A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

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 method of manufacturing a centrifugal fan is provided that includes cutting a metal sheet to form a positive pressure surface forming member and a negative pressure surface forming member, respectively, forming a positive pressure surface and a negative pressure surface; pressing the positive pressure surface forming member and the negative pressure surface forming member to form a first curved surface forming the positive pressure surface and a second curved surface forming the negative pressure surface; trimming the positive pressure surface forming member provided with the fast curved surface and the negative pressure surface forming member provided with the second curved surface to form a shroud bonding surface and a main plate bonding surface; bending the shroud bonding surface and the main plate bonding surface; bonding the positive pressure surface forming member and the negative pressure surface forming member to each other; and bonding the shroud bonding surface and a shroud to each other and bonding the main plate bonding surface and a main plate to each other in a bonded state of the positive pressure surface forming member and the negative pressure surface forming member.

A method of manufacturing a centrifugal fan is provided that includes cutting a metal sheet to form a positive pressure surface forming member and a negative pressure surface forming member, respectively, forming a positive pressure surface and a negative pressure surface; pressing the positive pressure surface forming member and the negative pressure surface forming member to form a first curved surface forming the positive pressure surface and a second curved surface forming the negative pressure surface; trimming the positive pressure surface forming member provided with the fast curved surface and the negative pressure surface forming member provided with the second curved surface to form a shroud bonding surface and a main plate bonding surface; bending the shroud bonding surface and the main plate bonding surface; bonding the positive pressure surface forming member and the negative pressure surface forming member to each other; and bonding the shroud bonding surface and a shroud to each other and bonding the main plate bonding surface and a main plate to each other in a bonded state of the positive pressure surface forming member and the negative pressure surface forming member.

A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

A method for manufacturing a blisk includes an intermediate product molding step of molding a blisk intermediate product including a circular disk-corresponding part, a plurality of rotor blade-corresponding parts, and bridges each connecting a front edge of one of each pair of the rotor blade-corresponding parts adjacent to each other and a rear edge of the other one of the rotor blade-corresponding parts. The method for manufacturing the blisk further includes a disk finishing step of cutting the disk-corresponding part so as to finish the disk-corresponding part into the disk in a product form, and a rotor blade finishing step of cutting each bridge so as to finish the respective rotor blade-corresponding parts into the respective rotor blades in a product form.

A method for manufacturing a blisk includes an intermediate product molding step of molding a blisk intermediate product including a circular disk-corresponding part, a plurality of rotor blade-corresponding parts, and bridges each connecting a front edge of one of each pair of the rotor blade-corresponding parts adjacent to each other and a rear edge of the other one of the rotor blade-corresponding parts. The method for manufacturing the blisk further includes a disk finishing step of cutting the disk-corresponding part so as to finish the disk-corresponding part into the disk in a product form, and a rotor blade finishing step of cutting each bridge so as to finish the respective rotor blade-corresponding parts into the respective rotor blades in a product form.

This method for manufacturing a high-temperature component formed of a Ni-based alloy includes a step of subjecting a workpiece of the Ni-based alloy to hot die forging using predetermined dies to form a forge-molded article, the step including: a die/workpiece co-heating substep of heating the workpiece interposed between the dies to a forging temperature; and a hot forging substep of taking out the workpiece and the dies into a room temperature environment and immediately performing hot forging on the workpiece using a press machine. The predetermined dies are formed of another Ni-based superalloy comprising and phases, and have features in that: a solvus temperature of the phase is 1050-1250 C.; and the phase precipitates at least 10 vol. % at 1050 C. and has two kinds of forms of intra-grain phase precipitations within the phase grains and inter-grain phase precipitations between/among the phase grains.

A forging assembly may comprise a first die and a second die configured to translate toward the second die. A first sensor may be coupled to at least one of the first die or the second die. The first sensor may be configured to output a first signal correlating to a first distance between the first die and the second die. Additional sensors may be applied to track die alignment during the forging process.