A system for fabricating an object includes an additive manufacturing apparatus configured to build a three dimensional (3D) tool by additively depositing two or more layers of material. The system includes a deposition apparatus configured to deposit at least one metal on the 3D tool to form the object on the 3D tool. The system includes a burnout apparatus configured to heat the 3D tool to remove the 3D tool from the object.

A system for fabricating an object includes an additive manufacturing apparatus configured to build a three dimensional (3D) tool by additively depositing two or more layers of material. The system includes a deposition apparatus configured to deposit at least one metal on the 3D tool to form the object on the 3D tool. The system includes a burnout apparatus configured to heat the 3D tool to remove the 3D tool from the object.

A sliding member (1) is formed of a sintered compact. The sintered compact includes: a base layer (3), which mainly contains an Fe-based structure and further contains 1.0 wt % to 5.0 wt % of Cu, a metal having a melting point lower than a melting point of Cu, and C; and a sliding layer (2), which is sintered together with the base layer (3) in a state of being held in contact with the base layer (3) and has a sliding surface (A). The sliding layer (2) mainly contains an Fe-based structure containing at least one kind of alloy element selected from Ni, Mo, Mn, and Cr and further contains Cu and C, and the content of Cu in the sliding layer (2) is larger than the content of Cu in the base layer.

Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

A cylinder for a molding machine comprising a HIP-sintered lining layer on an inner surface of a cylindrical steel body, the lining layer comprising 38-70% by volume of tungsten carbide particles having a median diameter d.sub.50 of 1-7 m and a matrix composed of an Ni-based alloy, and the maximum length of the matrix in an arbitrary cross section being 12 m or less.

Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.

A method of manufacturing a component is described comprising building a preform from a powdered first material, the preform having residual porosity, applying a coating of a second material to a porous surface of the preform by a cold spray powder deposition process to form a coated preform having a gas-tight surface, and then consolidating the coated preform to produce a component. The component may comprise a duct system.

A method for 3D printing includes printing a first metallic material on a substrate as a support structure (48). A second metallic material, which is less anodic than the first metallic material, is printed on the substrate as a target structure (46), in contact with the support structure. The support structure is chemically removed from the target structure by applying a galvanic effect to selectively corrode the first metallic material.

A method for 3D printing includes printing a first metallic material on a substrate as a support structure (48). A second metallic material, which is less anodic than the first metallic material, is printed on the substrate as a target structure (46), in contact with the support structure. The support structure is chemically removed from the target structure by applying a galvanic effect to selectively corrode the first metallic material.

A composite component may include a substrate including a first material and defining a surface; and at least one feature attached to the surface of the substrate. The at least one feature may include a second, different material attached to the surface using cold spraying. Cold spraying may include accelerating particles of the second material toward the surface without melting the particles.