Patent ID: 6814538
Filing Date: 2004-11-09
Classification: F01D,F05D,Y10T

Abstract:
A stator shroud of a multi-stage gas turbine comprising:a shroud segment having a surface for, in part, defining a hot gas path through one stage and overlaying tips of buckets of said one stage forming part of a turbine rotor, said shroud segment having a leading, upstream edge and a trailing, downstream edge; said shroud segment comprising an outer shroud and at least one inner shroud connected thereto; said outer shroud having a groove defined adjacent and along each of said leading and trailing edges thereof, said grooves opening axially in a same direction; said inner shroud having a leading edge axially projecting tab portion and a trailing edge axially projecting tab portion for respectively engaging said grooves of said outer shroud, said engagement axially and radially locking said inner shroud to said outer shroud; and an anti-rotation pin extending through a bore defined in said outer shroud into a corresponding receptacle defined in said inner shroud to circumferentially lock said inner shroud to said outer shroud, said bore being defined through the outer shroud so that the pin is accessible for removal from the outer shroud when the inner shroud is radially locked to said outer shroud.