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A compliant shim for use between the root of a gas turbine fan blade and a dovetail groove in a gas turbine rotor disk to reduce fretting therebetween. The compliant shim has first and second slots for engaging tabs extending from the fan blade root. The slots and tabs cooperate to hold the shim dur

A compliant shim for use between the root of a gas turbine fan blade and a dovetail groove in a gas turbine rotor disk to reduce fretting therebetween. The compliant shim has first and second slots for engaging tabs extending from the fan blade root. The slots and tabs cooperate to hold the shim during engine operation. An oxidation layer covers the compliant shim.

대표청구항 ▼

1. A rotor assembly for a gas turbine engine, comprising:a disk having along its periphery at least one dovetail groove; a blade having an airfoil portion and a root portion, said root portion contoured to be received within said dovetail groove and having an inner surface that extends axially from

1. A rotor assembly for a gas turbine engine, comprising:a disk having along its periphery at least one dovetail groove; a blade having an airfoil portion and a root portion, said root portion contoured to be received within said dovetail groove and having an inner surface that extends axially from a leading edge to a trailing edge, said inner surface having first and second tab members extending inward therefrom to define a gap between said inner surface and a base of said groove; and a compliant shim disposed in said gap and having a first slot for engaging said first tab and a second slot for engaging said second tab.