System and method having flame stabilizers for isothermal expansion in turbine stage of gas turbine engine

Patent metadata

Field	Value
Publication number	US-12247739-B2
Application number	US-202418634814-A
Country	US
Kind code	B2
Filing date	Apr 12, 2024
Priority date	Dec 30, 2022
Publication date	Mar 11, 2025
Grant date	Mar 11, 2025

Abstract

A system includes a gas turbine having a turbine shaft disposed along a rotational axis, a turbine casing disposed circumferentially about the turbine shaft, a combustion gas path disposed between the turbine shaft and the turbine casing, and a turbine stage disposed in the combustion gas path. The turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The gas turbine includes an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system includes a plurality of flame stabilizers configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion. The flame stabilizers are disposed in different axial positions over an axial length between leading and trailing edges of the turbine blades, wherein at least one flame stabilizer is coupled to each of the turbine blades.

First claim

The invention claimed is:

1. A system, comprising:
a plurality of turbine vanes having a plurality of fluid injectors configured to inject at least a fuel within a turbine stage; and
a plurality of turbine blades within the turbine stage, the plurality of turbine blades having a plurality of flame stabilizers configured to stabilize flames from combustion of the fuel, wherein the plurality of fluid injectors and the plurality of flame stabilizers are configured to distribute a heat release from the flames via different axial positioning of the flames over an axial length of the plurality of turbine blades.

2. The system of claim 1 , wherein the plurality of fluid injectors is configured to inject the fuel and an oxidant.

3. The system of claim 1 , wherein the plurality of fluid injectors is configured to inject the fuel, an oxidant, and a barrier gas between the fuel and the oxidant.

4. The system of claim 1 , wherein the plurality of flame stabilizers excludes fluid injection, and the plurality of turbine blades excludes fuel injection.

5. The system of claim 1 , wherein each turbine vane of the plurality of turbine vanes has a different injection flow rate by one or more fluid injectors of the plurality of fluid injectors from at least one other turbine vane of the plurality of turbine vanes.

6. The system of claim 1 , wherein each turbine vane of the plurality of turbine vanes has a different injector arrangement of one or more fluid injectors of the plurality of fluid injectors from at least one other turbine vane of the plurality of turbine vanes.

7. The system of claim 6 , wherein the different injector arrangement of the one or more fluid injectors of the plurality of fluid injectors comprises an average axial position that varies from a first turbine vane to a second turbine vane in the plurality of turbine vanes.

8. The system of claim 7 , wherein each turbine vane of the plurality of turbine vanes has the one or more fuel injectors at a single axial position defining the average axial position, and the single axial position varies from the first turbine vane to the second turbine vane in the plurality of turbine vanes.

9. The system of claim 7 , wherein each turbine vane of the plurality of turbine vanes has the one or more fuel injectors at multiple axial positions defining the average axial position.

10. The system of claim 6 , wherein the different injector arrangement of the one or more fuel injectors of the plurality of fuel injectors are disposed at two or more of:
a leading edge portion of a first set of one or more turbine vanes of the plurality of turbine vanes;
an intermediate portion of a second set of one or more turbine vanes of the plurality of turbine vanes; or
a trailing edge portion of a third set of one or more turbine vanes of the plurality of turbine vanes.

11. The system of claim 10 , wherein the different injector arrangement of the one or more fuel injectors of the plurality of fuel injectors are disposed at each of the leading edge portion of the first set, the intermediate portion of the second set, and the trailing edge portion of the third set.

12. The system of claim 1 , wherein each turbine blade of the plurality of turbine blades has a different stabilizer arrangement of one or more flame stabilizers of the plurality of flame stabilizers from at least one other turbine blade of the plurality of turbine blades.

13. The system of claim 12 , wherein the different stabilizer arrangement of the one or more flame stabilizers of the plurality of flame stabilizers comprises an average axial position that varies from one turbine blade to another in the plurality of turbine blades.

14. The system of claim 13 , wherein each turbine blade of the plurality of turbine blades has the one or more flame stabilizers at a single axial position defining the average axial position, and the single axial position varies from one turbine blade to another in the plurality of turbine blades.

15. The system of claim 13 , wherein each turbine blade of the plurality of turbine blades has the one or more flame stabilizers at multiple axial positions defining the average axial position.

16. The system of claim 13 , wherein the different stabilizer arrangement of the one or more flame stabilizers of the plurality of flame stabilizers are disposed at two or more of:
a leading edge portion of a first set of one or more turbine blades of the plurality of turbine blades;
an intermediate portion of a second set of one or more turbine blades of the plurality of turbine blades; or
a trailing edge portion of a third set of one or more turbine blades of the plurality of turbine blades.

17. The system of claim 16 , wherein the different stabilizer arrangement of the one or more flame stabilizers of the plurality of flame stabilizers are disposed at each of the leading edge portion of the first set, the intermediate portion of the second set, and the trailing edge portion of the third set.

18. The system of claim 1 , wherein the one or more flame stabilizers of the plurality of flame stabilizers comprise a recess, a protrusion, or a combination thereof.

19. A system, comprising:
a plurality of turbine vanes having a plurality of fluid injectors configured to inject at least a fuel within a turbine stage; and
a plurality of turbine blades within the turbine stage, the plurality of turbine blades having a plurality of flame stabilizers, wherein each turbine blade of the plurality of turbine blades has a different stabilizer arrangement of one or more flame stabilizers of the plurality of flame stabilizers from at least one other turbine blade of the plurality of turbine blades.

20. The system of claim 19 , wherein the different stabilizer arrangement of the one or more flame stabilizers of the plurality of flame stabilizers comprises an average axial position that varies from one turbine blade to another in the plurality of turbine blades.

21. The system of claim 20 , wherein each turbine vane of the plurality of turbine vanes has at least one of: a different injection flow rate by one or more fluid injectors of the plurality of fluid injectors, a different injector arrangement of one or more fluid injectors of the plurality of fluid injectors, or a combination thereof.

22. A method, comprising:
injecting a fluid comprising fuel from a plurality of fluid injectors of a plurality of turbine vanes of a turbine stage of a gas turbine; and
stabilizing flames from combustion of the fuel via a plurality of flame stabilizers of a plurality of turbine blades of the turbine stage, wherein the injecting and the stabilizing comprises distributing a heat release from the flames via different axial positioning of the flames over an axial length of the plurality of turbine blades.

Assignees

• Ge Infrastructure Technology Llc

Inventors

• Hall Joel Meador
• Woodall John Farrior

Classifications

• F05D2220/3212

  the first stage of a turbine · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F23R3/20

  incorporating fuel injection means · CPC title

• F23R3/22 Primary

  movable, e.g. to an inoperative position; adjustable, e.g. self-adjusting · CPC title