Wear protection system for turbine engine rotor and blade

A rotor and blade assembly for a gas turbine engine, comprising:

• a rotor having a dovetail slot in a rotor circumference thereof, the dovetail slot including at least a pair of side walls diverging in a direction from the circumference toward an inward portion of the rotor, and terminating at a bottom;
• a blade having a dovetail at a first end thereof, the dovetail including at least a pair of side faces diverging in a direction along the blade toward its first end and terminating in a stub end;
• and
• a multilayer clad shim comprising a structural center strip having sufficient strength and rigidity to maintain its manufactured shape and having two faces, a first surface layer permanently joined to a first face of the strip by cold rolling and a second surface layer permanently joined to a second face of the strip by cold rolling;
• wherein each surface layer is comprised of an antifretting material having sufficient strength to withstand stresses between the blade and rotor during engine operation and sufficient ductility for forming into the manufactured shape;
• and
• wherein the shim is disposed between the dovetail and the dovetail slot, such that a portion of the first surface layer of the shims contacts at least a portion of each side face of the dovetail, and such that a portion of the second surface layer of the shim contacts at least a portion of each side wall of the dovetail slot.