Sealing between a combustion chamber and a turbine nozzle in a turbomachine

1. A turbomachine comprising:

an annular combustion chamber;

a sectorized turbine nozzle comprising a plurality of nozzle sectors which are circumferentially arranged end to end, the sectorized turbine nozzle being disposed at an outlet from the chamber; and

sealing means interposed axially between the chamber and the sectorized turbine nozzle,

wherein the sealing means comprises an annular gasket that is axially resilient, the gasket including a first axial bearing means for axially bearing against a downstream end of the chamber and a downstream annular lip that is sectorized into a plurality of sectors such that adjacent sectors of the downstream lip are structurally separated from each other, each sector of the downstream lip being in alignment with a nozzle sector of the sectorized turbine nozzle and including a second axial bearing means for axially bearing against an upstream end of the nozzle sector of the sectorized turbine nozzle.

2. A turbomachine according to claim 1 , wherein the gasket is mounted with cold axial prestress between the chamber and the sectorized turbine nozzle.

3. A turbomachine according to claim 1 , wherein the first axial bearing means for bearing against the chamber includes an upstream annular lip of the gasket.

4. A turbomachine according to claim 3 , wherein the first and second axial bearing means of the lips of the gasket comprise respective annular bearing surfaces of convex rounded shape.

5. A turbomachine according to claim 3 , wherein the first and second axial bearing means of the lips of the gasket are formed at free end portions of the lips.

6. A turbomachine according to claim 3 , wherein the lips of the gasket are connected together by a corrugated portion.

7. A turbomachine according to claim 1 , wherein a downstream lip of the gasket includes a number of sectors that is equal to or greater than a number of nozzle sectors.

8. A turbomachine according to claim 7 , wherein the adjacent sectors of the downstream lip are structurally separated from each other by calibrated through slots in the downstream lip.

9. A turbomachine according to claim 1 , wherein the gasket comprises a single part.

10. A turbomachine according to claim 1 , wherein the gasket presents a section that is V-, W-, WV-, WW-, or Ω-shape.

11. A turbomachine according to claim 1 , wherein the gasket includes radial bearing means for bearing against at least one of the chamber or the nozzle for centering the gasket.

12. A turbomachine according to claim 1 , wherein the gasket includes calibrated orifices for passing ventilation air.

13. A turbomachine according to claim 1 , wherein at least one of the downstream end of the chamber or the upstream end of the nozzle includes air-passing orifices for at least one of feeding air to an annular enclosure in which the gasket is housed or for discharging air from the enclosure.

14. An axially-resilient annular sealing gasket for a turbomachine according to claim 1 , the gasket made as a single part and including two annular lips, one of which includes radial through slots defining, between them, lip sectors that are configured to move freely independently of one another.

15. A gasket according to claim 14 , presenting a section that is V-, W-, WV-, WW-, or Ω-shape.

16. A turbomachine according to claim 1 , wherein the number of sectors of the downstream annular lip is equal to the number of nozzle sectors and presents an angular extent around an axis of the gasket which is substantially equal to an angular extent of the nozzle sector.

17. A turbomachine according to claim 8 , wherein the slots are regularly distributed around an axis of the gasket.

18. A turbomachine according to claim 8 , wherein at least one of the slots extends over about half of a radial dimension of the downstream lip.