Cooled shroud assembly and method of cooling a shroud

摘要

A cooled shroud assembly for a gas turbine engine having a longitudinal centerline includes at least one arcuate shroud segment (30) surrounding a row of rotating turbine blades (16). The shroud segment (30) has a forward flange (48), an aft flange (50) defining an axially-facing aft edge (52), and an inwardly-facing flowpath surface (47), and the shroud segment (30) lacks cooling holes (72) for cooling the aft flange (50) or the aft edge. At least one stationary turbine nozzle (28) is disposed axially next to the shroud segment (30) and includes an airfoil-shaped airfoil (34) and an arcuate outer band (36) disposed at a radially outer end of the airfoil (34) and positioned axially adjacent to the shroud. At least one cooling hole (72) is formed in the outer band (36) in fluid communication with a source of cooling air. The cooling hole (72) is positioned so as to direct a flow of cooling air against the shroud segment (30).