General Electric Company
Interlocking Stage of Airfoils

Abstract:

A method is provided for repairing a turbine engine including a stage of vanes, the stage of vanes including a first vane having a first shroud and a second vane having a second shroud. The method includes: inspecting the stage of vanes in situ, wherein inspecting the stage of vanes in situ includes determining an actual gap width of a gap defined between the first shroud of the first vane and the second shroud of the second vane is greater than a predetermined threshold; and installing a shim in situ in the gap between the first shroud and the second shroud.