Patent ID: 7190162
Filing Date: 2007-03-13
Classification: G01N

Abstract:
1. A method for inspecting a gas turbine engine rotor disk, wherein the rotor disk includes a plurality of dovetail slots, said method comprising: providing a probe assembly including an eddy current probe and a probe fixture, wherein the eddy current probe includes a body portion and a tip portion including an eddy current probe coil, and wherein the probe fixture includes a platform, a first leg, and a second leg; inserting the eddy current probe into the probe fixture; coupling the probe fixture to the rotor disk such that at least a portion of the probe fixture is coupled to at least one of the dovetail slots and such that the eddy current probe is positioned adjacent the rotor disk, and such that at least one of the first leg and the second leg is slidably adjustable along the platform; generating an eddy current in the rotor disk using the eddy current probe coil; and inspecting the rotor disk using the probe assembly.