Gas-turbine combustion chamber with mixing air orifices and chutes in modular design

Patent metadata

Field	Value
Publication number	US-9328665-B2
Application number	US-201313947797-A
Country	US
Kind code	B2
Filing date	Jul 22, 2013
Priority date	Aug 3, 2012
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

The present invention relates to a gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber.

First claim

What is claimed is:

1. A gas-turbine combustion chamber comprising:
a combustion chamber wall,
tiles arranged on an interior of the combustion chamber wall, at least portions of the tiles being spaced apart from the combustion chamber wall;
mixing air orifices passing through the combustion chamber wall and the tiles,
a mixing air wall element extending at least around a portion of a circumference of the combustion chamber and including a plurality of the mixing air orifices;
wherein, each of the plurality of mixing air orifices includes a tubular chute passing from an exterior of the combustion chamber wall through at least one tile to an interior of the combustion chamber, the tubular chute including an inflow area;
a flange transitioning to the tubular chute in the inflow area of the tubular chute, the flange level with a surrounding adjacent portion of the combustion chamber wall and smoothly transitioning between the surrounding adjacent portion of the combustion chamber wall and the inflow area;
wherein the mixing air wall element is shaped as a circular segment.

2. The gas-turbine combustion chamber in accordance with claim 1 , wherein the combustion chamber wall includes tile support wall elements supporting the tiles, wherein the mixing air wall element is connected to tile support wall elements positioned on opposite sides of the mixing air wall element.

3. The gas-turbine combustion chamber in accordance with claim 2 , and further comprising threaded fasteners connecting the mixing air wall element to the tile support wall elements.

4. The gas-turbine combustion chamber in accordance with claim 2 , wherein the mixing air wall element is welded to the tile support wall elements.

5. The gas-turbine combustion chamber in accordance with claim 1 , wherein the mixing air wall element is a casting.

6. The gas-turbine combustion chamber in accordance with claim 1 , wherein the tubular chutes of the plurality of mixing air orifices are arranged in a single row in a circumferential direction of the combustion chamber.

7. The gas-turbine combustion chamber in accordance with claim 1 , wherein the combustion chamber wall includes tile support wall elements supporting the tiles, with at least portions of the tiles being spaced apart from the tile support wall elements.

8. The gas-turbine combustion chamber in accordance with claim 7 , and further comprising a combustion chamber head and a plurality of the mixing air wall elements and the tile support wall elements, each formed as at least one chosen from a ring and a ring segment, each extending in a circumferential direction of the combustion chamber, the at least one chosen from the rings and ring segments being adjacently arranged in an axial direction of the combustion chamber and connected to the combustion chamber head.

9. The gas-turbine combustion chamber of claim 8 , wherein the mixing air wall elements attach tile support wall elements upstream of the mixing air wall elements to tile support wall elements downstream of the mixing air wall elements.

10. The gas-turbine combustion chamber of claim 9 , wherein the inflow area includes a radiused portion and the radiused portion extends through the combustion chamber wall toward an interior of the combustion chamber to a position beyond a combustion chamber side of the combustion chamber wall.

11. The gas-turbine combustion chamber in accordance with claim 1 , wherein each of the tubular chutes of the plurality of mixing air orifices includes a rounded inflow area.

12. The gas-turbine combustion chamber of claim 1 , wherein the circular segment attaches a portion of the combustion chamber wall upstream of the circular segment to a portion of the combustion chamber wall downstream of the circular segment.

13. The gas-turbine combustion chamber of claim 12 , wherein the inflow area includes a radiused portion and the radiused portion extends through the combustion chamber wall toward an interior of the combustion chamber to a position beyond a combustion chamber side of the combustion chamber wall.

14. The gas-turbine combustion chamber of claim 1 , wherein the inflow area includes a radiused portion and the radiused portion extends through the combustion chamber wall toward an interior of the combustion chamber to a position beyond a combustion chamber side of the combustion chamber wall.

15. The gas-turbine combustion chamber of claim 14 , wherein a radius of the radiused portion is greater than a thickness of the combustion chamber wall.

16. The gas-turbine combustion chamber of claim 1 , wherein the flange is connected to the tubular chute.

17. The gas-turbine combustion chamber of claim 1 , wherein the flange is integral with the tubular chute.

18. A gas-turbine combustion chamber comprising:
a combustion chamber wall,
tiles arranged on an interior of the combustion chamber wall at a certain distance from the combustion chamber wall;
mixing air orifices passing through the combustion chamber wall and the tiles,
a mixing air wall element extending at least around a portion of a circumference of the combustion chamber and including a plurality of the mixing air orifices;
wherein, each of the plurality of mixing air orifices includes a tubular chute passing from an exterior of the combustion chamber wall through at least one tile to an interior of the combustion chamber, the tubular chute including an inflow area;
wherein the inflow area includes a radiused portion and the radiused portion extends through the combustion chamber wall toward an interior of the combustion chamber to a position beyond a combustion chamber side of the combustion chamber wall;
wherein the mixing air wall element is shaped as a circular segment.

19. The gas-turbine combustion chamber of claim 18 , wherein a radius of the radiused portion is greater than a thickness of the combustion chamber wall.

20. A gas-turbine combustion chamber comprising:
a combustion chamber wall,
tiles arranged on an interior of the combustion chamber wall, at least portions of the tiles being spaced apart from the combustion chamber wall;
mixing air orifices passing through the combustion chamber wall and the tiles,
a mixing air wall element extending at least around a portion of a circumference of the combustion chamber and including a plurality of the mixing air orifices;
wherein, each of the plurality of mixing air orifices includes a tubular chute passing from an exterior of the combustion chamber wall through at least one tile to an interior of the combustion chamber, the tubular chute including an inflow area;
a flange transitioning to the tubular chute in the inflow area of the tubular chute, the flange level with a surrounding adjacent portion of the combustion chamber wall and smoothly transitioning between the surrounding adjacent portion of the combustion chamber wall and the inflow area;
wherein the combustion chamber wall includes tile support wall elements supporting the tiles, wherein the mixing air wall element is connected to tile support wall elements positioned on opposite sides of the mixing air wall element.

Assignees

• Rolls Royce Deutschland

Inventors

• Doerr Thomas
• Rackwitz Leif
• Penz Stefan

Classifications

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/045

  using pipes · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title