Patent ID: 7785067

Claim:
A method of assembling a gas turbine engine, said method comprising: coupling at least one turbine nozzle segment within the gas turbine engine, wherein the at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface, each turbine nozzle outer band aft flange comprising cooling holes defined therein; coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, each shroud assembly leading edge comprising cooling holes defined therein; and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment, wherein said coupling further comprises positioning each of the cooling holes defined within each turbine nozzle outer band aft flange in substantial alignment with a corresponding cooling hole defined in the shroud assembly leading edge.