Patent ID: 6398499
Filing Date: 2002-06-04
Classification: F01D,F05C,F05D

Abstract:
A rotor assembly for a gas turbine engine, comprising:a disk having along its periphery at least one dovetail groove; a first blade having an airfoil portion and a root portion, said root portion contoured to be received within said dovetail groove and having a bottom surface that extends axially from a leading edge to a trailing edge, said bottom surface having first and second tab members extending inward therefrom to define a gap between said bottom 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; said compliant shim further comprising: an upstanding wall portion disposed against said root portion; and a seal element disposed against a first platform of said assembly, as well as disposed radially between said airfoil portion and said root portion, wherein said seal element extends beyond a periphery of said first platform.