Patent ID: 7588412
Filing Date: 2009-09-15
Classification: F01D,Y02T

Abstract:
1. A cooled shroud assembly for a gas turbine engine having a longitudinal centerline, said shroud assembly comprising: at least one arcuate shroud segment surrounding a row of rotating turbine blades, said shroud segment having a forward flange, an aft flange defining an axially-facing aft edge, and an inwardly-facing flowpath surface, wherein said shroud segment lacks cooling holes for cooling said aft flange; and at least one stationary turbine nozzle disposed axially next to said shroud segment, comprising: an airfoil; and an arcuate outer band disposed at a radially outer end of said airfoil and positioned axially adjacent to said shroud; wherein a plurality of cooling holes including at least a first cooling hole and at least a second cooling hole are formed in said outer band and in fluid communication with a source of cooling air, said first cooling hole and said second cooling hole being positioned so as to impinge a flow of cooling air against said shroud segment and such that said first cooling hole and said second cooling hole converge at about the same place on said shroud segment.