Abstract: A method is disclosed for mechanically bonding a metal component to a ceramic material, comprising providing a metal component comprising an anchor material attached to at least a first portion of one surface of the metal component; providing a ceramic material having a first surface and a second surface, wherein the ceramic material defines at least one conduit extending from the first surface to the second surface, wherein the at least one conduit has a first open end defined by the first surface, a second open end defined by the second surface, a continuous sidewall and a cross sectional area; positioning the ceramic material such that at least a portion of the at least one conduit is in overlying registration with at least a portion of the anchor material; and applying a bonding agent into at least a portion of the at least one conduit.

Abstract: The present disclosure relates to brazed coated diamond-containing materials and methods of producing brazed coated diamond-containing materials. The method for brazing the coated diamond-containing material may include bringing a braze metal into contact with the refractory metal layer and a substrate; heating at least the braze metal above the melting temperature of the braze metal; and bringing the braze metal into contact with the substrate to form a braze metal layer to join the diamond-containing material, braze metal layer, and substrate together. An advantage of the method may include that the brazing step may be performed in air, under ambient pressure, and without the need for a protective layer.

Abstract: This invention discloses a method, using pure niobium as a transient liquid reactive braze material, for fabrication of cellular or honeycomb structures, wire space-frames or other sparse builtup structures or discrete articles using Nitinol (near equiatomic titanium-nickel alloy) and related shape-memory and superelastic alloys. Nitinol shape memory alloys (SMAs), acquired in a form such as corrugated sheet, discrete tubes or wires, may be joined together using the newly discovered technique. Pure niobium when brought into contact with Nitinol at elevated temperature, liquefies at temperatures below the melting point and flows readily into capillary spaces between the elements to be joined, thus forming a strong joint. A series of diagrams of the interface at various stages of brazing is illustrated by FIG. 10.

Abstract: A composite body which can withstand high thermal stresses is formed by high-temperature soldering at least a part of a high-temperature-resistant, metallic or nonmetallic component and at least a part of a high-temperature-resistant, nonmetallic component. Prior to soldering, a metallic barrier layer, which is impervious to the solder melt, of one or more elements selected from the group consisting of V, Nb, Ta, Cr, Mo, W, Ti, Zr, Hf and alloys thereof, is deposited on that surface of each nonmetallic component which is to be soldered. Solder material, barrier layer and soldering conditions are adapted to one another in such a manner that during the soldering operation the metallic barrier layer remains at least partially in the solid state, so that after the soldering operation it is still present in a thickness of at least 10 ?m at least over the majority of the soldering surface.

Abstract: Fabrication techniques for and examples of metallic composite materials with high toughness, high strength, and lightweight for various structural, armor, and structural-armor applications. For example, various advanced materials based on metallic-intermetallic laminate (MIL) composite materials are described, including materials with passive damping features and built-in sensors.

Abstract: A process for repairing a component includes the steps of placing a piece of refractory metal material over an area of component to be repaired; depositing a repair filler metal material proximate to the piece of refractory metal material in an amount sufficient to repair the component; subjecting the repair filler material to a welding treatment without directly heating the piece of refractory metal material; flowing the repair filler material within the area; and casting the repair filler material.

Abstract: Discloses is a metal-based resistance heat-generation element. The element comprises a core made of a platinum group metal or refractory metal, and a coating film formed on the core. The coating film has at least two layers including a core-side inner layer of a Re—Cr based ? (sigma) phase and a surface-side outermost layer of an aluminide or silicide. Alternatively, the element may comprise a core made of an alloy containing a platinum group metal or refractory metal and Re and Cr diffused therein, and a coating film formed on the core. The coating film has at least one layer including an aluminide or silicide layer.

Abstract: A highly heat-resistant laminated component for a fusion reactor has at least of a plasma-facing area made of tungsten or a tungsten alloy, a heat-dissipating area of copper or a copper alloy with a mean grain size of more than 100 ?m, and an interlayer of a refractory metal-copper-composite. The refractory metal-copper-composite has a macroscopically uniform copper and refractory-metal concentration progression and a refractory metal concentration of between 10 vol. % and 40 vol. % over its entire thickness.

