A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

The present disclosure relates to a composite panel having a sandwich structure formed by a central core having a primary cellular structure, for example, of the honeycomb type, sandwiched between two skins. The primary cellular structure includes an array of main cells. The composite panel further includes a plurality of pins, each pin being, on the one hand, arranged to be housed and to cooperate inside a main cell and, on the other hand, formed of a secondary cellular structure having an array of secondary cells.

A method may include removing a portion of a base component adjacent to a damaged portion of the base component to define a repair portion of the base component. The base component may include a cobalt- or nickel-based superalloy, and the repair portion of the base component may include a through-hole extending from a first surface of the base component to a second surface of the base component. The method also may include forming a braze sintered preform to substantially reproduce a shape of the through-hole. The braze sintered preform may include a Ni- or Co-based alloy. The method additionally may include placing the braze sintered preform in the through-hole and heating at least the braze sintered preform to cause the braze sintered preform to join to the repair portion of the base component and change a microstructure of the braze sintered preform to a brazed and diffused microstructure.

A manufactured article is comprised of an additively manufactured component having sequentially joined layers of metallic powder. A braze material is disposed on at least a portion of an outer surface of the component. The braze material is located in expected crack locations in the outer surface. At least one crack formed in the outer surface, during a heat treatment, is filled with the braze material. The additively manufactured component comprises a metallic material from a precipitation hardened nickel-based superalloy, which forms a phase.

The present disclosure relates to a method for producing a final metal part for a nacelle of a turbojet. The method includes brazing at least two parts, one being an inner part having an inner surface and the other being an outer part having an outer surface. The method further includes a step of heating the outer surface of the outer part using an external heating means, and a step of heating the inner surface of the inner part using an internal heating means.

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.

A method of seamless bonding comprises in sequence: feeding a filler wire into a de-scaling unit; removing with the de-scaling unit a contamination layer disposed onto a core of the filler wire, removing the contamination layer comprising: applying a laser beam to the filler wire at a wavelength causing at least a portion of the contamination layer to break away from the core of the filler wire while leaving the core unaffected; and feeding the filler wire to a seamless bonding unit. A seamless bonding device is also presented.

A method of manufacturing includes depositing a first braze material to a first joint location between a first component having a first coefficient of thermal expansion and an intermediate component. The first component is fitted to the intermediate component at room temperature at the first joint location. A second braze material is deposited to a second joint location between the intermediate component and a second component having a second coefficient of thermal expansion. The second component is fitted to the intermediate component at room temperature at the second joint location. The intermediate component has a coefficient of thermal expansion between the first coefficient of thermal expansion and the second coefficient of thermal expansion.

A nanoparticle powder is disclosed including a plurality of stabilized nanoparticles having a superalloy composition. At least about 90% of the particles have a convexity between about 0.980-1 and a circularity between about 0.850-1. A method for forming a braze paste is disclosed including mixing the plurality of stabilized nanoparticles with at least one organometallic precursor and up to about 5 wt % binder. A method for modifying an article is disclosed including applying the braze paste to a substrate including at least one crack, removing at least about 70% of the binder in the braze paste, and then applying additional braze paste over the first portion. Under vacuum or inert gas atmosphere, essentially all remaining binder is evaporated. The braze paste is brazed to the article at about 40-60% of the superalloy's bulk liquidus temperature, forming a brazed material and thereby sealing the at least one crack.

Provided is a part and to the filling, layer by layer, of a defective spot by means of solder and parent metal. Because a defective spot is filled layer by layer, good mechanical properties are obtained for the defective spot and the entire part.