Patent ID: 9409262
Filing Date: 2016-08-09
CPC Classification: B23K,B23P,F01D,F05D,Y02T,Y10T

Claim Text:
1. A method of repairing a rotor or stator blade of a gas turbine engine, the method comprising: in a first step, maneuvering a laser ablation tool within the gas turbine engine to a rotor or stator blade that is to be repaired within the gas turbine engine, and directing an energy beam from the laser ablation tool toward the rotor or stator blade to ablate a first region of material to form a gap extending through the rotor or stator blade between a repair region and a base region of the rotor or stator blade, such that subsequent to the first step, the repair region and the base region are joined by a connecting portion formed by a region of material not removed in the first step; and in a second step, directing the energy beam toward the rotor or stator blade to ablate the repair region to remove the repair region from the rotor or stator blade.