A turbine rotor for an exhaust gas turbine has a turbine rotor wheel made of a highly heat-resistant metal alloy and a rotor shaft made of steel. A rotor wheel hub and a rotor shaft end are connected to each other in a metallurgical bond by way of a solder connection. The rotor shaft end and/or the rotor wheel hub is formed with a central recess, which acts as a thermal choke. A closing plug is arranged in the respective recess, forming a closed cavity with the recess and closing off the recess toward the respective end face. The solder connection is formed between the end faces of the rotor wheel hub and the rotor shaft, between the closing plug and the rotor wheel hub, and between the closing plug and the rotor shaft.

A rotor (10) of a rotary machine (T1) according to the invention includes a plurality of rotor members (20, 30, and 40) which are joined to each other in the axial direction in which the axis (P) extends, and among the plurality of rotor members (20, 30 and 40), the first rotor member (30) in hydraulic fluid injection portions (3a and 3b) of a passageway (3) is formed of Ni-based alloy so that the inside thereof is hollow throughout the entire length in the axial direction.

A method to repair a peripheral portion of a body including: removing a damaged portion from a peripheral region of the body; mounting a replacement ring to the body after removal of the damaged portion; forming an interior groove between the inner surface of the replacement ring and the peripheral surface of the body, wherein the groove is between ridges; welding the replacement ring to the body, wherein weld material is applied only within end grooves, and leaving a void in said center section after the welding of the replacement ring to the body.

A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a raised portion having a first mating surface. The sealing arrangement further includes a locking pin having a planar section for receiving the first raised surface. The locking pin also includes a pin section having a second mating surface that abuts against the first mating surface to thereby lock the locking pin and the seal strip segment together. Further, the pin section is located within the aperture to stop circumferential movement of the seal strip segment relative to first and second disks.

An inertia friction welding (IFW) method for welding together two portions of a rotary subassembly for a turbine engine is provided. At least one of the portions includes a plurality of hooked teeth at its periphery for anchoring blade roots. One of the two portions for welding together is held by a clamp and set into rotation by a motor, and the other one of the two portions for welding together is held by a torque take-up ring gear mounted on a carriage that is movable in translation. In order to avoid any crack formation in the hooks of the teeth during welding, the plurality of hooked teeth is covered with a damper device for shifting the frequency of the vibratory response of the teeth, thereby creating damping.

A turbine rotor includes a high- and low-temperature side rotor base materials. The high- and low-temperature materials include concavities and grooves. The turbine rotor has an enclosed space formed by the concavity of the high- and low-temperature materials being disposed opposingly, and a gap formed by the grooves of the high- and low-temperature materials being disposed opposingly. The turbine rotor contains a buildup welding section formed between the high- and low-temperature materials, which has the same composition as that of the high- or low-temperature material, and has a penetration bead on the enclosed space side, and the gap contains a weld metal filled therein. Thus, a stable penetration bead can be formed in a dissimilar material welded rotor combining two kinds of alloy materials with different thermal properties, and then generation of a non-welded portion of a butting section that becomes a start point of fracture can be suppressed.

A method of producing a turbine rotor, in particular a steam turbine rotor, is provided. A forged and machined existing steam turbine rotor having partially larger dimensions as dimensions of an intended rotor is provided. The form of the existing rotor is compared with the form of the intended rotor and a position of the intended rotor within the existing rotor is chosen. Material is applied by build-up welding on portions of the existing rotor where not enough material is present for machining the intended rotor at the chosen position. The intended rotor is produced at the chosen position by machining the existing rotor.

A nickel (Ni) based alloy for forging includes: 0.001 to 0.1 wt. % of carbon (C); 12 to 23 wt. % of chromium (Cr); 3.5 to 5.0 wt. % of aluminum (Al); 5 to 12 combined wt. % of tungsten (W) and molybdenum (Mo) in which the Mo content is 5 wt. % or less; a negligible small amount of titanium (Ti), tantalate (Ta) and niobium (Nb); and the balance of Ni and inevitable impurities.

A method of repairing a damaged dovetail on a peripheral portion of a turbine wheel includes the steps of removing buckets from the dovetail; removing a damaged dovetail from the peripheral portion of the turbine wheel, leaving a rotor wheel body having a peripheral rim; disposing a replacement ring about the peripheral rim, the replacement ring and the rim defining therebetween a pair of end grooves and a center section; and welding the replacement ring to the peripheral rim, with weld material applied only within the end grooves, leaving a void in the center section.

An axial compressor rotor assembly includes a plurality of rotor disks extending axially along and circumferentially about a central axis between an upstream end and a downstream end. The rotor disks extend radially between an inner radial hub and an outer radial rim, and axially between a forward rim end and a rearward rim end. An airfoil extends spanwise from each of the rotor disks. A first rotor disk is disposed forward of a second rotor disk. The second rotor disk includes an interstage shaft. The interstage shaft includes an outer radial end, an inner radial end, and an arm. The arm extending axially from an outer surface of the interstage shaft to a distal end. The rearward rim end of the first rotor disk is fixedly joined to the distal end of the arm, for example, by inertia welding.