According to the invention, a blade is friction-welded to a rotor disk of a turbomachine, the disk comprising a projecting block having an outer surface to which the blade is to be welded. To this end: a surfacing process is carried out on at least a part of the periphery of the block, in the region of said outer surface; the outer surface of the block and the surfacing are machined in order to level same; and friction-welding is then carried out between the surfaced outer surface of the block and the blade.

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

A method is provided during which surface data indicative of a measured surface geometry of a component is received. The surface data is processed to provide model data indicative of a solid model of the component. The model data is processed to determine a center of gravity distance of the component. A moment weight of the component is determined based on the center of gravity distance of the component and a measured weight of the component. The moment weight is communicated with the component.

A method for producing an enhanced property integrally bladed rotor includes solution heat treating a stub-containing rotor hub forging; water quenching the solution heat treated stub-containing rotor hub; aging the water quenched stub-containing rotor hub forging; linear friction welding airfoils onto each of a multiple of stubs of the stub-containing rotor hub forging; and concurrently stress relieving the linear friction welds of each of the multiple of stubs within a predefined area while ensuring that a hub inner diameter does not exceed a predetermined temperature.

The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising:a step of producing a blank from at least two parts (50, 51), at least one of which is a solid part, the at least two parts being assembled by a diffusion connection technique and without melting, anda step of machining this blank in order to produce a blade with a defined profile.

An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

Disclosed is a method of making an integrally bladed rotor. According to the method, a titanium alloy rotor disk with 15-50% by volume of primary alpha grains with a grain size less than 10 m and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 m is subjected to thermal processing. After thermal processing, a blade having an airfoil and a base is positioned such that a base surface is in contact with an outer rim surface of the disk. Heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the disk outer rim surface.

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disk.

An oscillation jig includes: an oscillation jig base connected to an oscillation table; a first clamp member provided in the oscillation jig base; a second clamp member located at a position opposed to the first clamp member in an oscillation direction and configured to hold a first metal component together with the first clamp member; a link mechanism provided in the oscillation jig base, composed of a plurality of links connected together, connected to the second clamp member, and caused to extend and contract in the oscillation direction; and a clamp actuator configured to cause the link mechanism to extend and contract in the oscillation direction. When the first clamp member and the second clamp member hold the first metal component, a connection center line connecting connection centers of the respective links is made straight in the oscillation direction.

A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.