Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

The apparatus and method allows multiple components to be simultaneously bonded to a central shaft or tube using linear friction welding in a single welding process. The method involves simultaneously pressing the work pieces radially against the central shaft or tube at the desired locations while the shaft is vibrated axially. The weld is facilitated by the use of a linear friction welding machine, which includes a number of fixtures and press assemblies to hold and press the various work pieces against the central shaft or tube and a vibrating assembly for vibrating the central shaft or tube.

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.

A cam assembly in a linear friction welding system includes two power shafts. Each of the shafts have two timing gears mounted thereupon. For one of the shafts, one of the timing gears includes a slot extending within the timing gear which is formed as an arc about a center of rotation of the power shaft. The other timing gear on that shaft includes a fixed pin which extends into the slot. A cross-over shaft is operably connected to both power shafts.

A method of depositing an extrudate onto a substrate, the method including steps of rotating a stirring tool about an axis of rotation while urging a tool distal end of the stirring tool against the substrate, and wherein the stirring tool defines a bore, extending therethrough; positioning a die adjacent to the stirring tool, such that the stirring tool rotates relative to the die; and passing feedstock through the bore toward the tool distal end.

According to an embodiment, a method for manufacturing a safety busbar comprises placing a second conductor on each of two opposite ends of a first conductor, performing linear friction welding between the first conductor and the second conductor, and cutting the first conductor to a predetermined depth.

The present invention provides a weathering steel for solid-state welding that forms an excellent weld when subjected to solid-state welding and has tensile properties equivalent or superior to those of high tensile strength steel, said steel having weathering properties superior to those of conventional weathering steel for welding, wherein the reliability of the weld is equivalent or superior to that of the parent material; and a weathering steel material for solid-state welding. Further, there is provided a solid-state welded structure that includes the weathering steel for solid-state welding according to the present invention, and a solid-state welding method for said weathering steel for solid-state welding. The weathering steel for solid-state welding having a steel composition comprises, in % by mass, C: 0.10 to 0.60% and P: more than 0.035 to 1.000%, with the remainder consisting of Fe and unavoidable impurities.

A friction stir welding apparatus is used at a butted portion where a second workpiece is butted against a first workpiece such that the second workpiece is upright on the first workpiece. The friction stir welding apparatus includes: a rotary tool that is plunged into one inner corner of a pair of inner corners that are positioned, at the butted portion, on both sides of the second workpiece, respectively; an inner corner presser that presses the other inner corner of the pair of inner corners; and a mover that moves the rotary tool and the inner corner presser along a direction in which the butted portion extends. The inner corner presser includes a pressing roller that presses the other inner corner while rolling in a state where the inner corner presser is being moved by the mover.

A method of operating a linear friction welding system in one embodiment includes establishing a ram vibration amplitude by positioning a stop of a phase change assembly and positioning the phase change assembly in different configurations to establish different phase relationships between two eccentrically engaged power shafts while one of the power shafts is driven by a timing component and the other power shaft is driven by the timing component through the phase change assembly. In one phase change assembly configuration a ram operably connected to one of two components to be welded does not vibrate when the first power shaft and the second power shaft rotate while in another phase change assembly configuration the ram vibrates. Pressure between the two components is controlled to provide scrub pressure when the ram vibrates and forge pressure when the ram is no longer vibrating.

An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.