Abstract: A method of manufacturing a component, the method including a maraging steel blank with an initial shape; and performing an incremental cold forming operation on the maraging steel blank, wherein the incremental cold forming operation reduces a thickness of the maraging steel blank.

Abstract: There is disclosed a tubular blank (31) for attaching to a stepped mandrel (41) of a flow forming assembly, wherein the tubular blank (31) has a stepped inner profile that may be tailored to the shape of the mandrel (41) before any flow forming is carried out on the blank (31). Also disclosed is a corresponding method of flow forming a shaped article by plastically deforming the tubular blank (31) over the stepped mandrel (41), where the forming of the shaped article may be carried out in one operation.

Abstract: A method of shear forming a component comprises the steps of: (i) providing a pre-formed metallic sheet blank, the sheet blank having a first surface and an opposite second surface, the perpendicular separation between the first surface and the second surface defining a thickness of the sheet blank; (ii) applying a surface modification process to the first surface of the sheet blank to reduce a surface roughness of the first surface to a first predetermined roughness value; (iii) positioning the second surface of the sheet blank against a mandrel; and (iv) applying a roller to the first surface of the sheet blank in a shear forming operation to form the sheet blank into the component.

Abstract: A method of forming a shaped article. The method comprises providing a pre-form 40 comprising a chromium molybdenum vanadium steel alloy, heat treating the pre-form to obtain a surface hardness of between 420 and 480 according to the Vickers hardness test, and, subsequent to the heat treating step, flow forming the pre-form 40 to shape the pre-form.

Abstract: A sealing element for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure comprising a plurality of radially inwardly projecting walls. The walls may be abradable and may define cells for receiving an abradable sealing material.

Abstract: A sealing element for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure comprising a plurality of radially inwardly projecting walls. The walls may be abradable and may define cells for receiving an abradable sealing material.