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A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further include

A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.

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1. A method for assembling a gas turbine engine, said method comprising: coupling a transition piece between a combustor liner and a nozzle assembly;extending a first portion of a flow sleeve from the transition piece to circumscribe at least a portion of the combustor liner; andcoupling a second po

1. A method for assembling a gas turbine engine, said method comprising: coupling a transition piece between a combustor liner and a nozzle assembly;extending a first portion of a flow sleeve from the transition piece to circumscribe at least a portion of the combustor liner; andcoupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the second portion extends axially from the first portion and at least partially about at least a portion of the transition piece, wherein the second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening, wherein the scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece, and wherein the scoop extends from a radially outermost portion of the second portion of the flow sleeve, relative to a longitudinal axis extending through the gas turbine engine wherein the scoop-shaped opening is formed at a radially innermost portion of the transition piece. 2. A method in accordance with claim 1 wherein coupling a second portion of the flow sleeve to the first portion of the flow sleeve further comprises coupling the scoop in flow communication with a cooling air source. 3. A method in accordance with claim 1 wherein coupling the second portion of the flow sleeve to the first portion of the flow sleeve comprises welding at least a portion of the flow sleeve first portion to at least a portion of the flow sleeve second portion. 4. A method in accordance with claim 3 wherein welding at least a portion of the flow sleeve first portion to at least a portion of the second portion comprises welding at least a portion of an attachment ring to the flow sleeve first portion. 5. A method in accordance with claim 1 wherein coupling a second portion of the flow sleeve to the first portion of the flow sleeve comprises positioning the unitary cooling air passage about at least a top portion of the transition piece. 6. A method in accordance with claim 1 wherein coupling a second portion of the flow sleeve to the first portion of the flow sleeve comprises extending at least a portion of the scoop about at least a side portion of the transition piece such that at least a portion of the scoop extends below a predetermined portion of the transition piece side portion. 7. A combustor assembly for use with a turbine engine, said combustor assembly comprising: a combustor liner coupled in flow communication with a transition piece; anda flow device comprising: a first portion sized to circumscribe at least a portion of said combustor liner; anda second portion coupled to and extending axially from said flow device first portion, said flow device second portion at least partially extends about at least a portion of said transition piece, wherein said flow device second portion comprises a scoop that cooperates with said transition piece to define a unitary cooling air passage including a unitary scoop-shaped opening such that said scoop is oriented to introduce a substantially uniform cooling air flow to said transition piece, and wherein the scoop extends from a radially outermost portion of the second portion of the flow device, relative to a longitudinal axis extending through the turbine engine wherein the scoop-shaped opening is formed at a radially innermost portion of the transition piece. 8. A combustor assembly in accordance with claim 7 wherein at least a portion of said flow device first portion is welded to at least a portion of said flow device second portion. 9. A combustor assembly in accordance with claim 8 wherein said flow device second portion comprises an attachment ring. 10. A combustor assembly in accordance with claim 9 wherein at least a portion of said attachment ring is welded to the at least a portion of said flow device first portion. 11. A combustor assembly in accordance with claim 7 wherein said flow device extends from a portion of said combustor liner to a nozzle assembly of the turbine engine. 12. A combustor assembly in accordance with claim 7 wherein said transition piece comprises a top portion and the unitary cooling air passage and the unitary scoop-shaped opening are oriented to extend over said transition piece top portion. 13. A combustor assembly in accordance with claim 7 wherein said scoop is coupled in flow communication with a cooling air source. 14. A gas turbine engine comprising: a transition piece extending in flow communication between a combustor liner and a nozzle assembly; anda flow device comprising: a first portion sized to circumscribe at least a portion of said combustor liner; anda second portion coupled to and extending axially from said flow device first portion, said flow device second portion at least partially extends about at least a portion of said transition piece, wherein said flow device second portion comprises a scoop that cooperates with said transition piece to define a unitary cooling air passage including a unitary scoop-shaped opening such that said scoop is oriented to introduce a substantially uniform cooling air flow to said transition piece, and wherein the scoop extends from a radially outermost portion of the second portion of the flow device, relative to a longitudinal axis extending through the gas turbine engine wherein the scoop-shaped opening is formed at a radially innermost portion of the transition piece. 15. A gas turbine engine in accordance with claim 14 wherein at least a portion of said flow device first portion is welded to at least a portion of said flow device second portion. 16. A gas turbine engine in accordance with claim 15 wherein said flow device second portion comprises an attachment ring. 17. A gas turbine engine in accordance with claim 16 wherein at least a portion of said attachment ring is welded to at least a portion of said flow device first portion. 18. A gas turbine engine in accordance with claim 14 wherein said flow device extends from a portion of said combustor liner to said nozzle assembly. 19. A gas turbine engine in accordance with claim 14 wherein said transition piece comprises a top portion and the unitary cooling air passage and the unitary scoop-shaped opening are oriented to extend over said transition piece top portion. 20. A gas turbine engine in accordance with claim 14 wherein said scoop is coupled in flow communication with a cooling air source.