A method locates and maintains a core in fixed space relationship within the interior of a shell mould. The method provides at least one pin extending into the core with at least one axial end of the pin protruding from the core. A wax pattern having an outer surface is formed by encasing the core and at least one protruding axial end of the pin in wax such that at least one protruding axial end of the pin terminates at the outer surface of the wax pattern. A shell mould is formed around the wax pattern such that, upon removal of the wax pattern, and in a subsequent casting process for production of hollow metal components, at least one protruding axial end of the pin abuts the shell mould, thus fixing the pin and maintaining a position of the core relative to the mould. The protruding axial end of the pin has an enlarged head.

An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.

A component is formed from a component material introduced into a mold assembly. The mold assembly includes a mold that has a cavity defined therein by an interior wall. The cavity receives the component material in a molten state to form the component. A multiple component core assembly is positioned with respect to the mold and has a first core component attached to a second core component at a core split line. A core connection component is attached to each of the first and second core components at the core split line, such that the first core component is held adjacent the second core component at the core split line. The core connection component is formed from a connection component material that is at least partially absorbable by the component material.

A foundry core for manufacturing a blade of a turbomachine including a tip section offset, including a core element for forming various internal cavities, the core element including a leading-edge cavity internal core, central cavity internal cores, and a trailing-edge cavity internal core. The internal core for the central cavity adjacent to the internal core for the trailing-edge cavity includes a bulge extending toward the core for the leading-edge cavity.

A foundry core for manufacturing a blade of a turbomachine including a tip section offset, including a core element for forming various internal cavities, the core element including a leading-edge cavity internal core, central cavity internal cores, and a trailing-edge cavity internal core. The internal core for the central cavity adjacent to the internal core for the trailing-edge cavity includes a bulge extending toward the core for the leading-edge cavity.

A method of manufacturing a ceramic core for a blade including a lower part forming a core body, an upper part forming a squealer tip recess and a set of rods for holding the upper part and the lower part together, includes: coating the rods with a material that has a flash point below 1000 C.; positioning the rods in a mold; molding the upper and lower parts by injecting ceramic; firing the ceramic core.

A method of manufacturing a ceramic core for a blade including a lower part forming a core body, an upper part forming a squealer tip recess and a set of rods for holding the upper part and the lower part together, includes: coating the rods with a material that has a flash point below 1000 C.; positioning the rods in a mold; molding the upper and lower parts by injecting ceramic; firing the ceramic core.

A method produces a casting, in particular a housing of a turbocharger, wherein at least one mold part for forming the casting has a respective parting plane which is arranged at a predetermined angle with respect to the longitudinal axis of the casting, and wherein at least one core element is provided.

A method produces a casting, in particular a housing of a turbocharger, wherein at least one mold part for forming the casting has a respective parting plane which is arranged at a predetermined angle with respect to the longitudinal axis of the casting, and wherein at least one core element is provided.

A side frame may include a bolster opening configured to receive an outbound portion of a bolster. A center core may be used during the manufacture of the side frame to form the bolster opening. The center core may include first and second side walls configured to form the first and second side frame columns of the bolster opening. Additionally, each of the first side wall and second side wall may include one or more pin core holes each of which is configured to receive a pin core used in forming the fastening holes of the first and second side frame columns.