Suspension assembly for a turbine engine

1 . A suspension assembly for a turbine engine, comprising:

a beam configured to be attached to an aircraft pylon, the beam comprising a first portion and a second portion each carrying a half-housing which together define a ball joint housing,

a ball joint nut hingedly engaged to rotate in the ball joint housing,

a cylindrical part configured to be attached to a fixed portion of the turbine engine, hinged in the ball joint housing, and mounted so as to be pivotable about an axis in the ball joint nut, and

a support ring surrounding the two half-housings around an entire circumference, said support ring being provided to perform a safety function in an event of failure of at least one element of the suspension assembly.

2 . The suspension assembly according to claim 1 , wherein the beam extends axially and wherein the two portions of the beam and the two half-housings are symmetrical to each other with respect to a radial plane and are secured to each other by fastening elements arranged on the beam.

3 . The suspension assembly according to claim 2 , wherein the support ring comprises two ring portions which are symmetrical to each other and which bear against each other via ring flanges, said ring flanges being provided for fastening the two ring portions together.

4 . The suspension assembly according to claim 3 , wherein the two ring portions are symmetrical to each other according to the radial plane, the ring flanges being arranged radially internally and radially externally, and wherein each half-housing comprises ball joint housing flanges arranged radially internally and externally, the ring flanges and the ball joint housing flanges being provided for a joint attachment.

5 . The suspension assembly according to claim 3 , further comprising a retaining ring, wherein the ball joint housing is cylindrical and without fastening elements, the retaining ring being arranged on an outer circumference of the ball joint housing, and the support ring being arranged on an outer circumference of the retaining ring, the two ring portions of the support ring being symmetrical to each other according to an axial plane perpendicular to the radial plane, the ring flanges of the two ring portions extending axially in an axial direction.

6 . The suspension assembly according to claim 1 , further comprising a ball joint ring arranged against an inner circumference of the ball joint housing, the ball joint nut being arranged in the ball joint ring.

7 . The suspension assembly according to claim 6 , further comprising a vibration damper arranged radially between the ball joint ring and the inner circumference of the ball joint housing.

8 . The suspension assembly according to claim 1 , wherein the cylindrical part comprises a first half-cylinder and a second half-cylinder which are arranged end-to-end circumferentially, and wherein the first half-cylinder comprises a first half-cylinder flange extending radially to the first half-cylinder and the second half-cylinder comprises a second half-cylinder flange extending radially to the second half-cylinder, the first half-cylinder flange and the second half-cylinder flange respectively comprising a first attachment means and a second attachment means for the independent attachment of each half-cylinder to the fixed portion of the turbine engine.

9 . Aircraft assembly comprising a pylon and a turbine engine, the turbine engine comprising a fixed portion, the aircraft assembly further comprising the suspension assembly according to claim 1 .