Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes

Patent metadata

Field	Value
Publication number	US-9518738-B2
Application number	US-201414180028-A
Country	US
Kind code	B2
Filing date	Feb 13, 2014
Priority date	Feb 26, 2013
Publication date	Dec 13, 2016
Grant date	Dec 13, 2016

Abstract

The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.

First claim

What is claimed is:

1. A gas turbine combustion chamber, comprising:
a combustion chamber wall including a tile carrier,
a plurality of wall tiles mounted on the tile carrier spaced apart from the tile carrier to form an impingement cooling gap between the tile carrier and the plurality of wall tiles,
wherein the tile carrier includes a plurality of impingement cooling holes and each wall tile includes a plurality of effusion holes with inlet openings,
wherein each wall tile includes, on a side facing the tile carrier, a surface structure which includes raised portions rising from a surface of the wall tile and extending in a direction toward the tile carrier;
wherein the inlet openings of the effusion holes are located on the raised portions of the surface structure;
wherein the centric axes of the inlet openings are arranged substantially perpendicular to a surface of the tile carrier;
wherein the centric axes of the inlet openings are arranged substantially parallel to centric axes of the impingement cooling holes;
wherein the raised portions are formed as ribs;
wherein the impingement cooling holes are arranged to direct impingement air jets into a space between the ribs and spaced apart from the inlet openings.

2. The gas turbine combustion chamber in accordance with claim 1 , wherein the inlet openings of the effusion holes are spaced a distance from the surface of the tile carrier which is 0.5 to 1.5 times a diameter of the inlet openings.

3. The gas turbine combustion chamber in accordance with claim 1 , and further comprising a spacer arranged around at least one of the inlet openings that at least partially encloses the at least one of the inlet openings.

4. The gas turbine combustion chamber in accordance with claim 3 , wherein the spacer is shaped to impart a swirl to air flowing into the at least one of the inlet openings.

5. The gas turbine combustion chamber in accordance with claim 1 , and further comprising a spacer arranged adjacent to at least one of the inlet openings.

6. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes are straight.

7. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes have a constant.

8. The gas turbine combustion chamber in accordance with claim 1 , wherein the raised portions include polygonal cells, with a prism positioned in each of the polygonal cells.

9. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes have a widening diameter.

10. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes are curved.

11. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes are partially straight.

12. The gas turbine combustion chamber in accordance with claim 1 , wherein the effusion holes are partially curved.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Gerendas Miklos

Classifications

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title