Patent ID: 6733233
Filing Date: 2004-05-11
Classification: F01D,F05D,Y02T

Abstract:
A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising:an annular ceramic shroud ring, circumferentially disposed about radially extending blades of a turbine rotor and partially defining an annular hot gas passage of said turbine portion; a plurality of arcuate shroud support segments, radially disposed outwardly of said ceramic shroud ring and contiguous therewith; a plurality of inwardly biased resilient members, each engaged between one of said shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than said ceramic shroud ring, said resilient members maintaining contact between said shroud support segments and said ceramic shroud ring; and said shroud supporting segments and said resilient members being adapted to deflect to compensate for relative thermal growth differences between said ceramic shroud ring and said turbine support case.