Operation and Turndown of a Segmented Annular Combustion System

• US 20170276359A1
• Filed: 03/21/2017
• Published: 09/28/2017
• Est. Priority Date: 03/25/2016
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Berry, Jonathan Dwight, Hughes, Michael John
• Granted Patent: US 10,563,869 B2
• Time in Patent Office: Days
• CPC Class Codes: F23R 3/346 for staged combustion

Abstract

The present disclosure is directed to the operation and turndown of a segmented annular combustion system. The method includes injecting, via a fuel nozzle, a combustible mixture into a primary combustion zone between an adjacent pair of integrated combustor nozzles and burning the combustible mixture. The method further includes flowing air and injecting fuel into a premixing channel defined within a first integrated combustor nozzle to produce a second combustible mixture. The second combustible mixture is injected into a secondary combustion zone where it is combusted. The flow of combustion gases is accelerated, via turbine nozzles of the integrated combustor nozzles, toward turbine blades of a downstream turbine section. The method permits turndown of the combustion system by reducing or shutting off fuel to various components of the combustion system.

Claims

1. A method for operating a segmented annular combustion system, comprising:

injecting a first combustible mixture into a primary combustion zone defined between a pair of circumferentially adjacent integrated combustor nozzles of the segmented annular combustion system via a fuel nozzle;

burning the first combustible mixture in the primary combustion zone to produce a flow of combustion gases;

flowing compressed air into a first premixing channel defined within a first integrated combustor nozzle of the pair of circumferentially adjacent integrated combustor nozzles;

injecting fuel into the first premixing channel such that the fuel mixes with the compressed air to provide a second combustible mixture;

injecting the second combustible mixture from the first premixing channel into a secondary combustion zone downstream from the primary combustion zone, the second combustible mixture burning in the secondary combustion zone and combining with the flow of combustion gases from the primary combustion zone; and

accelerating the flow of combustion gases toward a plurality of turbine blades, via a turbine nozzle portion of each integrated combustor nozzle.

2. The method as in claim 1, further comprising igniting the first combustible mixture prior to burning the first combustible mixture in the primary combustion zone, the igniting being accomplished by an igniter adjacent the fuel nozzle.

3. The method as in claim 1, wherein the injecting a first combustible mixtures into a primary combustion zone occurs before the injecting of fuel into the first premixing channel.

4. The method as in claim 1, wherein the pair of circumferentially adjacent integrated combustor nozzles are two of a plurality of integrated combustor nozzles defining the segmented annular combustion system, and wherein each circumferentially adjacent pair of integrated combustor nozzles of the plurality of integrated combustor nozzles defines therebetween a respective primary combustion zone upstream of a respective fuel nozzle and a respective secondary combustion zone downstream of the primary combustion zone.

5. The method as in claim 4, further comprising propagating ignition around the segmented annular combustion system via cross-fire tubes defined in each respective integrated combustor nozzle.

6. The method as in claim 4, wherein the first premixing channel of each integrated combustor nozzle is one of a first plurality of premixing channels in each integrated combustor nozzle, and wherein flowing compressed air into the first premixing channel comprises flowing compressed air into the first plurality of premixing channels of each integrated combustor nozzle, and wherein injecting fuel into the first premixing channel comprises injecting fuel into the first plurality of premixing channels of each integrated combustor nozzle via a respective fuel injection lance.

7. The method as in claim 6, wherein injecting the second combustible mixture into the secondary combustion zone defined between each circumferentially adjacent pair of integrated combustor nozzles comprises injecting the second combustible mixture from the first plurality of premixing channels in a radial plane.

8. The method as in claim 6, further comprising reducing fuel flow to one or more of the first plurality of premixing channels in one or more of the plurality of integrated combustor nozzles.

9. The method as in claim 8, wherein reducing fuel flow to one or more of the first plurality of premixing channels in one or more of the plurality of integrated combustor nozzles comprises reducing fuel flow to one or more of the first plurality of premixing channels in two integrated combustor nozzles of the plurality of integrated combustor nozzles, and wherein the two integrated combustor nozzles are circumferentially separated.

10. The method as in claim 6, further comprising shutting off fuel flow to one or more of the first plurality of premixing channels in one or more of the plurality of integrated combustor nozzles.

11. The method as in claim 10, further comprising shutting off fuel flow to each premixing channel of the first plurality of premixing channels in one or more of the plurality of integrated combustor nozzles.

