A part includes a three-dimensional porous metallic workpiece printed via an additive manufacturing process and subsequently subjected to a diffusion-based process to convert at least a portion of the porous metallic workpiece to a ceramic workpiece or an intermetallic workpiece.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A method of mechanically processing a metallic material component is provided whereby alloying, carburizing, nitriding and boriding can be performed using a friction stir processing tool. This method for mechanically processing metallic material surfaces is cost effective, efficient and does not require specialized equipment.

A method for producing a wear and corrosion resistant WC based material coated with one or more metals selected from group IVB, VB and VIB metals (according to CAS system) and Al is disclosed. The method comprises treating of said coated structure with electrochemical boriding treatment in an electrolyte which is substantially free of halogenated compounds wherein the electrolyte comprises alkali carbonates and boron sources and said electrolyte being heated during electrolysis under an induction heating regime having electromagnetic frequency ranging from 50 to 300 kHz during electrolysis.

Apparatuses and methods of manufacturing of thermally formed composite structures, such as a projectile firing structure, are provided. One simplified exemplary method includes: determining material properties of a projectile firing structure comprising a rifled barrel including thermal conductivity, wear, and tensile strength; wrapping a plurality of thermally reactive layers onto a cylindrical press form structure, the cylindrical press form structure comprising a plurality of spiraled grooves and lands, the thermally reactive layers comprising metal or metal oxides that when heated produce thermal diffusion byproducts in a composite structure forming the rifled barrel having the plurality of material properties; disposing an enclosing structure around the thermally reactive layers wrapped around the cylindrical press form structure; and heating the plurality of thermally reactive layers at a temperature and time so that the plurality of thermally reactive layers thermally react via thermal diffusion forming the rifled barrel having the plurality of material properties.

A chain element (2), in particular a chain pin (4), for joining at least two chain links (3), characterized in that it comprises a surface layer (5) containing boron and vanadium, formed by at least one step of diffusing boron and vanadium in the areas of the chain element (2) which are close to the surface. The surface layer (5) containing boron and vanadium is formed by boriding and subsequently vanadizing a substrate material having a carbon content of 0.60 wt.-% to 1.0 wt.-%.

A powder boronizing composition comprising: a. 0.5 to 4.5 wt % of a boron source selected from B.sub.4C, amorphous boron, calcium hexaboride, borax or mixtures thereof; b. 45.5 to 88.5 wt % of a diluent selected from SiC, alumina or mixtures thereof; c. 1.0 to 20.0 wt % of an activator selected from KBF.sub.4, ammonia chloride, cryolite or mixtures thereof; and d. 10.0 to 30.0 wt % of a sintering reduction agent selected from carbon black, graphite or mixtures thereof.

A process comprising: placing a boronizing powder composition in the interior of a metal pipe comprising a first end, a second end, an inside surface and an outside surface; heating the pipe in a vessel having an interior, to a temperature from 1400 F. to 1900 F., thereby forming spent boronizing reaction gases and a borided layer on the inside surface, wherein the vessel interior has an atmosphere that surrounds the outside surface of the metal pipe; and flowing the spent boronizing reaction gases into the atmosphere surrounding the outside surface of the pipe, thereby forming an oxygen-depleted atmosphere.