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A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition n

A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.

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1. A method of assembling a turbine assembly, said method comprising: integrally forming a transition nozzle including a transition portion and a turbine nozzle portion, wherein integrally forming includes manufacturing the transition nozzle as a unitary component such that the transition nozzle is

1. A method of assembling a turbine assembly, said method comprising: integrally forming a transition nozzle including a transition portion and a turbine nozzle portion, wherein integrally forming includes manufacturing the transition nozzle as a unitary component such that the transition nozzle is a monolithic piece, and wherein the turbine nozzle portion functions as a stage one turbine nozzle;orienting a plurality of openings in a sidewall of the transition nozzle to channel air across an inner surface of the transition nozzle to facilitate cooling at least one of the transition portion and the turbine nozzle portion, the transition nozzle including the plurality of openings; andorienting the transition portion to channel combustion gases downstream towards the turbine nozzle portion; andinjecting fuel through at least one secondary fuel injector coupled along an axial length of the transition nozzle. 2. A method in accordance with claim 1, wherein integrally forming a transition nozzle further comprises integrally forming the transition nozzle to include a liner portion such that the liner portion, the transition portion, and the turbine nozzle portion forms the unitary component, wherein the transition portion is oriented to channel combustion gases from the liner portion. 3. A method in accordance with claim 2, wherein orienting a plurality of openings further comprises: providing a first opening defined in a sidewall of the liner portion;providing a second opening defined in a sidewall of the transition portion; andproviding a third opening defined in a sidewall of the turbine nozzle portion, wherein the plurality of openings includes the first, second, and third openings. 4. A method in accordance with claim 2, wherein orienting a plurality of openings further comprises providing an opening defined in a sidewall of the liner portion, wherein the plurality of openings includes the opening. 5. A method in accordance with claim 1, wherein orienting a plurality of openings further comprises providing an opening defined in a sidewall of the transition portion, wherein the plurality of openings includes the opening. 6. A method in accordance with claim 1, wherein orienting a plurality of openings further comprises providing an opening defined in a sidewall of the turbine nozzle portion, wherein the plurality of openings includes the opening. 7. A transition nozzle for use with a turbine assembly, said transition nozzle comprising: a transition portion; anda turbine nozzle portion integrally formed with the transition portion, wherein said transition portion and said turbine nozzle portion are manufactured as a unitary component such that the transition nozzle is a monolithic piece, and wherein said turbine nozzle portion functions as a stage one turbine nozzle;a plurality of openings oriented in a sidewall of at least one of said transition portion and said turbine nozzle portion to channel air across an inner surface of said transition nozzle to facilitate cooling at least one of said transition portion and said turbine nozzle portion, wherein said transition portion is oriented to channel combustion gases downstream towards said turbine nozzle portion; andat least one secondary fuel injector coupled along an axial length of the transition nozzle. 8. A transition nozzle in accordance with claim 7 further comprising a liner portion integrally formed with said transition and turbine nozzle portions to form said unitary component, wherein said transition portion is oriented to channel combustion gases from said liner portion. 9. A transition nozzle in accordance with claim 8, wherein said liner portion is configured to receive a fuel and air mixture at a plurality of locations along an axial length of said liner portion. 10. A transition nozzle in accordance with claim 8, wherein the plurality of openings includes a first opening extending through a sidewall of said liner portion, a second opening extending through said sidewall of said transition portion, and a third opening extending through said sidewall of said turbine nozzle portion. 11. A transition nozzle in accordance with claim 8, wherein at least one of the plurality of openings extends through a sidewall of said liner portion. 12. A turbine assembly comprising: a primary fuel nozzle configured to mix fuel and air to create a fuel and air mixture; anda transition nozzle oriented to receive the fuel and air mixture from said fuel nozzle, said transition nozzle comprising a transition portion and a turbine nozzle portion, wherein said transition portion and said turbine nozzle portion are manufactured as a unitary component such that the transition nozzle is a monolithic piece, and said transition nozzle includes a sidewall including a plurality of openings oriented to channel air across an inner surface of said transition nozzle to facilitate cooling at least one of said transition portion and said turbine nozzle portion,wherein said transition portion is oriented to channel combustion gases downstream towards said turbine nozzle portion, and wherein said turbine nozzle portion functions as a stage one turbine nozzle; andat least one secondary fuel injector coupled along an axial length of the transition nozzle downstream of said primary fuel nozzle, wherein said secondary fuel injector is configured to inject additional fuel to the fuel and air mixture. 13. A turbine assembly in accordance with claim 12, wherein said transition nozzle further comprises a liner portion integrally formed with said transition and turbine nozzle portions to form said unitary component, wherein said transition portion is oriented to channel combustion gases from said liner portion. 14. A turbine assembly in accordance with claim 13, wherein said liner portion is configured to receive the fuel and air mixture at a plurality of locations along an axial length of said liner portion. 15. A turbine assembly in accordance with claim 13, wherein the plurality of openings includes a first opening extending through a sidewall of said liner portion, a second opening extending through a sidewall of said transition portion, and a third opening extending through a sidewall of said turbine nozzle portion. 16. A turbine assembly in accordance with claim 13, wherein at least one of the plurality of openings extends through a sidewall of said liner portion. 17. A turbine assembly in accordance with claim 12, wherein at least one of the plurality of openings extends through a sidewall of said transition portion. 18. A turbine assembly in accordance with claim 12, wherein at least one of the plurality of openings extends through a sidewall of said turbine nozzle portion.