Patent ID: 7811054
Filing Date: 2010-10-12
Classification: F01D,F05D

Abstract:
1. 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 the 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 groove along said trailing edge opening in an axially upstream direction; said inner shroud having a leading edge axially projecting hook portion and a trailing edge axially projecting hook portion for respectively engaging said grooves of said outer shroud, said engagement axially and radially locking said inner shroud to said outer shroud; and wherein at least one of said trailing edge hook of said inner shroud and said trailing edge groove of said outer shroud includes a sloped surface disposed at an angle to an axial direction of said rotor and to a radial direction of said rotor and facing the other of said inner shroud and outer shroud whereby a radial inward force on said inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between said inner and outer shrouds.