Patent ID: 6398485
Filing Date: 2002-06-04
Classification: F01D,Y02T

Abstract:
A stator stage for cooling high and low pressure rotor discs of a gas turbine, comprising:a turbine housing; an annular array of nozzle segments carried by said turbine housing, each said nozzle segment including a plurality of airfoils; an outer ring carried by said housing adjacent an outer margin of each nozzle segment and defining with said housing a chamber for containing cooling air; an inner ring carried by said housing, said nozzle segments being disposed between said outer ring and said inner ring; at least one airfoil of each nozzle segment having a passage in communication between said chamber and a location adjacent said high and low pressure discs for supplying cooling air from said chamber to said location to cool said discs; said outer ring having an additional mobile ring movable to compensate for differential thermal expansion between said housing and said outer ring.