A method for stripping ceramic from a component includes applying a liquid to a ceramic coating of an outer surface of the component. The method also includes directing a plurality of laser pulses at the ceramic coating with the applied liquid in order to spall the ceramic coating from the component.

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.

A method for repairing an at least externally coated hollow component. The direct mechanical machining of a coated component after use removes the need for a coating-removal and selective hollowing step and a selective repair of cracks, since a design adaptation leads to a component being engineered or used such that it can be used again as a result of external dimensional stipulations.

A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

Additive manufacturing techniques are used to achieve customized preforms for repair or manufacture of turbomachinery. A method of modifying a section of a product includes forming, a preform set to fit the section. A base material is selected with properties desired for the modification of the section. A binder is selected that vaporizes at a temperature below a melting point of the base material. The preform set is built by the selective application of the binder to the base material to achieve design dimensions of the section when the preform is joined to the section. The section is prepared for effecting the extent of modification and the preform is positioned on the section. The section and the preform are heated to substantially eliminate the binder from the preform and then thermally processed to harden the preform and to bond the preform to the section.

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

A method for forming a vertically cracked thermal barrier coating is disclosed including positioning an article relative to a heat source. The article includes a thermal barrier coating disposed on a first surface of a substrate, and the substrate includes a second surface distal across the substrate from the first surface. Heat is applied locally to at least one discrete portion of the second surface of the substrate. At least one vertical crack in the thermal barrier coating is formed disposed over the at least one discrete portion. An article is disclosed including a substrate and a vertically-cracked thermal barrier coating disposed on the substrate. The vertically cracked thermal barrier coating includes at least one vertical crack in the thermal barrier coating and at least one of a low density of less than 85% of a theoretical density for the thermal barrier coating and a selective crack distribution.

A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

A method for the layer-by-layer additive manufacturing of a composite material having the selective irradiation of a base material to produce a first, dense material phase and to produce a second, porous material phase, wherein the production of the first material phase and the production of the second material phase take place alternately. A correspondingly produced composite material and to a component has the composite material.

A system includes a gas turbine component having a recessed portion with a recessed surface in a hard-to-weld (HTW) material. The system includes a plate disposed over the recessed portion. The plate has an easy-to-weld (ETW) material. The plate has an outer surface and an inner surface, and the inner surface faces the recessed portion. The system includes a braze material disposed within the recessed portion between the recessed surface and the inner surface of the plate. The braze material is configured to bond the recessed surface of the recessed portion with the inner surface of the plate when the braze material is heated to a brazing temperature. The system includes a filler material disposed on the outer surface of the plate disposed over the recessed portion. Application of the filler material to the outer surface of the plate is configured to heat the braze material to the brazing temperature.