Suspension for mounting a turbojet engine on an aircraft

1. An isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the engine axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing, characterized in that the plane formed by the two links of the rear attachment is inclined with respect to a vertical plane of the exhaust casing.

2. The suspension as claimed in claim 1 , wherein the rear attachment comprises a cross member, the two rear attachment links connecting the ends of the member to the outer shell of the exhaust casing.

3. The suspension as claimed in claim 2 , wherein the rear attachment comprises a link for taking up the torque Mx along the engine axis XX, this link being positioned between the two rear attachment links.

4. The suspension as claimed in claim 2 , wherein the two rear attachment links are connected to the exhaust casing by clevis joints whose lugs lie in a plane which is inclined with respect to the vertical plane of the exhaust casing.

5. The suspension as claimed in claim 1 , wherein said plane formed by the two rear attachment links cuts the axis of the turbojet engine XX in the proximity of the center of gravity of the engine.

6. The suspension as claimed in claim 2 , wherein the two thrust bars are fixed at their downstream ends to said cross member.

7. The suspension as claimed in claim 6 , wherein the two thrust bars are connected to the rear attachment by a rocking lever.

8. The suspension as claimed in claim 1 , wherein the downstream ends of the thrust bars are connected to the pylon.

9. The suspension as claimed in claim 8 , wherein the thrust bars and the rear suspension links converge on, or in the proximity of, the engine axis XX at a point of convergence.

10. The suspension as claimed in claim 9 , wherein the point of convergence is located above the height of the engine axis XX and at a distance of less than a quarter of the fan diameter from this axis.

11. The suspension as claimed in claim 1 , wherein the two thrust bars are fixed at their downstream ends to the pylon by the front attachment.

12. The suspension as claimed in claim 11 , wherein the front attachment is connected to the hub of the intermediate casing.

13. The suspension as claimed in claim 11 , wherein the plane of the thrust bars and the plane of the two rear attachment links converge on, or in the proximity of, the engine axis XX at a point of convergence.

14. The suspension as claimed in claim 13 , wherein the point of convergence is located above the height of the engine axis XX and at a distance of less than a quarter of the fan diameter from this axis.

15. The suspension as claimed in claim 1 , wherein the front attachment comprises a cross member and two front attachment links connecting the member to the shell of the intermediate casing.

16. The suspension as claimed in claim 15 , wherein the front attachment comprises a link for taking up the torque Mx along the engine axis XX, this link being positioned between the two front attachment links.

17. The suspension as claimed in either one of claims 15 or 16 , wherein the front attachment has a system for taking up the engine torque Mx along the engine axis XX by means of a link of the boomerang type.

18. A turbojet engine for an aircraft, characterized in that it has a suspension as claimed in any one of claims 1 to 16 .