Integrated Combustor Nozzle for a Segmented Annular Combustion System

• US 20170299187A1
• Filed: 03/21/2017
• Published: 10/19/2017
• Est. Priority Date: 03/25/2016
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Berry, Jonathan Dwight, Widener, Stanley Kevin, Hughes, Michael John, Hafner, Matthew Troy, Citeno, Joseph Vincent
• Granted Patent: US 10,605,459 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 7/24 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 Class Codes: F05D 2220/30 in turbines
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F23R 2900/03341 Sequential combustion chambers or burners
• CPC Class Codes: F23R 3/283 Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/34 Feeding into different combustion zones
• CPC Class Codes: F23R 3/346 for staged combustion
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52

Abstract

The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.

Claims

1. A combustor nozzle, comprising:

an inner liner segment;

an outer liner segment radially spaced from the inner liner segment; and

a fuel injection panel that extends radially between the inner liner segment and the outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, a second side wall, a plurality of premixing channels defined between the first side wall and the second side wall, and a plurality of injection outlets defined along at least one of the first side wall and the second side wall;

wherein each injection outlet of the plurality of injection outlets is in fluid communication with a respective premixing channel of the plurality of premixing channels; and

wherein the aft end portion of the fuel injection panel defines a turbine nozzle.

2. The combustor nozzle as in claim 1, wherein the first side wall is a pressure side wall, and the second side wall is a suction side wall.

3. The combustor nozzle as in claim 2, wherein the plurality of injection outlets comprises a plurality of suction side injection outlets radially spaced along the suction side wall, the plurality of suction side injection outlets defining a radial injection plane downstream of the forward end portion of the fuel injection panel, and wherein each suction side injection outlet is in fluid communication with a respective premixing channel of the plurality of premixing channels.

4. The combustor nozzle as in claim 2, wherein the plurality of injection outlets comprises a plurality of pressure side injection outlets radially spaced along the pressure side wall, the plurality of pressure side injection outlets defining a radial injection plane downstream of the forward end portion of the fuel injection panel, and wherein each pressure side injection outlet is in fluid communication with a respective premixing channel of the plurality of premixing channels.

5. The combustor nozzle as in claim 1, wherein the plurality of injection outlets comprises a plurality of suction side injection outlets radially spaced along the suction side wall in a first radial plane and a plurality of pressure side injection outlets radially spaced along the pressure side wall in a second radial plane, and wherein each suction side injection outlet and each pressure side injection outlet is in fluid communication with a respective premixing channel of the plurality of premixing channels.

6. The combustor nozzle as in claim 5, wherein the first radial plane is axially offset from the second radial plane.

7. The combustor nozzle as in claim 2, further comprising a premix air plenum defined between the pressure side wall and the suction side wall, wherein each premixing channel of the plurality of premixing channels is in fluid communication with the premix air plenum.

8. The combustor nozzle as in claim 2, further comprising a partition that extends within the fuel injection panel between an inner surface of the pressure side wall and an inner surface of the suction side wall, wherein the partition at least partially defines a cooling air cavity within the fuel injection panel.

9. The combustor nozzle as in claim 8, wherein the partition defines a plurality of apertures, wherein the plurality of apertures provide for cooling air flow through the partition into or out of the cooling air cavity.

10. The combustor nozzle as in claim 1, wherein one or more of the premixing channels of the plurality of premixing channels includes a straight portion and a curved portion, and wherein the curved portion is defined proximate to a respective injection outlet of plurality of injection outlets.

11. The combustor nozzle as in claim 2, wherein the plurality of premixing channels is radially stacked within the fuel injection panel between the pressure side wall and the suction side wall.

12. The combustor nozzle as in claim 11, wherein the plurality of premixing channels comprises a plurality of pressure side premixing channels and a plurality of suction side premixing channels arranged in an alternating radial stack between the pressure side wall and the suction side wall within the fuel injection panel.

13. The combustor nozzle as in claim 12, wherein each pressure side premixing channel of the plurality of pressure side premixing channels includes a straight portion and a curved portion that curves towards the pressure side wall, and each suction side premixing channel of the plurality of suction side premixing channels includes a straight portion and a curved portion that curves towards the suction side wall.

14. The combustor nozzle as in claim 1, further comprising a thermal shield extending at least partially across the turbine nozzle of the fuel injection panel.

15. The combustor nozzle as in claim 1, wherein the first side wall is a pressure side wall and the second side wall is a suction side wall, and wherein the turbine nozzle comprises a concave pressure side and a convex suction side, the concave pressure side being integral with the pressure side wall and the convex suction side being integral with the suction side wall.

16. The combustor nozzle as in claim 1, further comprising a plurality of collars radially stacked within the panel fuel injector upstream from the plurality or premixing channels, wherein each respective collar is aligned with a respective premixing channel of the plurality of premixing channels.

17. The combustor nozzle as in claim 16, wherein the first side wall is a pressure side wall and the second side wall is a suction side wall, and wherein each collar of the plurality of collars is connected to at least one of the pressure side wall and the suction side wall.

18. The combustor nozzle as in claim 16, wherein the fuel injection panel defines an opening disposed along the forward end portion and aligned with the plurality of collars, wherein one or more floating collars at least partially surround the opening.

19. The combustor nozzle as in claim 1, wherein the first side wall is a pressure side wall and the second side wall is a suction side wall, wherein the pressure side wall varies in thickness between the forward end portion and the aft end portion of the fuel injection panel, between the outer liner segment and the inner liner segment of the fuel injection panel, or both.

20. The combustor nozzle as in claim 1, wherein the first side wall is a pressure side wall and the second side wall is a suction side wall, and wherein the suction side wall varies in thickness between the forward end portion and the aft end portion of the fuel injection panel, between the outer liner segment and the inner liner segment of the fuel injection panel, or both.

21. The combustor nozzle as in claim 1, wherein an overall panel thickness of the fuel injection panel varies along at least one of an axial length and a radial span of the fuel injection panel.

22. The combustor nozzle as in claim 1, wherein the panel fuel injector defines a cross-fire tube that extends through the pressure side wall and the suction side wall.

23. The combustor nozzle as in claim 22, wherein the cross-fire tube includes a plurality of purge air holes in fluid communication with a cooling air cavity defined within the panel fuel injector.

24. The combustor nozzle as in claim 1, wherein the inner liner segment, the outer liner segment, and the fuel injection panel are formed as a singular body.