COMBUSTION CHAMBER OF A COMBUSTOR FOR A GAS TURBINE

• US 20140373548A1
• Filed: 12/21/2012
• Published: 12/25/2014
• Est. Priority Date: 01/05/2012
• Status: Active Grant

• Current Assignee: Siemens Energy Global GmbH & Co. KG (Siemens AG)
• Original Assignee: Siemens AG
• Inventors: Hasselqvist, Magnus, Rubensdorffer, Frank
• Granted Patent: US 9,885,480 B2
• Time in Patent Office: Days
• US Class Current: 60/737
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F01D 9/06 Fluid supply conduits to nozzles or the like
• CPC Class Codes: F23M 20/005 Noise absorbing means
• CPC Class Codes: F23M 9/06 in fire-boxes
• 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 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow means for creating turbulence F23R2900/03045
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/10 for primary air F23R3/06, F23R3/045 take precedence
• CPC Class Codes: F23R 3/16 with devices inside the flame tube or the combustion chamber to influence the air or gas flow
• CPC Class Codes: F23R 3/44 Combustion chambers comprising a single tubular flame tube within a tubular casing reverse-flow combustion chambers F23R3/54
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52

Abstract

A combustion chamber of a combustor for a gas turbine is provided. A combustion chamber includes a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising a radial inner wall portion and a radial outer wall portion, a first section comprising an opening for the installation of a burner, and a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment.

Claims

1-14. -14. (canceled)

15. A combustion chamber for an annular combustor for a gas turbine, comprising

a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising:

a radial inner wall portion and a radial outer wall portion,

a first section comprising an opening for the installation of a burner, and

a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment,

wherein the first section and the second section are located at opposing first end and second end of the combustion chamber,

wherein each segment comprises an inner surface and an outer surface with a channel defined between the inner surface and the outer surface,

wherein compressed air from a compressor of the gas turbine is directed into the airfoil,

wherein air from the airfoil is conducted into the channel, and

wherein the airfoil present at the second end guides a working medium through an exit located at the second end of the combustion chamber.

16. The combustion chamber according to claim 15, wherein the second end located downstream the first end comprises an exit to discharge a working medium.

17. The combustion chamber according to claim 15, wherein each segment comprises two airfoils, the airfoils extending between the radial inner wall portion and the radial outer wall portion of the respective segment.

18. The combustion chamber according to claim 15, wherein the outer surface is brazed.

19. The combustion chamber according to claim 15, further comprising a panel located at the first end for drawing compressed air into the combustion chamber.

20. The combustion chamber according to claim 15, wherein the airfoil and wall portions are formed from an alloy.

21. The combustion chamber according to claim 20, wherein the alloy is one of a Nickel based gamma prime strengthened alloy, IN738LC, or CM247CC.

22. The combustion chamber according to claim 15, wherein the airfoil and the wall portions are one piece of a material.

23. The combustion chamber according to claim 15, wherein the airfoil and wall portions are cast.

24. The combustion chamber according to claim 23, wherein two adjacent segments are assigned to one burner.

25. A combustor comprising a combustion chamber according to claim 15.

26. A gas turbine, comprising:

a combustor with an annular combustion chamber according to claim 15.