A method for the manufacture of a component comprises the following steps, in sequence using an additive layer manufacturing process to build a three-dimensional net shape of the component; performing a first abrasive blasting operation on a region of a surface of the component; and performing a second abrasive blasting operation on the region. The angle of incidence of the abrasive on the surface in the first abrasive blasting operation is less than the angle of incidence of the abrasive on the surface in the second abrasive blasting operation.

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 low-pressure casting apparatus includes a core that together with a mold forms a cavity and a reduced-pressure dryer configured to dry the core under reduced pressure. The core is disposed in the mold, the molded is closed, the core is dried under reduced pressure, and thereafter the cavity is filled with molten metal.

A low-pressure casting apparatus includes a core that together with a mold forms a cavity and a reduced-pressure dryer configured to dry the core under reduced pressure. The core is disposed in the mold, the molded is closed, the core is dried under reduced pressure, and thereafter the cavity is filled with molten metal.

A method of treating a surface of a mold. The method includes forming dimples on a surface of a mold by ejecting substantially spherical ejection-particles so as to bombard the surface of the mold. The dimples are formed so as to satisfy a condition defined by the following formula:

1+3.3e.sup.H/230W3+13.4e.sup.H/1060

wherein W is an equivalent diameter (m) of the dimples and H is a base metal hardness (Hv) of the mold.

A method of treating a surface of a mold. The method includes forming dimples on a surface of a mold by ejecting substantially spherical ejection-particles so as to bombard the surface of the mold. The dimples are formed so as to satisfy a condition defined by the following formula:

1+3.3e.sup.H/230W3+13.4e.sup.H/1060

wherein W is an equivalent diameter (m) of the dimples and H is a base metal hardness (Hv) of the mold.

A method of treating a surface of a mold for transparent resin molding. The method includes ejecting substantially spherical ejection particles against a surface of a mold employed to mold a transparent resin so as to bombard the surface. The method includes forming dimples with an equivalent diameter in a range that satisfies a condition defined by the following formula:

1+3.3e.sup.H/230W1.5+8.9e.sup.H/630

wherein W is an equivalent diameter (m) of the dimples and H is a base metal hardness (Hv) of the mold.

A method of treating a surface of a mold for transparent resin molding. The method includes ejecting substantially spherical ejection particles against a surface of a mold employed to mold a transparent resin so as to bombard the surface. The method includes forming dimples with an equivalent diameter in a range that satisfies a condition defined by the following formula:

1+3.3e.sup.H/230W1.5+8.9e.sup.H/630

wherein W is an equivalent diameter (m) of the dimples and H is a base metal hardness (Hv) of the mold.

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.