12. The method as in claim 11, wherein shutting off fuel flow to each premixing channel of the first plurality of premixing channels in one or more of the plurality of integrated combustor nozzles comprises shutting off fuel flow to each premixing channel of the first plurality of premixing channels in two integrated combustor nozzles of the plurality of integrated combustor nozzles, and wherein the two integrated combustor nozzles are circumferentially separated.

13. The method as in claim 11, further comprising shutting off fuel flow to each premixing channel of the first plurality of premixing channels in each integrated combustor nozzle of the plurality of integrated combustor nozzles.

14. The method as in claim 4, further comprising reducing fuel flow to at least one respective fuel nozzle upstream of at least one of the primary combustion zones.

15. The method as in claim 6, further comprising:

flowing compressed air into a second premixing channel defined within a second integrated combustor nozzle of the pair of circumferentially adjacent integrated combustor nozzles;

injecting fuel into the second premixing channel such that the fuel mixes with the compressed air to provide a third combustible mixture, and

injecting the third combustible mixture from the second premixing channel into the flow of combustion gases in the secondary combustion zone.

16. The method as in claim 15, wherein the pair of circumferentially adjacent integrated combustor nozzles are two of a plurality of integrated combustor nozzles defining the segmented annular combustion system, wherein each circumferentially adjacent pair of integrated combustor nozzles of the plurality of integrated combustor nozzles defines therebetween a respective primary combustion zone upstream of a respective fuel nozzle and a respective secondary combustion zone downstream of the primary combustion zone, and wherein each integrated combustor nozzle comprises a second premixing channel injecting the third combustible mixture into a respective secondary combustion zone.

17. The method as in claim 16, wherein the second premixing channel of each integrated combustor nozzle is one of a second plurality of premixing channels, and wherein flowing compressed air into the second premixing channel comprises flowing compressed air into the second plurality of premixing channels of each integrated combustor nozzle, and wherein injecting fuel into the second premixing channel comprises injecting fuel into the second plurality of premixing channels of each integrated combustor nozzle via a respective fuel injection lance.

18. The method as in claim 17, wherein injecting the third combustible mixture into the secondary combustion zone comprises injecting the third combustible mixture from the second plurality of premixing channels in a radial plane.

19. The method as in claim 17, further comprising reducing fuel flow to one or more of the second plurality of premixing channels in one or more of the plurality of integrated combustor nozzles.

20. The method as in claim 19, wherein reducing fuel flow to one or more of the second plurality of premixing channels in one or more of the plurality of integrated combustor nozzles comprises reducing fuel flow to one or more of the second plurality of premixing channels in two integrated combustor nozzles of the plurality of integrated combustor nozzles, and wherein the two integrated combustor nozzles are circumferentially separated.

21. The method as in claim 16, further comprising shutting off fuel flow to one or more of the second plurality of premixing channels in one or more of the plurality of integrated combustor nozzles.

22. The method as in claim 21, further comprising shutting off fuel flow to each of the second plurality of premixing channels in each of the plurality of integrated combustor nozzles.

23. The method as in claim 22, wherein shutting off fuel flow to each premixing channel of the second plurality of premixing channels in one or more of the plurality of integrated combustor nozzles comprises shutting off fuel flow to each premixing channel of the second plurality of premixing channels in two integrated combustor nozzles of the plurality of integrated combustor nozzles, and wherein the two integrated combustor nozzles are circumferentially separated.

24. The method as in claim 22, further comprising shutting off fuel flow to each premixing channel of the second plurality of premixing channels in each integrated combustor nozzle of the plurality of integrated combustor nozzles.

25. The method as in claim 19, further comprising reducing fuel flow to at least one respective fuel nozzle upstream of a respective primary combustion zone.

26. The method as in claim 17, further comprising reducing fuel flow the first plurality of premixing channels and then reducing fuel flow to the second plurality of premixing channels in each integrated combustor nozzle of the plurality of integrated combustor nozzles.

27. The method as in claim 17, further comprising simultaneously reducing fuel flow to the first plurality of premixing channels and to the second plurality of premixing channels in each integrated combustor nozzle of the plurality of integrated combustor nozzles.

28. The method as in claim 17, further comprising shutting off fuel flow the first plurality of premixing channels in each integrated combustor nozzle and then shutting off fuel flow to the second plurality of premixing channels in each integrated combustor nozzle.

29. The method as in claim 17, further comprising simultaneously shutting off fuel flow to both the first plurality of premixing channels in each integrated combustor nozzle and the second plurality of premixing channels in each integrated combustor nozzle.

30. The method as in claim 1, wherein the fuel nozzle defines a first fuel plenum and a second fuel plenum therein, and the method further comprises reducing fuel flow to the first fuel plenum of the fuel nozzle.