Patent ID: 7358466

Claim:
An apparatus for heat treating an edge section of an airfoil of a bladed disk comprising: a pair of heat treating bodies, a first heat treating body being hingedly connected to a second heat treating body, each body comprising: a first airfoil-receiving end section having a first end and a second opposite end section having a second end; the airfoil-receiving section comprising a cavity for receiving a gas turbine engine bladed disk airfoil edge section, the cavity being defined by a metal body and an airfoil edge section receiving aperture, the aperture comprising a slot section and a notch section, the notch section being positioned at the first end, the notch section and the slot section being configured to receive an airfoil edge; each body having a substantially planar path of hinged rotation, the at least substantially planar path of hinged rotation of the first body being at a preselected angle with respect to the at least substantially planar path of hinged rotation of the second body; a resistive heating element being disposed within at least one of the airfoil receiving cavities.