Patent ID: 6375415
Filing Date: 2002-04-23
Classification: F01D

Abstract:
A nozzle stage segment for a gas turbine, comprising:inner and outer bands spaced generally radially from one another and a nozzle vane extending between said bands, said nozzle vane having leading and trailing edges, said inner band and said nozzle vane being cantilevered radially inwardly from said outer band; said outer band including a wall for defining a portion of a hot gas flow path through the turbine and an outer cover radially outwardly of said wall defining a chamber with said wall for forming part of a closed loop cooling circuit through said nozzle stage segment, said cover having an inlet for flowing a cooling medium into said chamber; said outer cover having a generally axially forwardly directed hook for structurally attaching the nozzle stage segment to a support on the turbine.