A blade for a gas turbine includes a removed portion space, and further includes an airfoil portion defining the removed portion space, the airfoil portion formed from a base material, and a replacement component formed to fill the removed portion space. The replacement component is formed from a material that includes 50%-80% base material, 0%-30% braze material, and 0%-8% aluminum. A braze joint is formed between the airfoil portion and the replacement component to attach the replacement component to the airfoil portion and fill the removed portion space.

Embodiments described herein relate to methods and systems for controlling the packing behavior of powders for additive manufacturing applications. In some embodiments, a method for additive manufacturing includes adding a packing modifier to a base powder to form a build material. The build material may be spread to form a layer across a powder bed, and the build material may be selectively joined along a two-dimensional pattern associated with the layer. The steps of spreading a layer of build material and selectively joining the build material in the layer may be repeated to form a three-dimensional object. The packing modifier may be selected to enhance one or more powder packing and/or powder flow characteristics of the base powder to provide for improved uniformity of the additive manufacturing process, promote sintering, and/or to enhance the properties of the manufactured three-dimensional objects.

Methods for manufacturing a composite material and composite materials are provided. The method may include preparing a metal foam, preparing a mixture including the metal foam and a curable polymer, curing the curable polymer of the mixture to obtain a composite material, and performing a planarization treatment. The planarization treatment may be performed on the metal foam before preparing the mixture, on the mixture before curing the curable polymer, and/or on the composite material. The composite materials may include a metal foam and a polymer that is on a surface and/or in pores of the metal foam. The composite material may have a surface roughness of 2 μm or less and/or may have a thermal resistance of 0.5 Kin.sup.2/W or less at 20 psi.

A piston pin includes a pipe-shaped main body made of an iron-based sintered alloy. The piston pin is installed to penetrate an upper end of the connecting rod and the piston and the piston pin has an eccentric mass center in a circumferential direction.

A piston pin includes a pipe-shaped main body made of an iron-based sintered alloy. The piston pin is installed to penetrate an upper end of the connecting rod and the piston and the piston pin has an eccentric mass center in a circumferential direction.

A ceramic honeycomb structure includes: an outer peripheral wall; and a partition wall disposed on an inner side of the outer peripheral wall, the partition wall defining a plurality of cells, each of the plurality of cells to form a fluid flow path extending from one end face to other end face. The honeycomb structure contains: 1) particles including one or more selected from silicon carbide, silicon nitride and aluminum nitride; and 2) silicon doped with a dopant. The dopant is a Group 13 element or a Group 15 element. The honeycomb structure has a silicon content (B) of from 20 to 80% by mass, and the honeycomb structure has a porosity of 30% or less.

Provided is a heat sink that has a clad structure of a Cu—Mo composite material and a Cu material and has a low coefficient of thermal expansion and high thermal conductivity. The heat sink comprises a pair of Cu—Mo composite layers and a Cu layer stacked in a thickness direction so that the Cu layer is interposed between the Cu—Mo composite layers or comprises three or more Cu—Mo composite layers and two or more Cu layers alternately stacked in the thickness direction so that two of the Cu—Mo composite layers are outermost layers on both sides, wherein each of the Cu—Mo composite layers has a thickness section microstructure in which flat Mo phase is dispersed in a Cu matrix. Such a clad structure achieves high thermal conductivity together with a low coefficient of thermal expansion.

Provided is a mining bit and a method for manufacturing the same wherein a plurality of cutting tips are provided in such a manner as to be easily made with a high concentration of abrasive particles, rounded on a cutting surface to induce optimal abrasion, and have a shape of an arch having the same width and rounded on inner and outer surfaces thereof. The mining bit includes: the layers have a shape of an arch with flat surfaces in such a manner as to be laminated onto each other in a horizontal direction with respect to a cutting surface of each cutting tip, and a distance (D2) between the abrasive particles on the adjacent layers is less than a distance (D1) between the abrasive particles on each layer.

A mining bit includes: a shank; and cutting tips attached to the shank, each cutting tip having a plurality of layers and a plurality of abrasive particles, wherein the layers have a shape of an arch with flat surfaces in such a manner as to be laminated onto each other in a horizontal direction with respect to a cut surface of each cutting tip, and a distance (D2) between the abrasive particles on the adjacent layers is less than a distance (D1) between the abrasive particles on each layer.

A manufactured article is comprised of an additively manufactured component having sequentially joined layers of metallic powder. A braze material is disposed on at least a portion of an outer surface of the component. The braze material is located in expected crack locations in the outer surface. At least one crack formed in the outer surface, during a heat treatment, is filled with the braze material. The additively manufactured component comprises a metallic material from a precipitation hardened nickel-based superalloy, which forms a γ′ phase.