Casting core for the manufacture of hollow metal aeronautical parts, in particular high-pressure turbine parts by lost-wax casting, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3 and M being a transition metal selected from the group consisting of titanium and/or niobium and/or molybdenum, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3.

Molding core for manufacturing an OMC hollow aeronautical part, in particular a fan module part, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3, and M being a transition metal selected from the group consisting of titanium, niobium, chromium or zirconium, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3

A production method for a ceramic casting core (20) in which one manufactures the core (20) by machining by mechanical removal of material from a fired ceramic material block (1), the machining operation comprising at least a first machining step to realize a first machined surface (6, 7) in the material block (1), and a second machining step to realize a second machined surface (9) in the material block (1), substantially opposite to the first machined surface (6). Prior to the second machining step, applying a reinforcement layer (8), made of a stiffening solution to protect the material block (1) from breaking during the second machining step, on at least part or the entire first machined surface (6, 7).

The present invention provides a method of forming a leading edge for an aerofoil component e.g. an aerofoil blade. The method comprises forming a pre-form having a precursor edge and processing said precursor edge to form the leading edge. The pre-form is formed using metal injection molding. The leading edge may have an elliptical profile.

A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

A casting core assembly comprising: a first ceramic piece including a projecting post; a second ceramic piece including a socket encircling the post; and a ceramic filler material between the post and the socket, wherein at least one of: in axial section at at least one location the post has: a lateral protrusion of at least 15 micrometers relative to a location proximal thereof; and in axial section at at least one location socket has: a lateral recess of at least 15 micrometers relative to a location outboard thereof.

Exemplary articles may comprise a surface alloyed layer, a base metal comprising a steel, and a transitional layer between the surfaced alloyed layer and the base metal. The surface alloyed layer may comprise nickel (Ni), chromium (Cr), manganese (Mn), molybdenum (Mo), silicon (Si), or combinations thereof. Exemplary methods of making an article may comprise coating a portion of a sand mold with a metal slurry, pouring a molten steel alloy onto the sand mold, and removing the article from the sand mold.