Patent ID: 6331096
Filing Date: 2001-12-18
Classification: F01D,F05D

Abstract:
For use in a gas turbine, a nozzle segment having outer and inner bands and at least one vane extending between said bands, at least one of said bands including a nozzle wall defining in part a hot gas path through the turbine, a cover radially spaced from said nozzle wall defining a chamber therebetween and an impingement plate secured within said segment and disposed in said chamber to define with said cover a first cavity on one side thereof for receiving a cooling medium, said impingement plate on an opposite side thereof from said first cavity defining with said nozzle wall a second cavity, said impingement plate having a plurality of apertures therethrough for flowing the cooling medium from said first cavity into said second cavity for impingement cooling said nozzle wall, said nozzle segment including a side wall extending generally radially between said nozzle wall and said cover and having an inturned flange spaced from said nozzle wall, said inturned flange defining with said nozzle wall and said side wall an undercut region adjacent said side wall, and a plurality of apertures through said inturned flange for flowing the cooling medium from said first cavity for impingement cooling the side wall in the undercut region.