Sealing device for a turbomachine turbine nozzle

Patent metadata

Field	Value
Publication number	US-9631557-B2
Application number	US-201214115014-A
Country	US
Kind code	B2
Filing date	May 4, 2012
Priority date	May 4, 2011
Publication date	Apr 25, 2017
Grant date	Apr 25, 2017

Abstract

A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.

First claim

The invention claimed is:

1. A sealing device for a nozzle of a turbomachine turbine comprising a turbine rotor, said turbine nozzle comprising at least one inner annular platform, said turbine rotor comprising a downstream spoiler disposed substantially axially, said sealing device comprising:
at least one sealing sheet disposed, radially, between the inner platform and the downstream spoiler of the rotor of the turbine,
wherein the downstream spoiler of the rotor axially overlaps the inner platform,
wherein the axial clearance between the sealing sheet and the turbine rotor is less than the axial clearance between the inner platform and the turbine rotor, such that the sealing sheet is crushed by the turbine rotor in the event of contact, and
wherein the sealing sheet extends below a lower portion of the downstream spoiler.

2. The sealing device according to claim 1 , wherein the sealing sheet axially overlaps the downstream spoiler of the rotor, said overlap of the downstream spoiler by the sealing sheet being greater than or equal to the overlap of the downstream spoiler by the inner platform.

3. The sealing device according to claim 1 , wherein the sealing sheet is a pre-cambered sheet so as to control the crushing of the sealing sheet in the event of contact with the turbine rotor.

4. The sealing device according to claim 1 , wherein the sealing sheet is fixed to the nozzle at at least one point.

5. The sealing device according to claim 1 , wherein said device further comprises a cut-off element disposed substantially perpendicular to the downstream spoiler and arranged to reduce the air flow path surface under the lower portion of the downstream spoiler.

6. The sealing device according to claim 1 , wherein the sealing sheet comprises an annular element.

7. The sealing device according to claim 6 , wherein the annular element further comprises slots distributed over the circumference of said annular element and perforations at the end of the slots so as to prevent propagation of the slots during operation of the turbine.

8. The sealing device according to claim 1 , wherein the sealing sheet comprises a plurality of sectorised elements.

9. The sealing device according to claim 8 , wherein the sectorised elements are connected in pairs by an intersector sheet or by overlap along a sectorisation line.

10. The sealing device according to claim 1 , wherein the inner platform includes a radial wall extending inwards and connected to a cylindrical support ring, and the sealing sheet is mounted on an upstream face of the radial wall.

11. The sealing device according to claim 1 , wherein the sealing sheet is mounted on an inner surface of the inner platform.

12. The sealing device according to claim 1 , wherein a portion of the sealing sheet below the lower portion of the downstream spoiler also axially overlaps the downstream spoiler.

13. A turbomachine turbine, comprising:
at least one turbine nozzle and at least one turbine rotor, said turbine nozzle comprising at least one inner annular platform, said turbine rotor comprising at least one downstream spoiler disposed substantially axially, said turbine comprising a sealing device that includes at least one sealing sheet disposed, radially, between the inner platform and the downstream spoiler of the rotor of the turbine,
wherein the downstream spoiler of the rotor axially overlaps the inner platform,
wherein the axial clearance between the sealing sheet and the turbine rotor is less than the axial clearance between the inner platform and the turbine rotor, such that the sealing sheet is crushed by the turbine rotor in the event of contact, and
wherein the sealing sheet extends below a lower portion of the downstream spoiler.

14. The turbomachine turbine according to claim 13 , wherein the sealing sheet axially overlaps the downstream spoiler of the rotor, said overlap of the downstream spoiler by the sealing sheet being greater than or equal to the overlap of the downstream spoiler by the inner platform.

15. The turbomachine turbine according to claim 13 , wherein the inner platform includes a radial wall extending inwards and connected to a cylindrical support ring, and the sealing sheet is mounted on an upstream face of the radial wall.

16. The turbomachine turbine according to claim 13 , wherein the sealing sheet is mounted on an inner surface of the inner platform.

17. The turbomachine turbine according to claim 13 , wherein a portion of the sealing sheet below the lower portion of the downstream spoiler also axially overlaps the downstream spoiler.

Assignees

• Luneau Florent Pierre Antoine
• Girard Patrick Joseph Marie
• Prestel Sebastien Jean Laurent
• Soupizon Jean-Luc
• Snecma

Inventors

• Luneau Florent Pierre Antoine
• Girard Patrick Joseph Marie
• Prestel Sebastien Jean Laurent
• Soupizon Jean-Luc

Classifications

• F01D21/08

  Restoring position · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title