Embodiments of a method for producing powder mixtures having uniform dispersion of ceramic particles within larger superalloy particles are provided, as are embodiments of superalloy powder mixtures. In one embodiment, the method includes producing an initial powder mixture comprising ceramic particles mixed with superalloy mother particles having an average diameter larger than the average diameter of the ceramic particles. The initial powder mixture is formed into a consumable solid body. At least a portion of the consumable solid body is gradually melted, while the consumable solid body is rotated at a rate of speed sufficient to cast-off a uniformly dispersed powder mixture in which the ceramic particles are embedded within the superalloy mother particles.

A method for manufacturing an alloy formed from a boride of a precious metal, may involve reacting a source of the precious metal with a source of boron in a salt or a mixture of salts in the molten state. An alloy formed from a boride of a precious metal may include crystalline nanoparticles of M.sub.xB.sub.y with M being a precious metal, distributed in an amorphous matrix of B or in an amorphous matrix of B and of M.sub.zB.sub.a.

A reinforced magnesium composite, and a method of producing thereof, wherein the reinforced magnesium composite comprises elemental magnesium particles, elemental nickel particles, and one or more ceramic particles with elemental nickel particles being dispersed within elemental magnesium particles without having intermetallic compounds therebetween. Various embodiments of the method of producing the reinforced magnesium composite are also provided.

A method for manufacturing a gas turbine engine component from a molybdenum-rich alloy. The method includes the steps of providing a molybdenum powder of at least 50% molybdenum by weight, extruding the molybdenum powder to provide a first shape, forming the first shape to a second shape and forging the second shape to provide a third shape.

A method for friction stir forming a metal matrix composite (MMC) structure (76). The method includes the step of providing a substrate (12) comprising a metallic material and securing a preformed MMC layer (14, 16) comprising an MMC material in a position overlying at least a portion of the substrate (12). The method further includes the step of friction stirring the preformed MMC layer (14, 16) with a friction stirring tool (50) which includes a rotating probe (56), including locating the probe (56) at a stirring depth at which the probe (56) extends through the preformed MMC layer (14, 16) into a portion of the substrate (12) and passing the tool (50) through the preformed MMC layer (14) at the stirring depth to friction stir the preformed MMC layer (14, 16) and integrate the preformed MMC layer (14, 16) with the substrate (12).

The invention relates to a highly heat conductive valve seat ring (1) comprising a carrier layer (2) and a functional layer (3), wherein the carrier layer (2) consists of a solidified copper matrix containing 0.10 to 20% w/w of a solidifying component s and the functional layer (3) consists of a solidified copper matrix which further contains, based on the copper matrix, 5 to 35% w/w of one or more hard phases.

The invention relates to a highly heat conductive valve seat ring (1) comprising a carrier layer (2) and a functional layer (3), wherein the carrier layer (2) consists of a solidified copper matrix containing 0.10 to 20% w/w of a solidifying component s and the functional layer (3) consists of a solidified copper matrix which further contains, based on the copper matrix, 5 to 35% w/w of one or more hard phases.

Disclosed herein, in certain embodiments, are composite materials, methods, tools and abrasive materials comprising a tungsten-based metal composition, a tungsten carbide, and an alloy. In some cases, the composite materials or matrix are resistant to oxidation.

A reinforcing metal blank may be used to form metal matrix composite (MMC) drill bits. For example, an MMC drill bit may include a shank attached to a reinforcing metal blank that extends into a bit body comprising a metal matrix composite, wherein the reinforcing metal blank comprises reinforcing structures that are positioned along at least a portion of an inner surface and/or at least a portion of an outer surface of the reinforcing metal blank and extend into the metal matrix composite; and a plurality of cutting elements coupled to an exterior portion of the bit body.

An alloy includes a matrix that includes an amount of high-melting-temperature superalloy between about 30% and 95% by weight and an amount of low-melting-temperature superalloy between about 0% and 70% by weight. The alloy also includes an amount of a ceramic reinforcement material between about 2% and 50% by volume, dispersed in the matrix.