Patent ID: 7722315

Claim:
A method of assembling a gas turbine engine, said method comprising: coupling a turbine shroud assembly within the gas turbine engine, wherein the turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface; coupling a turbine nozzle to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face; and defining a plurality of recuperated cooling openings through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge wherein defining further comprises defining a plurality of recuperated cooling opening groups, wherein each of the recuperated cooling opening groups includes a plurality of recuperated cooling openings having an aggregate cross-sectional area.