Gas-turbine combustion chamber wall

• US 8,099,961 B2
• Filed: 04/17/2008
• Issued: 01/24/2012
• Est. Priority Date: 04/17/2007
• Status: Expired due to Fees

• 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: Gerendas, Miklos
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Kim, Craig
• Application Number:
  US12/081,573
• Publication Number:
  US 20080264065A1
• Time in Patent Office: 1,377 Days
• Field of Search: 60752-760
• US Class Current: 60/752
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components

Abstract

A gas-turbine combustion chamber wall for a gas-turbine has a combustion chamber wall 9, on the inner side of which several tiles 10 are arranged, with an interspace 14 being formed between the tiles 10 and the combustion chamber wall 9, into which cooling air is introduced via impingement-cooling holes 8 provided in the combustion chamber wall 9 and from which the cooling air flows into the combustion chamber via effusion-cooling holes 11, 23 provided in the tile 10. The tile 10 includes a surface structure 19, 22 on the side facing the combustion chamber wall 9. The area of the impingement-cooling holes 8 and the area of the effusion-cooling holes 11 do not coincide.

Claims

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

a combustion chamber wall;

a plurality of tiles arranged on an inner side of the combustion chamber wall, with an interspace being formed between the tiles and the combustion chamber wall;

impingement-cooling holes provided in the combustion chamber wall for introducing cooling air into the interspace;

effusion-cooling holes provided in the tiles through which cooling air from the interspace flows into a combustion chamber;

wherein the tiles include a surface structure on a side facing the combustion chamber wall;

wherein an area provided with the impingement-cooling holes, an area provided with the surface structure and an area provided with effusion-cooling holes are offset relative to each other in an axial direction of the combustion chamber such that there are four regions progressing in consecutive numeric order in the axial direction in a direction of combustion gas flow from first to fourth, each region having an axial extent and an inward/outward extent that encompasses both the combustion chamber wall and the inwardly arranged tiles along the axial extent, the four regions being a first region of only impingement cooling holes, a second region of overlap of impingement cooling holes and the surface structure, a third region of overlap of effusion cooling holes and the surface structure and a fourth region of only effusion cooling holes.

2. The gas-turbine combustion chamber wall of claim 1, wherein the offset is also provided in a circumferential direction.

3. The gas-turbine combustion chamber wall of claim 1, wherein the surface structure comprises at least one rib.

4. The gas-turbine combustion chamber wall of claim 1, wherein the surface structure comprises at least one depression.

5. The gas-turbine combustion chamber wall of claim 1, wherein the surface structure comprises at least one polygonal protrusion.

6. The gas-turbine combustion chamber wall of claim 1, wherein the surface structure comprises at least one prismatic protrusion.

7. The gas-turbine combustion chamber wall of claim 1, wherein the tile includes a thermal barrier coating of ceramic material.

8. The gas-turbine combustion chamber wall of claim 1, wherein the impingement-cooling holes are variable in diameter in at least one of an axial direction and a circumferential direction.

9. The gas-turbine combustion chamber wall of claim 1, wherein the effusion-cooling holes are variable in diameter in at least one of an axial direction and a circumferential direction.

10. The gas-turbine combustion chamber wall of claim 1, wherein dimensions of the surface structure are variable in size in at least one of an axial direction and a circumferential direction.

11. The gas-turbine combustion chamber wall of claim 1, wherein the impingement-cooling holes are essentially vertical to the combustion chamber wall.

12. The gas-turbine combustion chamber wall of claim 1, wherein the effusion-cooling holes are at a shallow angle of between 10 and 45 degrees.

13. The gas-turbine combustion chamber wall of claim 12, wherein the effusion-cooling holes are at an angle of between 15 and 30 degrees.

14. The gas-turbine combustion chamber wall of claim 1, wherein the effusion-cooling holes are oriented axially to the combustion chamber as regards their center axes.

15. The gas-turbine combustion chamber wall of claim 1, wherein the effusion-cooling holes are oriented at an angle to the axial axis of the combustion chamber, as regards the center axes of the effusion-cooling holes.

16. The gas-turbine combustion chamber wall of claim 1, wherein the second region and the third region overlap in the axial direction.

17. The gas-turbine combustion chamber wall of claim 1, wherein the second region and the third region do not overlap in the axial direction.