A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

The disclosure describes techniques for joining a first component comprising a first metal or alloy and a second component comprising a second metal or alloy to each other. The techniques may include positioning the first and second component adjacent to each other to define a joint region between adjacent portions of the first component and the second component. The techniques also may include positioning a pre-sintered preform (PSP) braze material in the joint region, heating the PSP braze material to form a molten braze alloy, and cooling the molten braze alloy to join the first and second components. The PSP braze material may include a wide gap braze material.

A method for producing a sealing component has a body made of superalloy covered by a coating to be placed in contact with a gas turbine blade tip. Steps are carried out in which: a) the new coating is produced by moulding from an alloy of a cobalt-nickel-chromium-aluminium-yttrium (CoNiCrAlY) type further containing between 0.5 and 5% by mass (wt %) of boron, and b) the superalloy body and the new coating are brazed together in order to obtain the said sealing component.

An airfoil includes a first airfoil piece and a second airfoil piece that is bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc. The joint includes a braze element of magnesium, zinc, or combinations thereof in a higher concentration than in other portions of the first airfoil piece and the second airfoil piece.

A method of repairing a cast article defect, in accordance with various embodiments, is disclosed herein. The method may comprise: machining an aperture at a defect location of a cast article; coating a plug side surface of a plug with a braze material; coating at least one of a top surface or a bottom surface of the plug with an excess braze material; inserting the plug into the aperture from the inner surface of the cast article towards the outer surface of the cast article and leaving at least one void between a the braze material and a side surface of the aperture; and heating the cast article and the plug.

Systems and methods for moving a substrate to a vision system using a robot; using the vision system to determine where a braze material is to be applied to the substrate; moving the substrate to a braze dispenser using the robot; applying a braze material to the substrate using the braze dispenser based on the determination from the vision system; and using the vison system to determine whether to apply additional braze to the substrate, including for the substrate of a component for gas turbine engine, such as configured for use in an aircraft.

A method of joining includes applying braze to a braze reservoir in a first component. A second component is engaged to the first component, wherein a joint location is defined between the first and second components. A wicking structure provides flow communication from the braze reservoir to the joint location. The method also includes joining the first and second components together at the joint location by applying heat to the braze to flow the braze from the reservoir through the wicking structure to the joint location to form a braze joint at the joint location.

An embodiment of an apparatus includes means for peripherally welding a cavity-back blade and a cover of the cavity-back blade to form a 3-dimensional hollow blade assembly, and a plurality of bellows contained in one or both of a first die half and a second die half receiving the 3-dimensional hollow blade assembly. The plurality of bellows are disposed within the region defined around or inward of the peripherally welded interface of the cover and the blade. At least a portion of the plurality of bellows are arranged in a manner to provide pressure to the cover at approximately a 90 degree angle to each of a plurality of nodes, each node defined by an intersection of two or more ribs in the cavity-back blade.

A method of manufacturing a hard-to-weld material by a beam-assisted additive manufacturing process is presented. The method includes depositing a first layer for the material onto the substrate, the first layer including a major fraction of a base material for the component and a minor fraction of a solder, depositing a second layer of the base material for the component and a thermal treatment of the layer arrangement. The thermal treatment includes a first thermal cycle at a first temperature above 1200 C. for a duration of more than 3 hours, a subsequent second thermal cycle at a second temperature above 1000 C. for more than 2 hours, and a subsequent third thermal cycle and a third temperature above 700 C. for more than 12 hours. A manufactured component is also presented.

A dual walled component includes a spar comprising a plurality of pedestals; a coversheet attached to a first set of pedestals from the plurality of pedestals; and a repaired coversheet portion attached to a second set of pedestals from the plurality of pedestals and to the coversheet, where the repaired coversheet portion includes a braze material.