Gas turbine with welded combustor liners

• US 8,516,823 B2
• Filed: 03/16/2010
• Issued: 08/27/2013
• Est. Priority Date: 09/24/2007
• Status: Expired due to Fees

• Current Assignee: General Electric Technology GmbH (GE Aerospace)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Tschuor, Remigi, Schneider, Lothar, Markovic, Alen, Hhnle, Harmut
• Primary Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US12/724,550
• Publication Number:
  US 20100205973A1
• Time in Patent Office: 1,260 Days
• Field of Search: 607/52, 607/96, 60798-800, 607/54, 607/55, 607/57
• US Class Current: 60/752
• CPC Class Codes: B23P 2700/13 Parts of turbine combustion chambers
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: F23R 2900/00017 Assembling combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/00019 Repairing or maintaining combustion chamber liners or subparts
• 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: Y10T 29/49318 Repairing or disassembling

Abstract

In order to provide an annular combustion chamber (3) which can be heated without thermal distortion, expands without distortion, and is reliably closed, and for repairs can be opened and permanently closed again and can be reconditioned, the inner and/or outer shell (8, 7) of an annular combustion chamber (3) is produced from a rotationally symmetrical sheet metal. For assembly, the shells are cut open along a split line (16), and the lower half of the inner and of the outer shell (8, 7) is introduced into the lower casing half of a gas turbine. After the insertion of the rotor, the two upper shell halves can likewise be inserted and be connected to the lower halves by welding. In order to improve the service life of the split line weld seam (21), film cooling of the weld seam is routed by an indentation. This may be implemented, for example, by welded-in split line elements (15) which are also suitable for retrofitting.

Claims

1. A gas turbine comprising:

at least one annular combustion chamber comprising an annular inner shell and an annular outer shell, each shell being formed of sheet metal and having a split line which splits each shell into an upper half shell and a lower half shell;

wherein the inner shell is, the outer shell is, or both shells are closed in the split line by at least one split line weld seam; and

cooling holes in the inner shell, the outer shell, or both, along the at least one split line weld seam, the cooling holes being configured and arranged to film-cool at least part of the at least one split line weld seam;

wherein at least one of the inner and outer shells comprises an indentation having three bends in said sheet metal, the at least one split line weld seam and the cooling holes being formed in the indentation, the indentation having a bottom pointing away from the hot gas side of the at least one annular combustion chamber, the bottom being directly exposed to hot gases in the combustion chamber, the indentation configured and arranged to guide a cooling air film along the split line weld seam; and

wherein the bottom of the indentation extends lengthwise parallel to the main flow of the at least one annular combustion chamber.

2. A gas turbine as claimed in claim 1, further comprising a heat protection layer coated on the hot gas side of at least one of the inner shell and the outer shell.

3. A gas turbine as claimed in claim 1, wherein the cooling side of the at least one annular combustion chamber further comprises turbulence ribs in the region of the split line weld seam configured and arranged to cool the split line weld seam.

4. A gas turbine as claimed in claim 1, further comprising:

impingement cooling holes configured and arranged to cool the at least one split line weld seam.

5. A gas turbine as claimed in claim 1, further comprising:

a split line element having the indentation which points away from the hot gas side of the at least one annular combustion chamber and which guides cooling air film along the split line weld seam, the split line element being welded into at least one of the inner shell and the outer shell in the region of the split line.

6. A gas turbine as claimed in claim 5, wherein the split line element has a wall thickness which is different from that of said at least one of the inner shell and outer shell.

7. A gas turbine as claimed in claim 5, wherein the indentation has a dovetail shape.

8. A gas turbine as claimed in claim 1, wherein the at least one split line weld seam is arranged at the bottom of the indentation.

9. A gas turbine as claimed in claim 1, wherein the three bends comprise first, second, and third bends, the first bend and the third bend pointing away from the hot gas side of the annular surface of the inner or the outer shell, and the second bend being oriented opposite to the first bend and the third bend and connecting two ends of the first end and the third end, pointing toward the hot gas side forming an arc between the first bend and the third bend.