Patent ID: 8205335

Claim:
A method of repairing a gas turbine knife edge seal assembly comprising a used honeycomb ring seal and a knife edge, the method comprising: removing the used honeycomb ring seal; removing material from the knife edge to a first knife edge radial height, wherein the knife edge is circumferentially divided into interleaved segments with a first series of knife edge segments integral with disk flanges integral with a radially outward portion of a rotor disk and a second series of knife edge segments integral with blade flanges integral with a plurality of turbine blades assembled in the rotor disk; installing a replacement honeycomb ring seal with a stock radial thickness; removing material from the replacement honeycomb ring seal to a finished radial thickness for sealable engagement with the knife edge, wherein the finished radial thickness establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge begins rotating in the gas turbine; and shimming the turbine blades assembled in the rotor disk after the step of removing the used honeycomb ring seal and before the step of removing material from the knife edge, wherein the shimming step simulates a centrifugal force on the turbine blades when the rotor disk is rotating.