Suspension rods for the bypass flow duct of a turbojet with eccentric ball joints

1. A device for assembly of a suspension member on a casing of a turbo-engine comprising:

a clevis fixed to the casing and comprising first and second coaxially bored lugs;

a shaft traversing the bores of said lugs to which said suspension member is fixed, in a manner which is mobile in radial rotation;

a ball joint surrounding the shaft and fixing said suspension member to said shaft;

a support ring surrounding said shaft, said support ring including a radial shoulder and first and second longitudinal extensions extending from first and second sides of the radial shoulder of said support ring, respectively, said second side of said radial shoulder of said support ring facing a first side of said second lug; and

a bushing surrounding said shaft, said bushing including a radial shoulder and a longitudinal extension extending from said radial shoulder of said bushing and including a cutout, said radial shoulder facing a second side of said second lug,

wherein said support ring and said bushing are capable of being driven in rotation about an axis of the bores,

wherein said ball joint is fixed at one of the ends of said suspension member, and bored along an axis which is offset relative to an axis of symmetry of a spherical part of said ball joint, the axis of rotation of said support ring and said bushing being merged with the axis of said lugs such that the rotation of said support ring and said bushing about the axis of the bore of the lugs causes an offset of the axis of rotation of the suspension member in a direction perpendicular to said axis of the bores,

wherein said ball joint includes a cutout on a radial face facing said support ring, said first longitudinal extension of said support ring cooperating with said cutout on said radial face to fix in rotation said ball joint with said support ring about the axis of the bore of said lugs, and

wherein said second longitudinal extension of said support ring cooperates with said cutout on said longitudinal extension of said bushing to fix in rotation said support ring with bushing about the axis of the bores of said lugs.

2. The device as claimed in claim 1 , wherein said bushing comprises two parallel flat portions positioned on its circumference, permitting its rotation using a tool about the axis of the bore of said lugs.

3. The device as claimed in claim 1 , wherein the support shaft is hollow and traversed by an assembly consisting of a screw and a nut capable of providing the clamping of the radial shoulders of said bushing and the ring against the second lug of the clevis, so as to block the rotation of the bushing and the ball joint about the axis of the bore of said lugs.

4. The device as claimed in claim 3 , further comprising a washer positioned between the bushing and the nut, said washer comprising two parallel flat portions capable of being positioned opposite flat portions of said bushing.

5. A turbo-engine comprising the device for assembly as claimed in claim 1 .

6. The device as claimed in claim 1 , further comprising a second bushing surrounding said shaft and including a radial shoulder facing a first side of said first lug.

7. The device as claimed in claim 6 , wherein a clearance is provided between said radial shoulder of said second bushing and said first side of said first lug.