Device for attaching a combustion chamber

1. A turbomachine comprising an annular combustion chamber comprising:

a radially inner wall and a radially outer wall exhibiting symmetry of revolution with respect to the axis of the turbomachine;

an annular chamber end wall connected at upstream ends of the inner wall and the outer wall and equipped with fuel-injection means; and

a suspension device which suspends the upstream end of the combustion chamber from an outer casing,

wherein the suspension device includes at least one link rod articulated at a first end to the outer wall of the combustion chamber and at a second end to the outer casing, the first end of the link rod is articulated about a transverse axis on a first cylindrical pin mounted in a holes in a pair of clevises provided on the outer wall of the chamber and the second end of the link rod is articulated about the transverse axis on a second cylindrical pin mounted in holes provided in the outer casing, and

the downstream end of the combustion chamber is connected to an inner casing or outer casing by flexible connections or mounts.

2. The turbomachine as claimed in claim 1 , wherein the link rod lies in a plane that passes through the axis of the turbomachine.

3. The turbomachine as claimed in claim 1 , wherein the first end of the link rod is articulated to the upstream end of the outer wall of revolution and the second end is housed and articulated in an outwardly projecting boss belonging to the outer casing.

4. The turbomachine as claimed in claim 3 , wherein the boss includes a flat part and a head of the second cylindrical pin includes a flat which engages with the flat part.

5. The turbomachine as claimed in claim 1 , wherein guide bushings are set into the holes in the clevises.

6. The turbomachine as claimed in claim 1 , wherein the ends of the link rod are articulated on the cylindrical pins by ball swivels through which these pins pass.

7. The turbomachine as claimed in claim 1 , and which comprises three link rods distributed over the upper half-circumference of the outer wall of the chamber, one link rod lying in a vertical plane that passes through the axis of the turbomachine, the other two link rods being positioned symmetrically on each side of this vertical plane.

8. The turbomachine as claimed in claim 1 , wherein the link rod or each link rod is substantially parallel to the axis of the turbomachine.

9. The turbomachine as claimed in claim 1 , wherein the link rod or each link rod comprises means for adjusting length.

10. The turbomachine as claimed in claim 1 , wherein the link rod or each link rod is connected to the outer wall of the chamber between fuel injectors.

11. The turbomachine as claimed in claim 1 , wherein at least one of the walls that are the outer wall and the inner wall of the chamber comprises at its downstream end a flexible piece for connecting to or resting against an outer or inner casing.

12. The turbomachine as claimed in claim 11 , wherein the flexible connecting piece is welded or brazed to the chamber and rests substantially radially against a casing.

13. The turbomachine as claimed in claim 1 , wherein the downstream end of the inner wall of the chamber is connected by a flexible annular flange to an inner casing.

14. The turbomachine as claimed in claim 1 , wherein the annular combustion chamber is convergent and mounted from the upstream end inside the outer casing.

15. The turbomachine as claimed in claim 1 , wherein a radially inner part of each clevis includes a flat-surfaced rim and a head of the first cylindrical pin includes a flat which collaborates with the rim to prevent rotation of the first cylindrical pin.