A fuel nozzle is provided. The fuel nozzle includes a nozzle body, a plurality of swirler vanes, and at least one outlet. The nozzle body includes a back plate, a front plate, and a mixing zone defined therebetween. The back plate includes at least one inlet defined therein and the front plate inclu
A fuel nozzle is provided. The fuel nozzle includes a nozzle body, a plurality of swirler vanes, and at least one outlet. The nozzle body includes a back plate, a front plate, and a mixing zone defined therebetween. The back plate includes at least one inlet defined therein and the front plate includes at least one discharge defined therein. The plurality of swirler vanes are positioned between the back plate and the front plate and spaced circumferentially about the mixing zone. Each of the plurality of swirler vanes direct air obliquely into the mixing zone. The at least one outlet is defined within at least one of the nozzle body and the plurality of swirler vanes, the at least one outlet configured to inject fuel into said mixing zone.
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1. A method of assembling a gas turbine assembly, said method comprising: positioning a flow sleeve about a liner of a combustor, such that the flow sleeve extends circumferentially about the liner and defines a generally annular first plenum therebetween, wherein the liner at least partially define
1. A method of assembling a gas turbine assembly, said method comprising: positioning a flow sleeve about a liner of a combustor, such that the flow sleeve extends circumferentially about the liner and defines a generally annular first plenum therebetween, wherein the liner at least partially defines a combustion zone of the combustor and extends circumferentially about a centerline of the combustor;coupling a fuel nozzle to the combustor such that the fuel nozzle extends radially from at least the flow sleeve through the liner, wherein the fuel nozzle includes: a nozzle body that includes a back plate, a front plate, and a mixing zone defined therebetween, wherein the back plate includes at least one inlet defined therein and the front plate includes at least one discharge defined therein;a plurality of swirler vanes between the front plate and the back plate and circumferentially about the mixing zone such that the plurality of swirler vanes direct air obliquely into the mixing zone; andat least one outlet within at least one of the nozzle body and the plurality of swirler vanes, wherein the at least one outlet is configured to inject fuel into the mixing zone, wherein the back plate is directly coupled to the flow sleeve and the front plate is directly coupled to the liner such that a fuel-air mixture discharged from the fuel nozzle is directed generally radially towards the combustion zone relative to the centerline. 2. The method in accordance with claim 1 further comprising positioning the plurality of swirler vanes about the mixing zone such that a plurality of air flow passages are defined between adjacent swirler vanes, wherein each of the plurality of air flow passages are oriented obliquely with respect to a radial centerline of the nozzle body. 3. The method in accordance with claim 1 further comprising defining a gas fuel passage within at least one of the plurality of swirler vanes, wherein the gas fuel passage facilitates flow communication between the at least one inlet and the at least one outlet. 4. The method in accordance with claim 1 further comprising defining the at least one fuel outlet within a radially outer end of at least one of the plurality of swirler vanes. 5. The method in accordance with claim 1, wherein the nozzle body includes a centerbody, said method further comprising extending the centerbody from the back plate to at least partially within the mixing zone, wherein a fluid passage is defined within the centerbody, the fluid passage configured to facilitate flow communication between the at least one inlet and the at least one outlet. 6. A fuel nozzle for use with a combustor, said fuel nozzle comprising: a nozzle body comprising: a front plate configured to directly couple to a liner of the combustor, wherein the liner at least partially defines a combustion zone of the combustor and extends circumferentially about a centerline of the combustor;a back plate spaced from said front plate such that said back plate is configured to directly couple to a flow sleeve of the combustor, wherein the flow sleeve extends circumferentially about the liner and defines a generally annular first plenum therebetween, anda mixing zone defined between said back plate and said front plate, said back plate comprising at least one inlet defined therein, said front plate comprising at least one discharge defined therein;a plurality of swirler vanes positioned between said back plate and said front plate and spaced circumferentially about said mixing zone, each of said plurality of swirler vanes oriented to direct air obliquely into said mixing zone; andat least one outlet defined within at least one of said nozzle body and said plurality of swirler vanes, said at least one outlet configured to inject fuel into said mixing zone, wherein said fuel nozzle is configured to extend radially from at least the flow sleeve through the liner. 7. The nozzle in accordance with claim 6, wherein said at least one inlet comprises a gas fuel inlet and a liquid fuel inlet. 8. The nozzle in accordance with claim 7, wherein said gas fuel inlet is coupled in flow communication with said at least one outlet, wherein said at least one outlet is defined within at least one of said plurality of swirler vanes. 9. The nozzle in accordance with claim 6, wherein said at least one outlet is defined within a radially outer end of at least one of said plurality of swirler vanes. 10. The nozzle in accordance with claim 6, wherein at least one of said plurality of swirler vanes comprises a gas fuel passage defined therein, wherein said gas fuel passage channels fuel from said at least one inlet to said at least one outlet. 11. The nozzle in accordance with claim 6, wherein said nozzle body further comprises a centerbody extending from said back plate, said centerbody comprising a fluid passage defined therein that is coupled in flow communication with said at least one outlet, wherein said fluid passage is configured to channel liquid fuel therethrough when said centerbody is in a first operational mode. 12. The nozzle in accordance with claim 11, wherein said fluid passage is configured to channel air therethrough when said centerbody is in a second operational mode. 13. The nozzle in accordance with claim 6, wherein each of said plurality of swirler vanes comprises a centerline that is oriented obliquely with respect to a radial centerline of said nozzle body at an angle of from about 15° to about 60°. 14. The nozzle in accordance with claim 6, wherein each of said plurality of swirler vanes comprises a tear drop cross-sectional shape. 15. The nozzle in accordance with claim 6, wherein said plurality of swirler vanes are spaced about a centerline axis of said nozzle body such that a plurality of air flow passages are defined between adjacent swirler vanes, wherein each of said plurality of air flow passages are oriented obliquely with respect to a radial centerline of said nozzle body at an angle of from about 15° to about 60°. 16. A gas turbine assembly comprising: a combustor comprising: a liner at least partially defining a combustion zone and extending circumferentially about a centerline of said combustor; anda flow sleeve that extends circumferentially about said liner and defines a generally annular first air plenum therebetween; anda fuel nozzle coupled to said combustor such that said fuel nozzle extends radially from at least said flow sleeve through said liner, said fuel nozzle comprising: a nozzle body comprising a back plate, a front plate, and a mixing zone defined therebetween, said back plate comprising at least one inlet defined therein, said front plate comprising at least one discharge defined therein;a plurality of swirler vanes positioned between said back plate and said front plate and spaced circumferentially about said mixing zone, each of said plurality of swirler vanes oriented to direct air obliquely into said mixing zone; andat least one outlet defined within at least one of said nozzle body and said plurality of swirler vanes, said at least one outlet configured to inject fuel into said mixing zone, wherein said back plate is directly coupled to said flow sleeve and said front plate is directly coupled to said liner such that a fuel-air mixture discharged from said fuel nozzle is directed generally radially relative to the centerline towards said combustion zone. 17. The assembly in accordance with claim 16, wherein said fuel nozzle is configured such that air channeled through said first air plenum is channeled into said mixing zone of said fuel nozzle. 18. The assembly in accordance with claim 16, wherein said combustor further comprises a sheet positioned about said flow sleeve such that a second air plenum is defined therebetween.
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이 특허에 인용된 특허 (5)
Willis Jeffrey D,GBX, Combustion chamber comprising mixing ducts with fuel injectors varying in number and cross-sectional area.
Toon, Ian J.; O'Dell, Stephen J.; Currin, John H.; Willis, Jeffrey D., Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection.
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