Patent ID: 6341938
Filing Date: 2002-01-29
Classification: F01D,F05D,Y02T

Abstract:
A method for assembling a gas turbine engine including a low pressure turbine including a rotor and at least one shroud, the low pressure turbine disposed radially inward from the shroud, the shroud including a plurality of shroud segments, each of the shroud segments including a backplate and abradable material attached to the backplate, the backplate including an inner surface, an outer surface, an upstream end, a downstream end, and a body extending between the upstream end and the downstream end, the inner surface and the outer surface extending over the backplate, the backplate body having a first portion and a second portion, the first portion extending from the upstream end to the body second portion, the second portion extending from the body first portion to the backplate downstream end, said method comprising the steps of:fabricating a plurality of backplates wherein each backplate body first portion has a first thickness and each backplate body second portion has a second thickness; attaching abradable material to the inner surface of each backplate to form an interface with the rotor; assembling the shroud segments to form an annular array disposed radially outward from the low pressure turbine rotor.