A method for controlling a superplastic forming machine for imprinting a shape on a sheet, the machine comprising: a cover; a vat; a press and a peripheral seal for gripping the sheet at its periphery and sealing a pressurized forming chamber delimited by the sheet; members for heating the sheet directly by radiation, these being arranged facing the sheet; a programmable controller. The method involves: determining an initial heating configuration; a finite-element simulation relating to the temperature of the sheet and performed in such a way as to have a temperature that is substantially consistent across the sheet and substantially constant during the course of the forming, in order to obtain a forming specification comprising at least a cycle of powering the heating members and a cycle of pressure in the forming chamber; programming the programmable controller according to the forming specification yielded by the previous simulation.

A method for controlling a superplastic forming machine for imprinting a shape on a sheet, the machine comprising: a cover; a vat; a press and a peripheral seal for gripping the sheet at its periphery and sealing a pressurized forming chamber delimited by the sheet; members for heating the sheet directly by radiation, these being arranged facing the sheet; a programmable controller. The method involves: determining an initial heating configuration; a finite-element simulation relating to the temperature of the sheet and performed in such a way as to have a temperature that is substantially consistent across the sheet and substantially constant during the course of the forming, in order to obtain a forming specification comprising at least a cycle of powering the heating members and a cycle of pressure in the forming chamber; programming the programmable controller according to the forming specification yielded by the previous simulation.

An abrasion strip and method of manufacturing the same. The abrasion strip being composed of INCONEL alloy 718SPF and being shaped by superplastic forming.

A process of forming an aerofoil is provided. The process includes: providing a layered, planar pre-form; inflating and hot creep forming the pre-form to form an intermediate structure having aerofoil pressure and suction surfaces, and a front, edge-receiving portion joining front edges of the pressure and suction surfaces; providing a leading edge piece; and bonding the leading edge piece to the front, edge-receiving portion of the intermediate structure to form an aerofoil in which the leading edge piece forms an aerofoil leading edge.

Provided is a method for quick forming of a hot metal sheet. The method relates to a technology for forming a metal sheet part, and solves the problem that the existing hot metal sheet forming technology cannot ensure that a blank is deformed under reasonable temperature and pressure conditions, thereby failing to realize precise and quick forming of a complex metal sheet part, especially a thin-walled part. The method mainly includes the following steps: step one, placing a metal sheet blank to be formed on a forming mold; step two, introducing high-pressure gases with equal pressures simultaneously into upper and lower enclosed cavities respectively formed by the metal sheet blank and the sealing mold, and the metal sheet blank and the forming mold; step three, heating the metal sheet blank to a preset forming temperature condition; step four, quickly releasing the high-pressure gas from the cavity formed by the metal sheet blank and the forming mold, such that the metal sheet blank bulges; and step five, discharging the gas from the cavity formed by the metal sheet blank and the sealing mold, and opening the mold to obtain a formed metal sheet part. The present invention is used for manufacturing a metal sheet part.

An aerofoil structure with a hollow cavity is manufactured by diffusion bonding and superplastic forming. Outer panels are formed of a first material; a membrane is formed of a second material. Stop-off material is applied to preselected areas on at least one side of the membrane or of one of the panels so as to prevent diffusion bonding between the panels and the membrane at the preselected areas. The panels and the membrane are arranged in a stack and a diffusion bonding process is performed to bond together the first and second panels and the membrane to form an assembly. A superplastic forming process is performed at a forming temperature to expand the assembly to form the aerofoil structure. The forming temperature is selected so that the second material undergoes superplastic deformation at the forming temperature and the first material does not undergo superplastic deformation at the forming temperature.

An assembly for forming multiple nacelle components is disclosed. In accordance with various embodiments, the assembly includes a plurality of dies arranged about a central axis. A first one of the plurality of dies has a first wall and a first cavity extending through the first wall and a second one of the plurality of dies has a second wall and a second cavity extending through the second wall. The first wall and the second wall are configured to sandwich a pair of metal blanks there between. In various embodiments, a structural ring is configured to surround the plurality of dies.

An assembly for forming multiple nacelle components is disclosed. In accordance with various embodiments, the assembly includes a plurality of dies arranged about a central axis. A first one of the plurality of dies has a first wall and a first cavity extending through the first wall and a second one of the plurality of dies has a second wall and a second cavity extending through the second wall. The first wall and the second wall are configured to sandwich a pair of metal blanks there between. In various embodiments, a structural ring is configured to surround the plurality of dies.

A method of manufacturing an aerofoil blade includes the steps of providing: an aerofoil sub-assembly having a pair of aerofoil skins, wherein at least one of the skins is formed to have on its outer face an outer primary relief feature formed proud of the adjacent region of the outer face and an outer secondary relief feature projecting from the outer primary relief feature; arranging the aerofoil sub-assembly in a cavity die mould; and performing a hot forming process to form an internal cavity between the respective aerofoil skins by inflating the sub-assembly to conform the outer faces of the respective skins to the cavity die mould, whereby in conforming the respective outer faces of the skins to the cavity die mould, the outer primary and secondary relief features are transferred to the inner face of the respective skin to form respectively inner primary and secondary relief features.

A method of manufacturing an aerofoil blade includes the steps of providing: an aerofoil sub-assembly having a pair of aerofoil skins, wherein at least one of the skins is formed to have on its outer face an outer primary relief feature formed proud of the adjacent region of the outer face and an outer secondary relief feature projecting from the outer primary relief feature; arranging the aerofoil sub-assembly in a cavity die mould; and performing a hot forming process to form an internal cavity between the respective aerofoil skins by inflating the sub-assembly to conform the outer faces of the respective skins to the cavity die mould, whereby in conforming the respective outer faces of the skins to the cavity die mould, the outer primary and secondary relief features are transferred to the inner face of the respective skin to form respectively inner primary and secondary relief features.