Turbomachine with annular combustion chamber
Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.
1. A turbomachine with an annular combustion chamber comprising, at an upstream end of said combustion chamber, an annular bottom wall provided with fuel injectors, said combustion chamber having a downstream end attached by flexible annular flanges to radially inner and outer casings, the upstream end of the chamber being connected to at least one of the inner and outer casings by elastically deformable bridges each formed of a curved spring leaf extending circumferentially and distributed about the combustion chamber, said bridges being attached by bolting to one of the inner and outer casings and resting radially on the annular bottom wall or vice versa.
2. The turbomachine as claimed in claim 1 , wherein at least one of the inner and outer casings comprises a boss protruding towards the chamber allowing the radial resting of the bridge.
3. The turbomachine as claimed in claim 1 , wherein certain of the bridges have a closed contour and comprise a substantially flat branch resting radially on the annular bottom wall or on a casing and an opposite branch whose mid-portion is curved in the direction of the first branch, the two branches being connected by U-shaped bent ends.
4. The turbomachine as claimed in claim 3 , wherein the ends of the curved mid-portion comprise orifices for attachment to the inner or outer casing or to the combustion chamber.
5. The turbomachine as claimed in claim 1 , wherein certain bridges have an open contour and comprise a mid-portion curved toward the inside of the bridge with U-shaped or C-shaped bent ends.
6. The turbomachine as claimed in claim 5 , wherein the ends of the curved mid-portion of the spring leaf comprise orifices for attachment to the inner or outer casing or to the combustion chamber.
7. The turbomachine as claimed in claim 5 , wherein the ends of the bridges each comprise at least two substantially parallel, circumferentially oriented feet, applied to a cylindrical surface of a casing or of an annular chamber.
8. The turbomachine as claimed in claim 7 , wherein the end feet of a bridge extend toward one another.
9. The turbomachine as claimed in claim 7 , wherein the end feet are curved in an axial direction.
10. The turbomachine as claimed in claim 7 , wherein certain end feet extend toward the inside of the bridge, the other feet extending toward the outside of the bridge.
11. The turbomachine as claimed in claim 10 , wherein the end feet extending toward the outside of a bridge are nested with the end feet extending toward the outside of an adjacent bridge.
12. The turbomachine as claimed in claim 3 , wherein the bent end of a bridge in contact with the bent end of an adjacent bridge.
13. The turbomachine as claimed in claim 12 , wherein the bent ends in contact comprise matching undulations engaged in one another.
14. The turbomachine as claimed in claim 1 , wherein the bridges are mounted with an initial prestress between at least one of the inner and outer casings and the annular bottom wall.
15. A bridge providing support for an annular combustion chamber of a turbomachine as claimed in claim 1 , wherein the curved spring leaf is formed with an open or closed contour in which attachment orifices are formed.
16. The bridge as claimed in claim 15 , wherein the spring leaf is made of nickel and cobalt alloy.
17. The turbomachine as claimed in claim 1 , wherein said bridges are attached by bolting to the inner and outer casings and rest radially on the annular bottom wall.
18. The turbomachine as claimed in claim 1 , wherein said bridges rest radially on the inner and outer casings and are attached by bolting to the annular bottom wall.
19. The turbomachine as claimed in claim 1 , wherein said bridges have different stiffnesses.
20. The turbomachine as claimed in claim 1 , wherein said flexible annular flanges attaching the downstream end of the combustion chamber to the radially inner and outer casings are sufficiently flexible to allow relative movement between the combustion chamber and the casings.