Cooling of integrated combustor nozzle of segmented annular combustion system

• US 10,641,491 B2
• Filed: 03/21/2017
• Issued: 05/05/2020
• 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
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): Jordan, Todd N
• Application Number:
  US15/464,425
• Publication Number:
  US 20170276357A1
• Time in Patent Office: 1,141 Days
• 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

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 air cavities and the liner segments may be cooled by impingement inserts or panels.

Claims

1. An integrated combustor nozzle of an annular combustor, comprising:

a fuel injection panel extending radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion at an upstream end of the annular combustor, 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 portion of the fuel injection panel;

wherein the fuel injection panel further comprises an interior portion defined within the fuel injection panel between the first side wall and the second side wall, wherein the interior portion includes a plurality of walls that extend between an inner surface of the first side wall and an inner surface of the second side wall, thereby partitioning the semi-hollow interior portion into a plurality of air cavities.

2. The integrated combustor nozzle as in claim 1, wherein the plurality of air cavities includes a premix channel air cavity, wherein the plurality of premixing channels is disposed within the premix channel air cavity.

3. The integrated combustor nozzle as in claim 1, wherein the plurality of air cavities includes a premix air plenum defined upstream from the plurality of premixing channels.

4. The integrated combustor nozzle as in claim 1, wherein the inner liner segment defines one or more openings in fluid communication with one or more air cavities of the plurality of air cavities.

5. The integrated combustor nozzle as in claim 1, wherein the outer liner segment defines one or more openings in fluid communication with one or more air cavities of the plurality of air cavities.

6. The integrated combustor nozzle as in claim 1, wherein at least one wall of the plurality of walls defines a plurality of apertures, and wherein the plurality of apertures provide for cooling air flow through the at least one wall into or out of a respective cooling air cavity of the plurality of cooling air cavities.

7. The integrated combustor nozzle as in claim 1, further comprising at least one impingement air insert disposed within a corresponding air cavity of the plurality of air cavities.

8. The integrated combustor nozzle as in claim 7, wherein the at least one impingement air insert defines a plurality of cooling holes oriented to direct air flow onto one or more of the inner surfaces surface of the first side wall or the inner surface of the second side wall of the fuel injection panel.

9. The integrated combustor nozzle as in claim 7, wherein the at least one impingement air insert is open on at least one of a radially inner end and a radially outer end of the impingement air insert.

10. The integrated combustor nozzle as in claim 1, wherein at least one air cavity of the plurality of air cavities extends at least partially through the turbine nozzle portion of the fuel injection panel.

11. The integrated combustor nozzle as in claim 1, wherein at least one air cavity of the plurality of air cavities extends at least partially through the turbine nozzle portion of the fuel injection panel a respective air cavity of the plurality of air cavities extends at least partially through the turbine nozzle portion of the fuel injection panel, and wherein an impingement air insert is disposed within the respective at least one air cavity of the plurality of air cavities.

12. The integrated combustor nozzle as in claim 1, further comprising a plurality of impingement air inserts, wherein each impingement air insert is disposed within a respective air cavity of the plurality of air cavities.

13. The integrated combustor nozzle as in claim 12, wherein at least one impingement air insert of the plurality of impingement air inserts is open on both a radially inner end of the respective impingement air insert and a radially outer end of the respective impingement air insert.

14. The integrated combustor nozzle as in claim 1, further comprising an inner impingement panel disposed along an outer surface of the inner liner segment, wherein the inner impingement panel defines a plurality of impingement holes, and wherein the inner impingement panel is radially spaced from the outer surface of the inner liner segment to form a cooling flow gap therebetween.

15. The integrated combustor nozzle as in claim 14, wherein the cooling flow gap is in fluid communication with an inlet of a premix air plenum of the fuel injection panel.

16. The integrated combustor nozzle as in claim 14, wherein the inner impingement panel defines one or more openings in fluid communication with one or more corresponding air cavities of the plurality of cavities.

17. The integrated combustor nozzle as in claim 1, further comprising an outer impingement panel disposed along an outer surface of the outer liner segment, wherein the outer impingement panel defines a plurality of impingement holes, and wherein the outer impingement panel is radially spaced from the outer surface of the outer liner segment to form a cooling flow gap therebetween.

18. The integrated combustor nozzle as in claim 17, wherein the cooling flow gap is in fluid communication with a premix air plenum of the fuel injection panel.

19. The integrated combustor nozzle as in claim 17, wherein the outer impingement panel defines one or more openings in fluid communication with one or more corresponding air cavities of the plurality of cavities.

20. The integrated combustor nozzle as in claim 1, further comprising a mounting strut coupled to an outer surface of the outer liner segment, wherein the mounting strut includes a plurality of air inlet holes, and wherein the plurality of air inlet holes in the mounting strut is in fluid communication with at least one of the air cavities of the plurality of air cavities.

21. The integrated combustor nozzle as in claim 20, wherein the plurality of air inlet holes in the mounting strut is in fluid communication with a premix air plenum defined within the fuel injection panel.