The invention relates to a method for manufacturing a solid metal based component. The method comprising the steps of providing a plurality of metal based sheets; arranging the plurality of metal based sheets in a stack, 5 wherein the stack comprises a first metal based sheet, a last metal based sheet and at least one intermediate metal based sheet; perimetrically sealing at least a portion of the stack forming at least one cavity inside of the stack; removing gas from said at least one cavity, and subjecting the stack to a hot isostatic pressing process for a predetermined time at a predetermined 10 pressure and a predetermined temperature so that the plurality of metal based sheets of the stack bond metallurgically to each other to form a solid metal based component. The invention further relates to a single-piece metal based component.

A semiconductor element bonding body including: a substrate, in which a concave portion is formed; and a semiconductor element placed in the concave portion to be mounted to the substrate. A portion of the substrate in which the concave portion is formed is made of Cu. The concave portion has a perimeter portion in which a level difference is formed, and the level difference has a height d of 20 m or more and less than 50 m. The concave portion has a bottom surface having a flatness degree of /8.7 m or more and /1.2 m or less when a wavelength of a laser is 632.8 nm. A metal film is formed on the semiconductor element, and the bottom surface of the concave portion and the metal film are bonded directly to each other.

A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.

A bearing component including a first metallic material and a second metallic material. The first metallic material provides a first carbon content and the second metallic material presents a second carbon content. The first metallic material and the second metallic material have been joined by a diffusion welding process. The diffusion welding process results in a transition zone with a varying carbon content between the first metallic material and the second metallic material. Varying carbon content in the transition zone is within an interval and the interval end points are defined by the carbon contents of the first metallic material and the second metallic material.

Embodiments of golf club face plates with internal cell lattices are presented herein. Other examples and related methods are also disclosed herein.

The present invention provides an integrated method for forming and performance control of NiAl alloy thin-walled tubular parts. A Ni/Al laminated foil tube is obtained after Ni foils and Al foils are alternately laminated and coiled; and the Ni/Al laminated foil tube is subjected to plastic forming, reaction synthesis and densification treatment in a gas bulging forming die to obtain a NiAl alloy thin-walled tubular part. The present invention solves the problem in the prior art that the preparation of an existing NiAl alloy sheet and the formation of the thin-walled tubular part from the sheet feature difficulty in material flow and structural performance control and a complicated process. Data of embodiments shows that the NiAl alloy thin-walled tubular parts obtained by using the method of the present invention has a high forming rate, high dimensional precision, uniform composition distribution, good tubular part compactness and no defects on the surface.

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 method of manufacturing a heat exchanger by diffusion bonding in which deformation of bonding members as stainless steel plates is suppressed, and releasability (detachability of a bonding member from a release member) after diffusion bonding treatment is excellent. Provided is a method of manufacturing a heat exchanger, the method including layering a plurality of bonding members 1 made of stainless steel, and applying heat and pressure to effect diffusion bonding of the bonding members 1, in which release members 3 are arranged on the both surface sides of the bonding members 1, and holding jigs 4 are arranged so as to sandwich the bonding members 1 through the release members 3, and pressing is then performed through the holding jigs 4 with a pressure device, and in which the diffusion bonding is performed using a combination of the release members 3 and the bonding members 1, the release members 3 including a steel material containing 1.5 mass % or more of Si, and a ratio (Fr/Fp) of the high-temperature strength (Fr) of the release members 3 at 1000 C. to the high-temperature strength (Fp) of the bonding members 1 at 1000 C. being 0.9 or more.

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core;producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6);compacting the stack;removing the primary pins (26) from the primary bores (20);removing the secondary pin from the secondary bore; andtaking the core (14) away from the stack.

In some embodiments, a process treats a turbine component. The turbine component includes an article and a wear component brazed to the article. The process includes applying a braze tape on at least a portion of the wear component and thermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component. In some embodiments, an assembly includes a turbine component. The turbine component includes an article and a pre-sintered preform brazed to a surface of the article. The assembly also includes a braze tape on at least a portion of the pre-sintered preform. In some embodiments, a treated turbine component includes a treated article and a pre-sintered preform brazed to a surface of the treated article. The treated turbine component has been thermally processed with the pre-sintered preform being substantially free of re-flow.