An additive manufacturing machine for repairing a component includes a build platform that supports the component and a powder dispensing assembly for selectively depositing additive powder over the build platform. A powder seal assembly includes a powder support plate positioned above the build platform and defining an aperture for receiving the component without contacting the component. A clamping mechanism is movable relative to the powder support plate and defines a void for receiving a resilient sealing element around the aperture. An actuating mechanism, such as bolts or a linear actuator, moves the clamping mechanism toward the powder support plate to deform the resilient sealing element until the resilient sealing element contacts and forms a seal with the component.

A powder material for additive manufacturing providing an improved microstructure and shape of a product including particles, wherein at most 25 wt.-% of the particles provide a particle size differing more than 20% from the D.sub.50 based on the value of the D.sub.50. A method of additive manufacturing includes the step of manufacturing a product from this powder material or repairing a product utilizing this powder material.

A hybrid article is disclosed including a coating circumscribing the lateral surface of a hollow core having a core material and a channel disposed within the lateral surface. The coating includes about 35% to about 95% of a first metallic material, and about 5% to about 65% of a second metallic material with a lower melting point than the first metallic material. A method for forming the hybrid article is disclosed including disposing the hollow core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.

The production method comprises the steps for producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then assembling the preform to the turbine engine part by diffusion brazing. The thermal amplitude of the main transformation peak (A1) of the brazing material used to make the preform must at least be twice that of each of the respective thermal amplitudes of the secondary transformation peaks (A2, A3) of this brazing material.

A tool for forming a shaped product has a support body that is fabricated from a first material, such as for instance cast iron. The first material defines a first portion of a forming surface of the tool and has a feature supported thereon. The feature has a layer of a second material that is supported on the first material of the support body, a layer of a third material that is supported on the layer of the second material and a layer of a fourth material that is supported on the layer of the third material. The layer of the fourth material, such as for instance a tool steel alloy, defines a second portion of the forming surface of the tool. During use the first portion of the forming surface and the second portion of the forming surface cooperate to form a desired shape of the shaped product.

A method of repairing an airfoil is provided. The method includes providing an airfoil with a damaged section and removing the damaged section by machining or cutting an upper section of the airfoil. A replacement section is configured to mate with an upper surface of the airfoil. A presintered preform is provided to join the airfoil and the replacement sections through a resistance brazing process. The presintered preform is configured to mate with the upper surface of the airfoil and a lower surface of the replacement section and inserted between this upper surface and lower surface, creating a stacked airfoil comprising three mated sections in abutting contact. The stacked airfoil is resistance brazed such that only the braze material of the presintered preform melts and the upper surface of the airfoil and the lower surface of the replacement section remain below the grain boundary temperature of the material of the airfoil.

A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a skeleton, the volume of the skeleton being between 80 percent and 95 percent base material, and infiltrating the skeleton with a melting point depressant material to define a finished component, the finished component having less than one percent porosity by volume.

A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a skeleton, the volume of the skeleton being between 80 percent and 95 percent base material, and infiltrating the skeleton with a melting point depressant material to define a finished component, the finished component having less than one percent porosity by volume.

Provided is a nickel-based composite coating, method for producing the same and use thereof. A powder mixture is coated on the surface of a substrate to obtain a nickel-based composite coating, wherein the powder mixture comprises nickel-chromium-boron-silicon powders and barium titanate powders. The barium titanate powders are added to the nickel-based powders as a second phase to form BaTiO.sub.3—NiCrBSi metal-based ceramic composite coating. The nickel-based barium titanate composite coating has an excellent damping shock absorbing performance and gives the substrate strength as well. Comparing with the conventional coating materials, the coating obtained by the present disclosure through plasma cladding technique not only bonds with the substrate in a metallurgic way, but also has a small heat affected zone, specifically, an excellent damping shock absorbing performance. In embodiments of the present disclosure, vibration and noise generated by the cylinder head is reduced 20% by using the shock absorbing cladding coating.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.