A method of fabricating a reinforcing edge (10) of a turbine engine blade (70) in which there is provided a blank (10) of the reinforcing edge and an indentation is imprinted in said blank so as to form a rough surface (S). A reinforcing edge (10) obtained by such a method.

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.

The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).

The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).

A sheet metal blank is formed into a helical turbine blade by stretching an outer portion of the blank by creating indents and detents thereon. Then the stretched side is flattened and the stretched structure is formed into a helical shape.

A sheet metal blank is formed into a helical turbine blade by stretching an outer portion of the blank by creating indents and detents thereon. Then the stretched side is flattened and the stretched structure is formed into a helical shape.

A bond fixture includes a frame that defines a chamber for receiving a component. At least one bladder assembly is mounted to the frame and extends into the chamber to apply a pressure to an adjacent surface of the component. A caul assembly is positionable about the component and receivable within the chamber. The caul assembly heats a localized portion of the component.

A bond fixture includes a frame that defines a chamber for receiving a component. At least one bladder assembly is mounted to the frame and extends into the chamber to apply a pressure to an adjacent surface of the component. A caul assembly is positionable about the component and receivable within the chamber. The caul assembly heats a localized portion of the component.

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.