A void former is arranged in a mold (30). The void former includes an insert (1) made of flexible material that forms a loop around a core region (15) within the mold. Casting material is added in a fluid state into the mold so as to fill a predefined volume for the facing element, including the core region. After hardening of the casting material, the facing element (10) is removed from the mold, and the void former is removed from the facing element. The facing element comprises an anchoring core formed by the hardened casting material in the core region (15). Removing the void former comprises pulling the insert (1) away from a rear surface of the facing element (10). The flexible material of the at least one insert is deformed around the anchoring core (15) while it is pulled.

The present invention provides a composition for forming a casting mold or a mold liner, comprising solid particles of CaO, SiO, MgO, Al.sub.2O.sub.3 having an average particle size of 20 to 60 μm.

Aspects of the disclosure are directed to treating a substrate, the substrate including at least one of a refractory metal or a ceramic material, and depositing a media onto the treated substrate to generate a casting core. Embodiments include a fixture, a substrate located on the fixture, the substrate including at least one of a refractory metal or a ceramic material, and a delivery head that deposits media onto the substrate to generate a casting core. Aspects are directed to a core configured for casting a component, the core comprising: a substrate that includes at least one of a refractory metal or a ceramic material, and media deposited on the substrate, the media having a dimension within a range of between 0.5 and 500 micrometers.

The invention relates to a casting mold, in particular for use in cold casting methods, which is produced with the aid of a powder-based layering method, the final casting mold having a treated surface.

A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A method for manufacturing a turbine blade 1, is provided. The method comprises the following steps: producing a shell and core assembly by additive manufacturing process, the shell and core assembly defining at least one internal cavity and having an internal structure corresponding to at least one internal cooling circuit of the turbine blade; pouring molten metal in the internal cavity of the shell and core assembly; solidifying the metal; removing the shell and core assembly.

A metal mold for manufacturing a honeycomb structure having a plurality of cell density regions and an annular boundary wall includes a honeycomb-like slit part, which is opened to an extrusion surface of a single metal mold body, that is formed of a plurality of cell slits for forming the plurality of cell density regions and an annular boundary slit for forming the boundary wall. Out of the plurality of cell slits, adjacent cell slits adjacent to the boundary slit have all corner portions formed in a round shape by the adjacent cell slits and the boundary slit.

A composite substrate includes a supporting substrate and a functional substrate that are directly joined together, the supporting substrate being a sintered sialon body.