Patent ID: 6343911
Filing Date: 2002-02-05
Classification: F01D,F05D

Abstract:
For use in a gas turbine, a nozzle segment having a band portion including a nozzle wall defining in part a hot gas path through the turbine, a cover spaced from said nozzle wall defining a chamber therebetween and an impingement plate disposed in said chamber defining with said cover a first cavity on one side of said impingement plate for receiving a cooling medium, said impingement plate on an opposite side thereof defining with said nozzle wall a second cavity, said impingement plate having a plurality of apertures for flowing cooling medium from said first cavity into said second cavity for impingement cooling said nozzle wall, said nozzle segment including a side wall including an inturned flange extending along said side wall defining with said side wall and nozzle wall an undercut region, and means projecting into said undercut region and toward said side wall for receiving cooling medium from said first cavity, said projecting means having a plurality of apertures therethrough for flowing cooling medium from said first cavity into said undercut region for impingement cooling a portion of said nozzle side wall.