on a ball joint housing, the ball joint housing comprising a body and a ball joint nut articulated on the body, the cylindrical part being mounted so as to pivot about its axis in the ball joint nut, characterized in that the cylindrical part is intended to be integral with a fixed part of the turbomachine, the body of the ball joint housing being integral with the beam.

2. A system according to claim 1 , characterized in that the cylindrical part is mounted, at least in part, in a housing of the body, a clearance being provided between the said cylindrical part and the body.

3. A system according to claim 1 , characterized in that it comprises a connecting element mounted in the body and mounted with clearance in the cylindrical part, the said clearance being permitted in particular according to the direction of the axis of the cylindrical part.

4. A system according to claim 2 , characterized in that it comprises a connecting element mounted in the body and mounted with clearance in the cylindrical part, the said clearance being permitted in particular according to the direction of the axis of the cylindrical part.

5. A system according to claim 1 , characterized in that the beam comprises an upstream part at which the ball joint housing is located, and a downstream part used for attaching a spreader bar intended to support force-recovery rods.

6. A system according to claim 2 , characterized in that the beam comprises an upstream part at which the ball joint housing is located, and a downstream part used for attaching a spreader bar intended to support force-recovery rods.

7. A system according to claim 3 , characterized in that the beam comprises an upstream part at which the ball joint housing is located, and a downstream part used for attaching a spreader bar intended to support force-recovery rods.

8. A system according to claim 1 , characterized in that the cylindrical part comprises a collar, the said collar being intended to be attached to the fixed part of the turbomachine.

9. A system according to claim 2 , characterized in that the cylindrical part comprises a collar, the said collar being intended to be attached to the fixed part of the turbomachine.

10. A system according to claim 3 , characterized in that the cylindrical part comprises a collar, the said collar being intended to be attached to the fixed part of the turbomachine.

11. A system according to claim 5 , characterized in that the cylindrical part comprises a collar, the said collar being intended to be attached to the fixed part of the turbomachine.

12. A system according to claim 8 , characterized in that the cylindrical part comprises at least one recessed area intended to be located opposite a screw, the said recessed area being arranged downstream of the collar.

13. A system according to claim 8 , characterised in that the cylindrical part has a cylindrical upstream end located upstream of the collar.

14. A system according to claim 12 , characterised in that the cylindrical part has a cylindrical upstream end located upstream of the collar.

15. A double-flow turbojet comprising a flow vein of a primary flow, known as the primary vein, delimited by a radially internal wall and a radially external wall, and a flow vein of a secondary flow, known as the secondary vein, surrounding the primary vein and delimited by a radially internal wall and a radially external wall characterised in that it comprises a suspension system according to claim 11 , and in that the cylindrical part is attached to a fixed part of the turbojet, situated radially between the internal wall of the secondary vein and the external wall of the primary vein, the said fixed part being integral with at least one of the said walls.

16. A double-flow turbojet comprising a flow vein of a primary flow, known as the primary vein, delimited by a radially internal wall and a radially external wall, and a flow vein of a secondary flow, known as the secondary vein, surrounding the primary vein and delimited by a radially internal wall and a radially external wall characterised in that it comprises a suspension system according to claim 2 , and in that the cylindrical part is attached to a fixed part of the turbojet, situated radially between the internal wall of the secondary vein and the external wall of the primary vein, the said fixed part being integral with at least one of the said walls.

17. A double-flow turbojet comprising a flow vein of a primary flow, known as the primary vein, delimited by a radially internal wall and a radially external wall, and a flow vein of a secondary flow, known as the secondary vein, surrounding the primary vein and delimited by a radially internal wall and a radially external wall characterised in that it comprises a suspension system according to claim 3 , and in that the cylindrical part is attached to a fixed part of the turbojet, situated radially between the internal wall of the secondary vein and the external wall of the primary vein, the said fixed part being integral with at least one of the said walls.

18. A turbojet according to claim 15 , characterised in that the secondary vein comprises at least one arm extending radially between the internal and external walls of the secondary vein, the said arm being situated downstream of a fan of the turbojet, the fixed part to which the said cylindrical part is attached being situated axially opposite the arm.

19. A turbojet according to claim 15 , characterised in that the dilution ratio of the said turbojet is greater than 10.

20. A turbojet according to claim 18 , characterised in that the dilution ratio of the said turbojet is greater than 10.