A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (Θ) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes an inducer portion and an exducer portion, where, in the inducer portion, in a direction outwardly from the hub, each of the blades includes positive lean angles, a zero lean angle and negative lean angles and where, in the exducer portion, in a direction outwardly from the hub, each of the blades includes negative lean angles, a zero lean angle and positive lean angles.

According to an embodiment, a method of correcting a bend of a joint type-turbine rotor comprises: measuring displacement of a convex portion of the bend at a joined portion of the joint type-turbine rotor or displacement of a surface opposite to the convex portion in a circumferential direction of the joint type-turbine rotor; heating the convex portion; and cooling the joined portion after the step of heating. The steps of heating and cooling are performed during the step of measuring.

To provide a turbine rotor which enables mass production with a low-cost apparatus and which capable of suppressing leaning of the rotor shaft after welding to improve the yield, while a turbine blade rotor 12 and the rotor shaft 14 are fit to each other with concave and convex portions 12a and 14a and are permitted to be rotated, laser beam L from a laser beam generating device 30 is applied to a joint face 16 along the circumferential direction to weld the welding portion. Then, laser beam L is polarized to temper a region X on the rotor shaft side containing the welding portion with laser beam L. In contrast to residual stress R.sub.1 having a local angular distribution generated during the welding, residual stress R.sub.2 is permitted to be generated over the entire circumference by tempering. Leaning of the rotor shaft 14 after cooling is thereby be suppressed.

A method for manufacturing a shaft body by welding a plurality of shaft members together and forming the shaft body, the method including: a primary tempering step of subjecting a range in at least one of the shaft members, which is in the vicinity of an end of another shaft member side adjacent thereto, to tempering before the shaft members are welded together so that a strength of an end side of a region thereof is lower than a strength at a side which is opposite to the end of the region thereof; a welding step of welding the shaft members together after the primary tempering step; and a secondary tempering step of tempering the vicinity of a weld part between the shaft members after the welding step.

It is an objective of the invention to provide a steam turbine rotor that is capable of both reducing SCC susceptibility and improving LCF life thereof. There is provided a steam turbine rotor, comprising a rotor disk in a low pressure final stage L-0, and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0, the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding, wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa.

The present disclosure relates to a rotor for a gas turbine having a plurality of rotor disks arranged one behind the other in a rotor axis and connected to one another, where the geometrical form of the disks leads to the formation of cavities between adjacent disks. The rotor extends from a compressor part to a turbine part and has a central part between the compressor part and the turbine part, wherein the first turbine disk, the last compressor disk and the central part enclose a central cavity. A cooling system extends at least partially through the rotor with a central cooling section disposed between at least one inlet pipe and at least one outlet pipe, at least partially through the first turbine disk and/or the last compressor disk.

A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole.

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.

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.

Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN) for the hub disk and a maximum critical temperature for the rotor blades (T.sub.BLADE.sub._.sub.MAX) is established such that T.sub.BLADE.sub._.sub.MAX is less than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below T.sub.BLADE.sub._.sub.MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.