Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber

• US 20070283700A1
• Filed: 06/11/2007
• Published: 12/13/2007
• Est. Priority Date: 06/09/2006
• Status: Active Grant

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: Ebel, Michael, Gerendas, Miklos
• Granted Patent: US 7,926,278 B2
• Time in Patent Office: Days
• US Class Current: 60/754
• CPC Class Codes: F23R 2900/00014 Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators silence apparatus using resonance F01N1/023
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube

Abstract

A gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber with a combustion chamber casing 2, 3 and several combustion chamber segments arranged in the combustion chamber casing 2, 3 and forming a combustion chamber wall 10. Each of the combustion chamber segments is supplied with cooling air with film cooling via axial and/or radial cooling holes 16, 17, with the cooling holes 16, 17 being axially spaced from each other and with dampening openings 19a being provided in this area for the introduction of cooling air.

Claims

1. A gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber, comprising:

a combustion chamber casing;

several combustion chamber segments arranged in the combustion chamber casing and forming a combustion chamber wall, each of the combustion chamber segments being supplied with cooling air with film cooling via at least one of axial cooling holes and radial cooling holes, with the cooling holes being axially spaced from each other; and

dampening openings being provided in the combustion chamber wall for the introduction of air.

2. A gas-turbine combustion chamber wall in accordance with claim 1, wherein each of the combustion chamber elements is annular and conical.

3. A gas-turbine combustion chamber wall in accordance with claim 2, wherein the combustion chamber elements overlap each other in their edge zones.

4. A gas-turbine combustion chamber wall in accordance with claim 3, wherein the combustion chamber segments are arranged closely to a zone of maximum heat release of the gas turbine combustion chamber.

5. A gas-turbine combustion chamber wall in accordance with claim 3, wherein the combustion chamber segments are arranged centrally between burners and turbine inlet vanes.

6. A gas-turbine combustion chamber wall in accordance with claim 5, wherein the combustion chamber segments are of a single-wall design.

7. A gas-turbine combustion chamber wall in accordance with claim 5, wherein the combustion chamber segments are of a double-wall design and at least one include a damper casing arranged radially outward and forming a circumferential dampening volume.

8. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the damper casing is firmly attached to the combustion chamber segment.

9. A gas-turbine combustion chamber wall in accordance with claim 7, wherein one end of the damper casing is firmly attached to the combustion chamber segment and an other end is slideably connected to the combustion chamber segment.

10. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the circumferential dampening volume of the damper casing is subdivided into individual chambers.

11. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the circumferential dampening volume of the damper casing is at least partly filled with air-permeable material.

12. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of metal.

13. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of ceramics.

14. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of CMC.

15. A gas-turbine combustion chamber wall in accordance with claim 1, and further comprising effusion cooling holes arranged between the dampening openings, which essentially extend perpendicularly through the combustion chamber wall, with the effusion cooling holes being oriented at a shallow angle to a surface of the combustion chamber wall.

16. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber elements overlap each other in their edge zones.

17. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are arranged closely to a zone of maximum heat release of the gas turbine combustion chamber.

18. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are of a single-wall design.

19. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are of a double-wall design and at least one include a damper casing arranged radially outward and forming a circumferential dampening volume.

20. A gas-turbine combustion chamber wall in accordance with claim 19, wherein one end of the damper casing is firmly attached to the combustion chamber segment and an other end is slideably connected to the combustion chamber segment.