Patent ID: 6219916
Filing Date: 2001-04-24
Classification: B23K,Y10T

Abstract:
A process for joining a base for an airfoil and a disk for an integrally bladed rotor stage in a gas turbine engine, the process comprising:providing the disk for an integrally bladed rotor stage, said disk having a radially outer rim with a radially outer surface, said radially outer rim having a slot with a longitudinal axis, said radially outer surface having a portion adjacent said slot, said slot being defined by a recessed surface;providing the airfoil base, the airfoil base having a longitudinally extending root portion facing opposite a longitudinally extending support portion for supporting the airfoil, said root portion having a root surface, said support portion having an outer surface, said outer surface having lateral edges;bringing said root surface of said root portion of said base into contact with said recessed surface bounding said slot; andapplying pressure and relative movement between said base and said rim to achieve substantial contiguity between said root surface and said recessed surface over the area of said recessed surface, resulting in a substantially continuous linear friction weld between said base and said rim.