Fuel injection insert for a turbine nozzle segment

Patent metadata

Field	Value
Publication number	US-9458767-B2
Application number	US-201313845334-A
Country	US
Kind code	B2
Filing date	Mar 18, 2013
Priority date	Mar 18, 2013
Publication date	Oct 4, 2016
Grant date	Oct 4, 2016

Abstract

One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.

First claim

What is claimed is:

1. A turbine nozzle segment, comprising:
an inner platform, an outer platform and an airfoil that extends therebetween, the airfoil having a forward portion and an aft portion that is disposed downstream from the forward portion;
a fuel injection insert that extends between the inner platform and the outer platform, wherein the fuel injection insert is positioned downstream from the aft portion of the airfoil, the fuel injection insert including a pressure side, a suction side and a trailing edge defined along an aft portion of the fuel injection insert, wherein the fuel injection insert is detached from the airfoil, such that a gap is formed between a forward portion of the fuel injection insert and the aft portion of the airfoil;
a source of fuel in fluid communication with the fuel injection insert, wherein the fuel is combusted downstream of the airfoil;
a fuel circuit that extends within the fuel injection insert; and
a plurality of fuel injection ports disposed within the fuel injection insert, wherein the plurality of fuel injection ports are in fluid communication with the fuel circuit, wherein at least one fuel injection port of the plurality of fuel injection ports is defined along at least one of the pressure side and the suction side of the fuel injection insert.

2. The turbine nozzle segment as in claim 1 , wherein the fuel injection insert further comprises a fuel inlet port that is in fluid communication with the fuel circuit.

3. The turbine nozzle segment as in claim 1 , wherein the fuel injection ports are disposed on the suction side of the fuel injection insert.

4. The turbine nozzle segment as in claim 1 , wherein the fuel injection ports are disposed on both the pressure side and the suction side of the fuel injection insert.

5. The turbine nozzle segment as in claim 1 , wherein at least some of the fuel injection ports are disposed along the aft portion of the fuel injection insert.

6. The turbine nozzle segment as in claim 1 , further comprising an insert opening that extends through at least one of the inner platform or the outer platform, wherein the fuel injection insert extends through the insert opening.

7. The turbine nozzle segment as in claim 1 , wherein the fuel injection insert is removable from the turbine nozzle segment.

8. A turbine section of a gas turbine, comprising:
a stage of turbine blades arranged in an annular array around a shaft, the turbine blades being coupled to the shaft; and
a stage of turbine nozzle segments that are arranged in an annular array around the shaft upstream from the stage of turbine blades, wherein at least one turbine nozzle segment comprises:
an inner platform, an outer platform and an airfoil that radially separates the inner platform from the outer platform to define a hot gas flow path through the turbine nozzle segment, the airfoil having a forward portion and an aft portion disposed downstream from the forward portion;
a fuel injection insert that extends between the inner platform and the outer platform, wherein the fuel injection insert is positioned downstream from the aft portion of the airfoil, the fuel injection insert including a pressure side, a suction side and trailing edge defined along an aft portion of the fuel injection insert, wherein the fuel injection insert is detached from the airfoil, such that a gap is formed between a forward portion, of the fuel injection insert and the aft portion of the airfoil;
a source of fuel in fluid communication with the fuel injection insert, wherein the fuel is combusted downstream of the airfoil;
a fuel circuit that extends within the fuel injection insert; and
a plurality of fuel injection ports disposed within the fuel injection insert, wherein the plurality of fuel injection ports provide for fluid communication between the fuel circuit and the hot gas path downstream from the airfoil, wherein at least one fuel injection port of the plurality of fuel injection ports is defined along at least one of the pressure side and the suction side of the fuel injection insert.

9. The turbine section as in claim 8 , wherein the fuel injection insert further comprises a fuel inlet port that is in fluid communication with the fuel circuit and the turbine section includes a fuel supply that is in fluid communication with the fuel inlet port.

10. The turbine section as in claim 8 , wherein at least one of the fuel injection ports is disposed on the suction side of the fuel injection insert.

11. The turbine. section as in claim 8 , wherein at least one of the fuel injection ports is disposed on the pressure side and at least one of the fuel injection ports is disposed on the suction side of the fuel injection insert.

12. The turbine section as in claim 8 , wherein at least some of the fuel injection ports are disposed along the aft portion of the fuel injection insert.

13. The turbine section as in claim 8 , further comprising an insert opening that extends through at least one of the inner platform or the outer platform, wherein the fuel injection insert extends through the insert opening.

14. The turbine section as in claim 8 , wherein the fuel injection insert is removable from the turbine nozzle segment.

15. A gas turbine, comprising:
a compressor;
a combustor disposed downstream from the compressor;
a turbine section disposed downstream from the combustor, the turbine section having a stage of turbine blades coupled to a shaft; and
a stage of turbine nozzle segments that are arranged in an annular array around the shaft upstream from the stage of turbine blades, each turbine nozzle segment comprising:
an inner platform, an outer platform and an airfoil that radially separates the inner platform from the outer platform to define a hot gas path through the turbine nozzle segment, the airfoil having a forward portion and an aft portion disposed downstream from the forward portion;
a fuel injection insert that extends between the inner platform and the outer platform, wherein the fuel injection insert is positioned downstream from the aft portion of the airfoil, the fuel injection insert including a pressure side, a suction side and a trailing edge defined by an aft portion of the fuel injection insert, wherein the fuel injection insert is detached from the airfoil, such that a gap is formed between a forward portion of the fuel injection insert and the aft portion of the airfoil;
a source of fuel in fluid communication with the fuel injection insert, wherein the fuel is combusted downstream of the airfoil;
a fuel circuit that extends within the fuel injection insert; and
a plurality of fuel injection ports disposed within the fuel injection insert, wherein the plurality of fuel injection ports provide for fluid communication between the fuel circuit and the hot gas path downstream from the airfoil, wherein at least one fuel injection port of the plurality of fuel injection ports is defined along at least one of the pressure side and the suction side of the fuel injection insert.

16. The gas turbine as in claim 15 , further comprising an insert opening that extends through at least one of the inner platform or the outer platform, wherein the fuel injection insert extends through the insert opening.

17. The gas turbine as in claim 15 , wherein the fuel injection insert is removable from the turbine nozzle segment.

18. The gas turbine as in claim 15 , further comprising a fuel supply that is in fluid communication with the fuel circuit of the fuel injection insert.

19. The gas turbine as in clai

Assignees

• Gen Electric

Inventors

• Farrell Thomas Raymond

Classifications

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F01D5/185

  Liquid cooling (F01D5/181 takes precedence) · CPC title

• F02C6/003

  Gas-turbine plants with heaters between turbine stages · CPC title

• F01D9/06

  Fluid supply conduits to nozzles or the like · CPC title