Combustor transition

Patent metadata

Field	Value
Publication number	US-9429032-B2
Application number	US-201314062001-A
Country	US
Kind code	B2
Filing date	Oct 24, 2013
Priority date	Oct 24, 2012
Publication date	Aug 30, 2016
Grant date	Aug 30, 2016

Abstract

A combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine is disclosed. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end includes an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. A method for retrofitting a gas turbine and method for borescope inspection of a GT are disclosed.

First claim

What is claimed is:

1. A combustor transition adapted to guide combustion gases in a hot gas flow path extending between a gas turbine combustion chamber and a first stage of a turbine, the combustor transition comprising:
a duct having an inlet at an upstream end adapted for connection to the combustion chamber and an outlet at a downstream end adapted for connection to the first stage of the turbine, wherein the downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall, wherein at least one side wall has a side wall extension which extends in a downstream direction beyond the outlet and wherein the side wall extension at least partly encloses a first resonator volume or wherein the first and second side wall extensions of two combustor transitions are configured such that the first and second side wall extensions, when installed next to each other in a gas turbine, at least partly encloses a first resonator volume, and wherein at least one side wall extension comprises a resonator hole, which is configured as a neck of a Helmholtz-damper.

2. The combustor transition according to claim 1 , wherein the first resonator volume has a resonator upstream end, which is limited by a first separating member.

3. The combustor transition according to claim 1 , wherein the first resonator volume comprises a volume, which is at least partly enclosed by the side walls of the two combustor transitions when installed next to each other in a gas turbine, and wherein the first resonator volume is limited at an upstream end by a separating member.

4. The combustor transition according to claim 2 , wherein the combustor transition comprises a second resonator volume which is at least partly enclosed by the side walls of the two combustor transitions when installed next to each other in a gas turbine and is further limited at an upstream end by a second separating member, and wherein the first separating member comprises a second resonator hole connecting the first resonator volume and the second resonator volume configured as a neck of a Helmholtz-damper for suppression of at least two pulsation frequencies.

5. The combustor transition according to claim 1 , wherein the combustor transition comprises a hollow insert, which delimits the first resonator volume and/or a second resonator volume.

6. The combustor transition according to claim 1 , further comprising a cooling air supply to the first resonator volume and/or a second resonator volume.

7. The combustor transition according to claim 1 , wherein the first side wall ends at the outlet and wherein the second side wall has a side wall extension which extends in a downstream direction beyond the outlet and forms U-shaped cross-section, wherein a first leg of the U-shaped extension is connected to the second side wall, separating a hot gas side from a cooling side, and a second leg of the U-shaped extension begins directly downstream of the outlet on the cooling side of the first leg, and is connected to the first leg by a third leg at a downstream end, thereby at least partly enclosing the first resonator volume.

8. The combustor transition according claim 1 , wherein the first resonator volume is closed towards the outer wall and/or towards the inner wall by an end plate.

9. The combustor transition according to claim 8 , wherein the walls of the first resonator volume comprises film cooling and/or effusion cooling holes.

10. A can combustor with a combustion chamber, further comprising a combustor transition according to claim 1 .

11. A gas turbine with at least one compressor, at least one turbine, and at least one combustion chamber, further comprising a combustor transition according to claim 1 .

12. The gas turbine according to claim 11 , wherein the side wall extension extends downstream of the combustor transition into a space between an inner and outer platform of a vane one directly upstream of an airfoil of the vane one.

13. The gas turbine according to claim 12 , wherein at least one side wall extension extends downstream to the leading edge of the vane one airfoil leaving a gap which is sized to allow for thermal expansion between the combustion chamber and turbine.

14. A method for retrofitting a gas turbine comprising the steps of opening a gas turbine housing, removing at least one existing combustor transition, installing at least one combustor transition according to claim 1 , and of closing the gas turbine housing.

15. A method for borescope inspection of a gas turbine with a combustor transition according to claim 7 , wherein every second combustor transition is removed for inspection and the hot gas path downstream of the removed combustor transition as well as the hot gas path of a neighboring combustor, which remains installed in the gas turbine is inspected via a gap which is opened by removing the side wall extension together with the removed combustor transition.

Assignees

• Alstom Technology Ltd
• General Electric Technology Gmbh

Inventors

• Bothien Mirko Ruben
• Düsing Michael

Classifications

• F05D2260/963

  by Helmholtz resonators · CPC title

• F05D2250/52

  Outlet · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title