Abstract: A wristwatch case (11) and a method of manufacturing the case, the wristwatch case comprising a wristwatch case body (1) made of titanium or stainless steel and a crown pipe (3) fixed to each other, wherein a stem hole (2) corresponding to the crown pipe (3) is formed in the wristwatch case body (1), a small diameter part is formed in the crown pipe (3), and a small diameter part corresponding to the a small diameter part of the crown pipe is formed in the stem hole (2), the method comprising the step of fitting the crown pipe (3) into the stem hole (2) in the wristwatch case body (1) to form a solid phase diffusion joining part at a portion where the small diameter parts thereof are fitted closely to each other, and to form a brazed connection part at a portion other than that where the small diameter parts are fitted closely to each other, whereby a watch external part having excellent corrosion resistance and waterproof and a large number of design variations can be provided.

Abstract: A tantalum or tungsten target-backing plate assembly which comprises a tantalum or tungsten target and a copper alloy backing plate that are subject to diffusion bonding via an aluminum- or aluminum alloy-sheet insert material at least 0.5 mm thick, and which is provided with diffusion bonded interfaces between the respective materials, wherein the assembly suffers only a small deformation after diffusion bonding and is free from separation between the target and the backing plate or from cracking even when the target material and the backing plate differ greatly in thermal expansion, and can survive high power sputtering; and a production method therefor.

Abstract: A backing plate of Ti for supporting a Ti sputtering target is formed of at least two components welded together. The backing plate is welded by interposing a Cu or Zr foil or powder between faces to be welded, and then heating the assembly to a reaction temperature high enough to melt one of the Ti and Cu or Zr to produce a liquid phase. The heating temperature is retained for a time long enough to permit diffusion of the Cu or Zr into the Ti to produce a liquid phase diffusion weld. By permitting diffusion to occur, a separate metallic compound is not produced at the welding face. In effect welding is accomplished without producing a welding face, whereby no interface exists in the finished weld. The resulting weld has a strength substantially equal to the strength of the Ti material, and very good welding qualities.

Abstract: This invention relates to a high temperature melting composition and a method of using the composition for brazing high temperature niobium-based substrates, such as niobium-based refractory metal-intermetallic compositions (RMIC), including but not restricted to niobium-silicide composite alloys. The high temperature melting composition can include one or more alloys. The alloys include a base element selected from titanium, tantalum, niobium, hafnium, silicon, and germanium. The alloys also include at least one secondary element that is different from the base element. The secondary element can be selected from chromium, aluminum, niobium, boron, silicon, germanium and mixtures thereof. When two or more alloys are included in the composition, it is preferable, but not required, to select at least one lower melting alloy and at least one higher melting alloy. The composition is preferably a homogeneous mixture of the two or more alloys combined in powder form.

Abstract: An article, such as an airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises a first metallic element and a second metallic element, wherein the first metallic element is one of titanium, palladium, zirconium, niobium, and hafnium, and wherein the second metallic element is one of titanium, palladium, zirconium, niobium, hafnium, aluminum, chromium, vanadium, platinum, gold, iron, nickel, and cobalt, the first metallic element being different from the second metallic element.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece is a semi-solid braze that comprises a first component and a second component.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises one of germanium and silicon, and one of chromium, titanium, gold, aluminum, palladium, platinum, and nickel. This abstract is submitted in compliance with 37 C.F.R. 1.72(b) with the understanding that it will not be used to interpret or limit the scope of or meaning of the claims.

Abstract: Its basic means is a monolithically bonded construct prepared by monolithically bonding together a rare-earth magnet 2 and a an alloy material that is a high melting point metal or a high specific-tenacity material through the solid phase diffusion bonding by the hot isostatic pressing treatment, and a monolithically bonded construct with an interposal of a thin layer of the high melting point metal between a rare-earth magnet 2 and an alloy material 3, 4 that is a high specific-tenacity material.

Abstract: A refractory material powder of a carbide-forming metal or alloy is formed into an intermediate body having a shape and size corresponding to the desired shape and size of the article. The intermediate body is exposed to a gaseous hydrocarbon or a mixture of hydrocarbons at a temperature exceeding the decomposition temperature for the hydrocarbon or hydrocarbons until the mass of the intermediate body has increased by at least 3%. The intermediate body is thereafter exposed to a temperature of 1000-1700° C. in an inert atmosphere if the temperature during exposure to the hydrocarbon or hydrocarbons was too low to ensure a complete carbidization of the intermediate body.