Patent ID: 7442004

Claim:
A shroud assembly for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof, said shroud assembly comprising: at least one arcuate shroud segment adapted to surround a row of rotating turbine blades, said shroud segment having an arcuate, axially extending mounting flange; a shroud hanger having an arcuate, axially-extending hook disposed in mating relationship to said mounting flange; and an arcuate C-clip having inner and outer arms overlapping said mounting flange and said hook respectively; wherein the mating relationship is disposed at a medial location of said flange and said hook at the cold assembly condition, said mounting flange and the inner arm of said C-clip define a radial gap therebetween at the cold assembly condition, said shroud segment and said C-clip are subject to thermal expansion at said hot operating condition such that said shroud segment expands circumferentially thereby reducing the radial gap, and a dimension of said C-clip is selected to produce a preselected dimensional relationship between said shroud segment and said C-clip at said hot operating condition.