The present invention provides a shaped component for a compressor wheel that can be used to manufacture a turbo compressor wheel which is excellent in terms of high-temperature strength, rigidity, and dynamic balance and, furthermore, has optimal performance suitable for diverse required characteristics in individual portions. In the shaped component for an aluminum alloy turbo compressor wheel of the present invention, a continuous casting rod-shaped material having a small diameter or a forging-completed material obtained by carrying out hot closed die forging on the continuous casting rod-shaped material having a small diameter is used as a material, and the continuous casting rod-shaped material or the forging-completed material has a structure in which the average numbers of grain boundaries intersected in a circumferential direction on a transverse section orthogonal to a casting direction and a forging direction are minimized in a central portion and are maximized in an outer circumferential portion, and the casting direction and the forging direction of the material are along a rotational center axis line direction of a compressor wheel.

The present invention provides a shaped component for a compressor wheel that can be used to manufacture a turbo compressor wheel which is excellent in terms of high-temperature strength, rigidity, and dynamic balance and, furthermore, has optimal performance suitable for diverse required characteristics in individual portions. In the shaped component for an aluminum alloy turbo compressor wheel of the present invention, a continuous casting rod-shaped material having a small diameter or a forging-completed material obtained by carrying out hot closed die forging on the continuous casting rod-shaped material having a small diameter is used as a material, and the continuous casting rod-shaped material or the forging-completed material has a structure in which the average numbers of grain boundaries intersected in a circumferential direction on a transverse section orthogonal to a casting direction and a forging direction are minimized in a central portion and are maximized in an outer circumferential portion, and the casting direction and the forging direction of the material are along a rotational center axis line direction of a compressor wheel.

A process for shaping a part (12) of the turbine vane type, includes providing a part (12) comprising a blade (14) in an initial shape, providing a nominal definition representing the part in a nominal shape, comparing the initial shape with the nominal definition to determine compliance or non-compliance, for a non-compliant datum, determining a force to be applied to the part to deform said part, applying a force to obtain the part in a deformed shape, comparing the deformed shape with the nominal definition to determine compliance or non-compliance, and training a self-learning algorithm (82).

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component.

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component.

The present invention relates to a method for forging a component, in particular a component made of a TiAl material, in which the die for forging is heated to a specified first temperature prior to the forging, and in which a preform of the component to be forged is preheated to a specified second temperature, wherein the first temperature is lower than the second temperature, and first and second temperatures are selected so that during the forging, the surface temperature of the preform does not fall below a minimum forging temperature, and the temperature of the die does not increase above a maximum die temperature.

A tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, the tooling including a blade support for receiving a blade while leaving surfaces of the leading edge of the blade disengaged; and a leading edge reinforcement support on which the blade support is designed to be mounted, and including two lateral wedges between which the metal reinforcement for the leading edge of the blade is positioned, the wedges being suitable for being capable of moving towards each other and apart from each other and each of them being provided with a suction grid for gripping the metal reinforcement, the leading edge reinforcement support further including heater elements for polymerizing an adhesive film applied on the leading edge surfaces of the blade.

A shaping method making use of shaper tooling suitable for high-temperature shaping of a preformed metal part having two side fins extending from a nose, the method including putting the preformed metal part into place in a first bottom die of the tooling, holding the preformed metal part in a first determined position with a first movable central insert, forming one of the side fins of the preformed metal part into its final shape in alignment with the nose by moving with a first movable top die, turning over the preformed metal part, putting the preformed metal part into place in a second bottom die of the tooling, holding the preformed metal part in a second determined position with a second movable central insert, and shaping the other side fin into its final shape in alignment with the nose by moving with a second movable top die.

A shaping method making use of shaper tooling suitable for high-temperature shaping of a preformed metal part having two side fins extending from a nose, the method including putting the preformed metal part into place in a first bottom die of the tooling, holding the preformed metal part in a first determined position with a first movable central insert, forming one of the side fins of the preformed metal part into its final shape in alignment with the nose by moving with a first movable top die, turning over the preformed metal part, putting the preformed metal part into place in a second bottom die of the tooling, holding the preformed metal part in a second determined position with a second movable central insert, and shaping the other side fin into its final shape in alignment with the nose by moving with a second movable top die.

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.