Abstract: A manufacturing process for blades of a turbomachine, e.g. a gas turbine engine for an aircraft. In the process: a) a ceramic core piece that comprises at least two ceramic core elements and a clamping part that connects the ceramic core elements, is positioned in a wax forming device, subsequently; b) a molten wax material is applied to the outside of the ceramic core piece in the wax forming device and the wax is allowed to solidify, and subsequently; c) at least two turbomachine blades are cast using a crystallographically-oriented metal casting process and the wax and the ceramic core piece are removed.

Abstract: A manufacturing process for blades of a turbomachine, e.g. a gas turbine engine for an aircraft. In the process: a) a ceramic core piece that comprises at least two ceramic core elements and a clamping part that connects the ceramic core elements, is positioned in a wax forming device, subsequently; b) a molten wax material is applied to the outside of the ceramic core piece in the wax forming device and the wax is allowed to solidify, and subsequently; c) at least two turbomachine blades are cast using a crystallographically-oriented metal casting process and the wax and the ceramic core piece are removed.

Abstract: A system and a method of measuring grain orientations of a metal component. The method includes defining a series of measurement locations on the metal component at which to take a series of measurements indicative of grain orientations at corresponding measurement locations. The method further includes defining a nominal grain orientation at each measurement location. The method further includes loading the measurement locations into a computer-controllable fixture suitable for positioning the metal component. The method further includes locating the metal component in the computer-controllable fixture. The method further includes taking the series of measurements at the series of measurement locations. The method further includes analysing the measurement at each measurement location relative to the nominal grain orientation at the corresponding measurement location.

Abstract: Described is a ceramic core for producing cast component for a gas turbine engine, the core comprising: a first cavity forming member; a second member adjacent to or opposite the first cavity forming member; and a removable web which joins the first and second members.