A method of manufacturing a hollow aerofoil component 100 for a gas turbine engine 10 comprises joining a first panel 200 to a second panel 300 using bonding, and hot forming the panels into shape. The bonding step and the hot forming step are performed in the same rig, thereby optimizing process time and component quality.

An assembly for hot forming a component includes first and second location features reversibly attached to a sheet metal element that forms the component. The assembly is loaded into a high temperature forming rig by loosely locating the location features into corresponding datum features in a forming tool. As the assembly heats up, the location features locate accurately with the datum features. Thus, the assembly can be accurately located onto the tool accurately and with minimal opening of the hot forming rig, thereby improving efficiency and safety.

A shaping apparatus for shaping a workpiece includes a controlling module and a pressing module, a moving module, a sensing module and a shaping calculation module that are connected to the controlling module. The pressing module includes two pressing elements respectively applying load to a top/bottom surface of the workpiece. The moving module includes a moving platform moving the workpiece horizontally between a sensing zone and a processing zone. The sensing module performs a capturing process on the workpiece in the sensing zone to obtain a surface information. The shaping calculation module compares the surface information with an ideal shape data to calculate and get a shaping information. The moving platform moves the workpiece to the sensing zone. The sensing module performs a capturing process on the workpiece. The moving platform moves the workpiece to the processing zone. The pressing module performs a shaping treatment on the workpiece.

A shaping apparatus for shaping a workpiece includes a controlling module and a pressing module, a moving module, a sensing module and a shaping calculation module that are connected to the controlling module. The pressing module includes two pressing elements respectively applying load to a top/bottom surface of the workpiece. The moving module includes a moving platform moving the workpiece horizontally between a sensing zone and a processing zone. The sensing module performs a capturing process on the workpiece in the sensing zone to obtain a surface information. The shaping calculation module compares the surface information with an ideal shape data to calculate and get a shaping information. The moving platform moves the workpiece to the sensing zone. The sensing module performs a capturing process on the workpiece. The moving platform moves the workpiece to the processing zone. The pressing module performs a shaping treatment on the workpiece.

There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.

There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.

A method for attaching an abradable piece support by crimping to the radially inner wall of a vane sector of a turbomachine, comprises deforming opposite rims of the radially inner wall on opposite free axial ends of the abradable piece support respectively, jointly, by means of two pressure blocks (40A, 40B) respectively, which are attached to each other and delimiting a space (42) between them intended to accommodate a median portion of the abradable piece support. A crimping attachment device (30) comprising such pressure blocks can in particular be operated by means of a conventional press, and can enable the method for attaching the abradable piece support to be automated.

A method of retrofitting vortex generators on a wind turbine blade is disclosed, the wind turbine blade being mounted on a wind turbine hub and extending in a longitudinal direction and having a tip end and a root end, the wind turbine blade further comprising a profiled contour including a pressure side and a suction side, as well as a leading edge and a trailing edge with a chord having a chord length extending there between, the profiled contour, when being impacted by an incident airflow, generating a lift. The method comprises identifying a separation line on the suction side of the wind turbine blade, and mounting one or more vortex panels including a first vortex panel comprising at least one vortex generator on the suction side of the wind turbine blade between the separation line and the leading edge of the wind turbine blade.

A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.

Profiled blade for a fan wheel, with a profile body produced from at least one curved metal strip, whereby adjacent end zones of the at least one metal strip are connected to each other in an adhesively bonded and/or form-fit manner wherein a second end zone at a distance from a second end zone edge is equipped with at least one embossed area for forming a contact surface enabling a first end zone to, at least in sections, be brought into contact with it.