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In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a flu

In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.

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The invention claimed is: 1. A method of protecting a liquid fuel nozzle used in a dual-fuel gas turbine having a compressor, a combustor, and a turbine, the method comprising: flowing one of liquid fuel and purge air via a fuel passageway into the combustor; flowing atomizing air into the combusto

The invention claimed is: 1. A method of protecting a liquid fuel nozzle used in a dual-fuel gas turbine having a compressor, a combustor, and a turbine, the method comprising: flowing one of liquid fuel and purge air via a fuel passageway into the combustor; flowing atomizing air into the combustor via a first passageway having a first swirler; and interconnecting said first passageway with a second passageway having a second swirler, said first passageway disposed adjacent to said second passageway, via a conduit connected at a location upstream of the first swirler and downstream of the second swirler, to enable fluid flow therebetween to protect the nozzle from ingestion of hot combustor gases. 2. The method according to claim 1 further comprising: flowing said atomizing air into the combustor via said second passageway from an air source without a dedicated purge air system for said second passageway. 3. The method according to claim 2 further comprising: flowing water into the combustor via said second passageway wherein said flowing of said atomizing air via said second passageway from said air source without said dedicated purge air system for said second passageway reduces a risk of combustor flame-out due to excessive rapid introduction of said water into the combustor. 4. The method according to claim 2 further comprising: flowing water into the combustor via said second passageway wherein when an operation of the turbine switches from liquid fuel to gaseous fuel, any said water downstream of said second swirler disposed in said second passageway is atomized by the atomizing air prior to entering the combustor. 5. A method for operating a dual fuel gas turbine having a combustor, a compressor and a turbine, the method comprising: supplying liquid fuel to the combustor via a nozzle having a plurality of passageways, a first one of said passageways being a water injection passageway; interconnecting said water injection passageway to a second one of said plurality of passageways via a conduit to enable fluid flow therebetween, said second one of the plurality of passageways flowing high pressure air; and protecting the nozzle from ingestion of backflow combustion gases by diverting high pressure air from the second one of said plurality of passageways into said water injection passageway via said conduit. 6. The method according to claim 5 further comprising: flowing said high pressure air into the combustor via said water injection passageway from an air source without a dedicated purge air system for said water injection passageway. 7. The method according to claim 6 further comprising: flowing water into the combustor via said water injection passageway wherein said flowing of said high pressure air via said water injection passageway from said air source without said dedicated purge air system for said water injection passageway reduces a risk of combustor flame-out due to excessive rapid introduction of said water into the combustor. 8. The method according to claim 6 further comprising: flowing water into the combustor via said water injection passageway wherein when an operation of the turbine switches from liquid fuel to gaseous fuel, any said water downstream of a first swirler disposed in the water injection passageway is atomized by the atomizing air prior to entering the combustor. 9. In a dual-fuel gas turbine having a compressor, a combustor, and a turbine, a method of protecting a liquid fuel nozzle from ingestion of backflow combustion gases, the method comprising: flowing water into the combustor via a water injection passageway having a first swirler; flowing high pressure air into the combustor via a first passageway a second swirler; and interconnecting said first passageway and the water injection passageway via a conduit connected at a location upstream of the second swirler and downstream of the first swirler, to direct flow of high pressure air from said first passageway to said water injection passageway into the combustor. 10. In a gas turbine having a compressor, a combustor and a turbine, a liquid fuel unit for flowing liquid fuel into the combustor via a nozzle assembly, the nozzle assembly comprising: passageways for flowing a liquid fuel, water and high pressure air, respectively, into the combustor; a conduit interconnecting said water passageway and said high pressure air passageway enabling diversion of at least a portion of the high pressure air flow from said high pressure air passageway into said water passageway via said conduit to protect the nozzle from ingestion of hot combustor gases; a first swirler arranged in the water passageway; and a first end of said conduit being coupled to said water passageway downstream of said first swirler and an opposite second end of said conduit being in communication with the high pressure air passageway, the first end or said conduit being in communication with said water passageway downstream of said first swirler. 11. A nozzle assembly according to claim 10, including a second swirler disposed in the high pressure air passageway, the second end of said conduit being in communication with said high pressure air passageway upstream of said second swirler. 12. A liquid fuel nozzle assembly for supplying liquid fuel to a combustor of a gas turbine, the nozzle assembly comprising: a water injection passageway for flowing water into the combustor; an air passageway disposed adjacent to the water injection passageway for flowing atomizing air into the combustor, the water injection passageway and the atomizing air passageway being interconnected by a conduit to enable flow therebetween to protect the nozzle from ingestion of hot combustor gases; a first swirler unit disposed in said water injection passageway; a second swirler unit disposed in said air atomizing passageway, said first and second swirler units disposed proximate an exit of said respective water injection passageway and atomizing air passageways, said first and second swirler units acting as primary pressure drops in the respective passageways; a first end of said conduit being in communication with said water injection passageway at a location downstream of said first swirler unit and an opposite second end of said conduit being in communication with said atomizing air passageway at a location upstream of said second swirler unit. 13. A nozzle assembly according to claim 12 wherein the atomizing air passageway is maintained at a higher pressure than the water injection passageway. 14. The nozzle assembly according to claim 12 wherein said conduit allows for eliminating a dedicated purge air system for the second passageway. 15. The nozzle assembly according to claim 14 wherein said eliminating said dedicated purge air system for the second passageway reduces a risk of combustor flame-out due to excessive rapid water introduction into the combustor. 16. The nozzle assembly according to claim 14 wherein when an operation of the turbine switches from liquid fuel to gaseous fuel, any water downstream of the first swirler in the water injection passageway is atomized by the atomizing air prior to entering the combustor. 17. In a dual-fuel gas turbine baying a compressor, a combustor and a turbine, a method of passively protecting a liquid fuel nozzle, the method comprising: flowing a liquid fuel, water, and atomizing air into the combustor via respective nozzle passageways; coupling said water and said atomizing air passageways to one another via a conduit; diverting at least a portion of high pressure air from said atomizing air passageway into said water passageway to protect the nozzle from ingestion of hot combustor gases; disposing first and second swirler units for said water and atomizing air passageways, respectively, adjacent exit ends thereof; coupling a first end of said conduit to said water passageway at a location downstream of said first swirler unit in the water passageway; and coupling an opposite second end of said conduit to said atomizing air passageway at a location upstream of a second swirler unit in said atomizing air passageway.