Patent ID: 7448846
Filing Date: 2008-11-11
Classification: F01D

Abstract:
1. A shroud assembly for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition, said shroud assembly comprising: a supporting structure having an arcuate, axially-extending first hook with a first radius of curvature at a cold assembly condition; at least one arcuate shroud segment adapted to surround a row of rotating turbine blades, said shroud segment including: a first interface disposed between said first overhang and said first hook; a second interface disposed between said first mounting flange and said first hook; wherein a selected one of said second and third radii of curvature is substantially different from both the other one of said second and third radii of curvature and said first radius of curvature, such that a first gap is positioned at one of said first and second interface and said shroud hanger is subject to thermal expansion at the hot operating condition so that said shroud assembly expands circumferentially, thereby reducing the first gap.