Patent ID: 6413040
Filing Date: 2002-07-02
Classification: F01D,F05B,F05D

Abstract:
For use in a gas turbine, a nozzle segment having outer and inner band portions and at least one vane extending between said band portions, at least one of said band portions including a nozzle wall defining in part a hot gas path through the turbine, a cover radially spaced from said nozzle wall, said cover and said nozzle wall being secured to one another about margins thereof and defining a chamber therebetween, at least one structural element interconnecting said cover and said nozzle wall inwardly of said margins to substantially prevent movement of said cover and said nozzle wall relative to one another in a generally radial direction, 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 impingement plate including a hole therethrough for receiving said structural element.