Micro-Channel Cooling of Integrated Combustor Nozzle of a Segmented Annular Combustion System

• US 20170276358A1
• Filed: 03/21/2017
• Published: 09/28/2017
• 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, Hughes, Michael John
• Granted Patent: US 10,584,876 B2
• Time in Patent Office: Days
• CPC Class Codes: F23R 2900/00001 Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow means for creating turbulence F23R2900/03045
• 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: 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
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. The fuel injection panel includes an aft end portion, a first side wall, a second side wall, premixing channels defined between the first side wall and the side wall, and injection outlets defined along at least one of the first side wall and the second side wall. The aft end portion defines a turbine nozzle portion. An interior portion between the first side wall and the second side wall includes walls that extend between the first and second side walls, thereby partitioning the interior portion into discrete air cavities. The liner segments may be cooled by micro-channel cooling passages, which may be fluidly coupled to a collection trough.

Claims

1. An integrated combustor nozzle, comprising:

a fuel injection panel that extends radially between an inner liner segment and an 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, the aft end portion of the fuel injection panel defining a turbine nozzle;

wherein the inner liner segment defines a plurality of micro-channel cooling passages that extend between an inner surface and an outer surface of the inner liner segment, each micro-cooling passage having an inlet hole defined along the outer surface and a corresponding air outlet hole.

2. The integrated combustor nozzle as in claim 1, further comprising a duct coupled to the outer surface of the inner liner segment, wherein the duct defines a collection trough, and wherein at least one air outlet hole is disposed within the duct and is in fluid communication with the collection trough.

3. The integrated combustor nozzle as in claim 2, wherein the collection trough is in fluid communication with a premix air plenum defined within the fuel injection panel;

and wherein each premixing channel of the plurality of premixing channels is in fluid communication with the premix air plenum.

4. The integrated combustor nozzle as in claim 3, wherein the collection trough is in fluid communication with a premix channel air cavity defined within the fuel injection panel, and wherein the premix channel air cavity surrounds the plurality of premixing channels.

5. The integrated combustor nozzle as in claim 4, wherein the collection trough is in fluid communication with an air cavity defined within the fuel injection panel, the air cavity being downstream of the premix channel air cavity.

6. The integrated combustor nozzle as in claim 1, wherein a first micro-channel of the plurality of micro-channels is longer than a second micro-channel of the plurality of micro-channels.

7. The integrated combustor nozzle as in claim 1, wherein one or more outlet holes of one or more corresponding micro-channel cooling passages is disposed on a side wall of the inner liner segment.

8. The integrated combustor nozzle as in claim 1, wherein one or more outlet holes of one or more corresponding micro-channel cooling passages is disposed on an inner surface of the inner liner segment.

9. The integrated combustor nozzle as in claim 1, wherein a length of one or more outlet holes of one or more corresponding micro-channel cooling passages is six inches or less.

10. An integrated combustor nozzle, comprising:

a fuel injection panel that extends radially between an inner liner segment and an 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, the aft end portion of the fuel injection panel defining a turbine nozzle;

wherein the outer liner segment defines a plurality of micro-channel cooling passages that extend between an inner surface and an outer surface of the outer liner segment, each micro-cooling passage having an inlet hole defined along the outer surface and a corresponding air outlet hole.

11. The integrated combustor nozzle as in claim 10, further comprising a duct coupled to the outer surface of the outer liner segment, wherein the duct defines a collection trough, and wherein at least one air outlet hole is disposed within the duct and is in fluid communication with the collection trough.

12. The integrated combustor nozzle as in claim 11, wherein the collection trough is in fluid communication with a premix air plenum defined within the fuel injection panel, and wherein each premixing channel of the plurality of premixing channels is in fluid communication with the premix air plenum.

13. The integrated combustor nozzle as in claim 11, wherein the collection trough is in fluid communication with a premix channel air cavity defined within the fuel injection panel, and wherein the premix channel air cavity surrounds the plurality of premixing channels.

14. The integrated combustor nozzle as in claim 13, wherein the collection trough is in fluid communication with an air cavity defined within the fuel injection panel, the air cavity being downstream of the premix channel air cavity.

15. The integrated combustor nozzle as in claim 11, wherein a first micro-channel cooling passage of the plurality of micro-channel cooling passages is longer than a second micro-channel cooling passage of the plurality of micro-channels.

16. The integrated combustor nozzle as in claim 11, wherein one or more outlet holes of one or more corresponding micro-channel cooling passages is disposed on a side wall of the outer liner segment.

17. The integrated combustor nozzle as in claim 11, wherein one or more outlet holes of one or more corresponding micro-channel cooling passages is disposed on an inner surface of the outer liner segment.

18. The integrated combustor nozzle as in claim 11, wherein a length of one or more outlet holes of one or more corresponding micro-channel cooling passages is six inches or less.