Segmented annular combustion system with dual fuel capability

Patent metadata

Field	Value
Publication number	US-10830442-B2
Application number	US-201715464400-A
Country	US
Kind code	B2
Filing date	Mar 21, 2017
Priority date	Mar 25, 2016
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.

First claim

What is claimed is:

1. A fuel injection module, comprising: a bundled tube fuel nozzle portion including a plurality of tubes that extends through a fuel nozzle plenum defined within a housing body of the fuel injection module; a plurality of fuel injection lances in fluid communication with an injector fuel plenum defined within the housing body of the fuel injection module; a first conduit defining a first fuel passage in fluid communication with the plurality of fuel injection lances; a second conduit defining a second fuel passage in fluid communication with the fuel nozzle plenum; and at least one liquid fuel cartridge defined within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances, wherein the plurality of fuel injections lances are not in direct fluid communication with the plurality of tubes, wherein the first conduit comprises an outer conduit and the second conduit comprises an intermediate conduit disposed within the outer conduit, and wherein a third conduit is disposed within the intermediate conduit, a first liquid fuel cartridge of the at least one liquid fuel cartridge extending coaxially within the third conduit, wherein the at least one liquid fuel cartridge comprises a liquid fuel cartridge that extends axially within a respective fuel injection lance of the plurality of fuel injection lances.

2. The fuel injection module as in claim 1 , wherein at least one of the first conduit, the second conduit, and the third conduit is coupled to an end cover for a combustor.

3. The fuel injection module as in claim 1 , wherein the end cover defines one or more fuel circuits in fluid communication with at least one of the first conduit, the second conduit, and the third conduit.

4. The fuel injection module as in claim 1 , wherein the first liquid fuel cartridge of the at least one liquid fuel cartridge is configured to inject a liquid fuel downstream of respective outlets of each tube of the plurality of tubes.

5. The fuel injection module as in claim 4 , wherein a tip portion of the first liquid fuel cartridge projects axially downstream from an aft plate of the housing body, and wherein the tip portion includes a plurality of injection ports angled to inject a liquid fuel radially outwardly from the tip portion.

6. The fuel injection module as in claim 1 , wherein the first liquid fuel cartridge and the third conduit at least partially define an annular purge air passage therebetween.

7. The fuel injection module as in claim 1 , wherein the first liquid fuel cartridge is breech loaded through an opening defined in an end cover of a combustor, and wherein the end cover is configured to connect to a compressor discharge casing.

8. A gas turbine, comprising: a compressor; a compressor discharge casing disposed downstream from the compressor; a turbine disposed downstream from the compressor discharge casing; an annular combustion system disposed within the compressor discharge casing, the annular combustion system including a plurality of integrated combustor nozzles disposed in an annular array about an axial centerline of the gas turbine, wherein each integrated combustor nozzle includes a fuel injection panel having a downstream end portion defining a turbine nozzle portion accelerating a flow of combustion products into the turbine; and a plurality of fuel injection modules, wherein each fuel injection module of the plurality of fuel injection modules is disposed between a respective adjacent pair of integrated combustor nozzles of the plurality of integrated combustor nozzles upstream from a respective primary combustion zone defined therebetween, wherein at least one fuel injection module of the plurality of fuel injection modules comprises: a bundled tube fuel nozzle portion including a plurality of tubes that extends through a bundled tube fuel plenum defined within a housing body of the fuel injection module; a plurality of fuel injection lances in fluid communication with an injector fuel plenum defined within the housing body of the fuel injection module; a first conduit defining a first fuel passage in fluid communication the plurality of fuel injection lances; a second conduit defining a second fuel passage in fluid communication with the bundled tube fuel plenum; and at least one liquid fuel cartridge disposed, in each fuel injection module, within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances, wherein the plurality of fuel injections lances are not in direct fluid communication with the plurality of tubes, wherein the first conduit comprises an outer conduit and the second conduit comprises an intermediate conduit disposed within the outer conduit, and wherein a third conduit is disposed within the intermediate conduit, a first liquid fuel cartridge of the at least one liquid fuel cartridge extending coaxially within the third conduit, wherein the at least one liquid fuel cartridge comprises a liquid fuel cartridge that extends axially within a respective fuel injection lance of the plurality of fuel injection lances.

9. The gas turbine as in claim 8 , wherein at least one of the first conduit, the second conduit, and the third conduit of a first fuel injection module is coupled to an end cover for a combustor.

10. The gas turbine as in claim 9 , wherein the end cover defines one or more fuel circuits in fluid communication with at least one of the first conduit, the second conduit, and the third conduit of the first fuel injection module.

11. The gas turbine as in claim 10 , wherein the end cover defines one or more fuel circuits in fluid communication with at least one of the first conduit, the second conduit, and the third conduit of a second fuel injection module, and wherein the first fuel injection module and the second fuel injection module are disposed circumferentially around one of the plurality of integrated combustor nozzles.

12. The gas turbine as in claim 8 , wherein the first liquid fuel cartridge is configured to inject a liquid fuel downstream from respective outlets of each tube of the plurality of tubes.

13. The gas turbine as in claim 8 , wherein a tip portion of the first liquid fuel cartridge projects axially downstream from an aft plate of the housing body, and wherein the tip portion includes a plurality of injection ports angled to inject a liquid fuel radially outwardly from the tip portion.

14. The gas turbine as in claim 8 , wherein the first liquid fuel cartridge and the third conduit at least partially define an annular purge air passage therebetween.

Assignees

• Gen Electric

Inventors

• Berry Jonathan Dwight
• Widener Stanley Kevin
• Hughes Michael John
• Flanagan James Scott

Classifications

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title