A method and manufacturing unit for producing a rotor blade (5) of a wind turbine (1) from at least a first rotor blade element (11, 11, 12, 12) and a second rotor blade element (11, 11, 12, 12). The first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12) are positioned in the desired relative arrangement with respect to each other such that a joint gap (13) remains between the first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12). Adhesive is introduced into the joint gap (13) for joining the first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12).

A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade (23), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section (23) to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section (23) and the excess thickness section (31) perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section (31), gradually increases toward the blade tip from a prescribed position.

A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade (23), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section (23) to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section (23) and the excess thickness section (31) perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section (31), gradually increases toward the blade tip from a prescribed position.

A forging method serving to use shaping tooling suitable for high temperature forging of a preformed metal part having angular twist undercuts (49) in its final shape, the method comprising placing the preformed metal part on a movable central insert (44) of the tooling and blocking it in the tooling (40), and forming side fins of the preformed metal part (30) in their final shape by moving a movable top first die and the movable central insert in a common direction towards a stationary bottom die, the movable central insert including at least two cutaway zones (20, 52) for eliminating the angular twist undercuts and thus enabling the preformed metal part in its final shape to be dislodged in a single extraction direction.

A forging method serving to use shaping tooling suitable for high temperature forging of a preformed metal part having angular twist undercuts (49) in its final shape, the method comprising placing the preformed metal part on a movable central insert (44) of the tooling and blocking it in the tooling (40), and forming side fins of the preformed metal part (30) in their final shape by moving a movable top first die and the movable central insert in a common direction towards a stationary bottom die, the movable central insert including at least two cutaway zones (20, 52) for eliminating the angular twist undercuts and thus enabling the preformed metal part in its final shape to be dislodged in a single extraction direction.

A repaired article includes a body extending between a first side and a second side. The body has a repair section with an associated thickness between the first side and the second side. The repair section includes regions of plastic deformation distributed through the thickness. A gas turbine engine including the body is also disclosed.

A repaired article includes a body extending between a first side and a second side. The body has a repair section with an associated thickness between the first side and the second side. The repair section includes regions of plastic deformation distributed through the thickness. A gas turbine engine including the body is also disclosed.

A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.

A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.

A composition of matter is generally provided, in one embodiment, a titanium alloy comprising 5 wt % to 8 wt % aluminum; 2.5 wt % to 5.5 wt % vanadium; 0.1 wt % to 2 wt % of one or more elements selected from the group consisting of iron and molybdenum; 0.01 wt % to 0.2 wt % carbon; up to 0.3 wt % oxygen; silicon and copper; and titanium. A turbine component is also generally provided, in one embodiment, that comprises an article made from a titanium alloy. Additionally, methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature.