A turbine rotor disk and a method of making the turbine rotor disk using solid state bonding techniques are disclosed. The turbine rotor disk includes a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F. The turbine rotor disk also includes a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.

A method of joining a first component to a second component at respective connection surfaces, comprising, in order, applying a local surface treatment to the connection surface of at least one of the first and second components in order to locally alter the microstructure to a depth of between 60 μm and 10 mm below the connection surface; and joining the first component to the second component using a welding process.

A turbine rotor disk and a method of making the turbine rotor disk using solid state bonding techniques are disclosed. The turbine rotor disk includes a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F. The turbine rotor disk also includes a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.

A method for producing a centrifugal pump impeller having a base plate, which is a single piece with pump blades and a cover plate, which consists of a thermoplastic material, wherein contact areas are available, which are heated and melted by means of ultrasonic excitation and form a close bonded connection after cool-down. The objective of the invention is to ensure inherent stability with the individual parts and a simple and reliable pre-assembly as well as a fixed mechanical connection, wherein only a small amount of excitation energy is required, with a centrifugal pump impeller comprising a base plate and cover plate.

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.

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 present invention relates to a relief valve (1) for a turbocharger, in which the crank arm (3) is made of a first material and the shaft (4) is made of a second material different from the first material used for manufacturing the crank arm (3), each of the materials containing a composition that provides the necessary properties according to the application of each component of the relief valve (1). The present invention also relates to a process for manufacturing the relief valve (1), which allows the crank arm (3) and the shaft (4) to be manufactured separately, using different materials for the manufacture of each component.

A method of joining a first work piece and a second workpiece. The first and second workpieces may be rotor wheels of a rotor for a turbomachine. At least one of the workpieces includes an oxide dispersion strengthened alloy material and the first and second work pieces may be joined by welding a cladding on at least one of the workpieces to the other of the workpieces, without welding a substrate of the at least one workpiece which includes an oxide dispersion strengthened alloy material.

Disclosed is an adjustable guide vane for a turbomachine, especially for a turbine stage or compressor stage of a gas turbine, which comprises a vane airfoil for deflecting a working fluid of the turbomachine and which is produced at least partially from a second material, and at least one first vane section which is produced from a first material which is different from the second material.

A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.