A method of joining dissimilar metal, golf club components, and particularly golf club bodies, hosels, and faces, using a projection resistance welding process is disclosed herein. The method may include the step of applying an interlayer material before the projection resistance weld process occurs.

A solder alloy has an alloy composition consisting of, in mass %, Ag: 0 to 4%, Cu: 0.1 to 1.0%, Ni: 0.01 to 0.3%, Sb: 5.1 to 7.5%, Bi: 0.1 to 4.5%, Co: 0.001 to 0.3%, P: 0.001 to 0.2%, and the balance being Sn.

Provided herein are manufacturing methods, e.g., comprising: (1a) forming a layer, including: depositing a starting material including a mixture of a metal and a sacrificial material; and applying a laser beam to the deposited starting material to consolidate the deposited starting material and form the layer; (1b) optionally repeating (1a) one or more times; and (1c) at least partially removing the sacrificial material to form a porous metal part.

Methodologies and manufacturing processes to manufacture components by electron beam melting additive manufacturing, particularly components of molybdenum or a molybdenum-based alloy and particularly of complex nuclear component geometries. Input parameters are provided for controlling electron beam melting additive manufacturing equipment, such as electron beam melting machines. The input parameters relate to various process steps, including build set-up, initial thermal treatment, initial layering of powder, pre-consolidation thermal treatment, consolidation, post-consolidation thermal treatment, indexing of layers, and post-build thermal treatment. The methodologies and manufacturing processes allow manufacture of components of molybdenum having a purity of ≥99.0% and a density of ≥99.75%. Metallographic cross-sections of the manufactured molybdenum components were porosity-free and crack-free.

The present invention relates to a nickel-based superalloy for diffusion bonding, which includes a surface depletion layer in a state in which an aluminum (Al) or titanium (Ti) content is depleted, the surface depletion layer being formed to a depth of 50 μm or less from a surface for diffusion bonding, and a method for diffusion bonding using the same.

A method of reworking an aerospace component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity. The cavity is then at least partially filled with a multiple of layers of discrete laser powder deposition spots of a filler alloy. A cast component for a gas turbine engine includes a cast component non-fusion weldable base alloy with a cavity filled with a multiple of layers of laser powder deposition spots of a filler alloy. The filler alloy may be different than the non-fusion weldable base alloy. A layer of non-fusion weldable base alloy is at least partially within the cavity and over the filler alloy.

This method for producing a structure wherein base materials are bonded by atomic diffusion comprises: a step for applying a liquid resin on the base material; a step for smoothing the surface of the liquid resin by surface tension; a step for forming a resin layer by curing; a step for forming a metal thin film on the resin layer; a step for forming a metal thin film on the base material; and a step for bringing the metal thin film of the base material and the metal thin film of the base material into close contact with each other, thereby bonding the metal thin film of the resin layer and the metal thin film of the base material with each other by atomic diffusion.

A method for selectively adhering braze powders to a surface comprises applying a braze powder to a surface, and then directing a laser beam onto the braze powder while the laser beam moves along a predetermined path relative to the surface. The laser beam selectively heats the braze powder along the predetermined path such that the braze powder is sintered and bonded to the surface. Thus, a braze deposit is formed at one or more predetermined locations on the surface. After forming the braze deposit, excess braze powder, that is, the braze powder not selectively heated by the laser, is removed from the surface.

A method for repairing a part and the resulting is disclosed. The method includes positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component. The cavity has a circular cross-section at the external surface of the component. The plug completely fills the circular cross-section and the inner braze element is within the cavity. A braze paste is positioned at least partially around the plug at the external surface. The component is positioned such that the inner braze element is above the plug. The component is subjected to a thermal cycle to melt the inner braze element around the plug, completely sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component. During the thermal cycle the braze paste is melted to form a metallurgical bond with the plug and external surface.

A field device for processing and automation technology includes a first and a second component that can each be mechanically connected at a joining surface by means of a joining point. Two metal surface layers are each applied at least to the joining surface of the first component and the joining surface of the second component. The metal of the surface layers is different from the metal of the first and/or the metal of the second component. A joining material is applied between the respective joining surfaces of the two components, wherein the joining material includes particles at least partially consisting of a metal that corresponds with the metal of the surface layers The joining of the two components occurs at a joining temperature below 300° C.