LOCALIZED REPAIR OF SUPERALLOY COMPONENT

摘要

A method comprising:removing a gas turbine vane (140) from service; removing a damaged portion (144) of the component to reveal a repair surface; covering the repair surface with a powdered superalloy material; applying an energy beam to the powder to melt selected portions of the powder to form a patterned first layer of superalloy material (116') joined to the repair surface; covering at least a portion of the first layer of superalloy material with an additional amount of powdered superalloy material; applying the energy beam to the additional amount of powdered superalloy material to form a second layer of superalloy material joined to the first layer; repeating the covering and applying steps until layers of superalloy material form a new portion of the component to replace the damaged portion; and returning the vane (140) to service. The damaged portion may belong to a honeycomb structure (148).