Patent ID: 8397512

Claim:
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; and coupling 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.