The invention relates to a shaft-hub connection (1), particularly for mounting a rotor wheel on a shaft (10). The shaft-hub connection (1) comprises a shaft (10), a hub (20) and a filler material (30). The shaft (10) comprises an end section (11) on one end. A receiving region (21) is arranged in the hub (20). The end section (11) is arranged in the receiving region (21), with an intermediate layer of the filler material (30) positioned inbetween. The filler material (30) forms undercuts in the axial and rotational direction, in relation to the end section (11) and in relation to the receiving region (21), so as to create a positive embodiment of the shaft-hub connnection (1).

The turbine rotor assembly can include a turbine rotor disc drivingly mounted to a shaft for rotation about a rotation axis and having a central aperture extending coaxially with the shaft through the turbine rotor disc and being defined by a radially inner surface of the turbine rotor disc, a cavity downstream of and housing at least a part of the turbine rotor disc, a nut secured to the shaft and extending across the central aperture, a first air passage defined between an outer surface of the nut and the radially inner surface of the turbine rotor disc and fluidly connected to the cavity, a second air passage defined radially inward of the first air passage by an inner surface of the shaft and an inner surface of the nut.

Systems and methods for reducing friction during gas turbine engine assembly may comprise, a rear hub which may comprise a conical web, a horizontal arm coupled to the conical web, and/or a hub kickstand coupled to the conical web. The conical web, horizontal arm, and/or hub kickstand may converge at a pivot point. The hub kickstand may be removably coupled to the tie shaft.

An exhaust-gas turbocharger (1), having a shaft (2) which has an outer diameter (A.sub.2); a turbine wheel (5) which is fastened to the shaft (2); and a connecting device (8) via which the shaft (2) is fastened to the turbine wheel (5). The shaft (2) has, in the region of an end side (3), a shaft shoulder (4) with an outer diameter (A.sub.4) larger than the outer diameter (A.sub.2) of the shaft (2). The turbine wheel (5) has an external thread portion (7) integrally formed on its wheel rear side (6) The connecting device (8) has a sleeve nut (8A) which is screwed onto the external thread portion (7) and, in a process, engages behind the shaft shoulder (4) in order to brace the shaft (2) against the turbine wheel (5).

Provided is a method for bonding dissimilar metals to each other, the method comprising: dissimilar metal layer-forming steps (P2), (P3), (P4) for supplying, to form dissimilar metal layers; a second metal layer-forming step (P5) for supplying, on the surface of the dissimilar metal layers, a filler material formed of a second metal, and heating the filler material formed of the second metal to a temperature equal to or higher than a melting point of the second metal, to form a second metal layer formed of the second metal; and a second material-to-be-bonded welding step (P6) for welding a second material to be bonded that is formed of the second metal, onto the second metal layer.

A rotary machine includes a cylindrical rotary shaft extending in a direction of an axis, a fastening bolt having a bolt body that extends in a direction of an axis 0 in the rotary shaft to form fastening portions at both ends, a pair of rotary bodies each having an end portion in the direction of the axis that is fixed to each of the pair of fastening portions to be in contact with an end surface of the rotary shaft in the direction of the axis, and a bolt extension mechanism that temporarily extends the bolt body in the direction of the axis.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

A gas turbine engine rotor assembly comprises a torque tube, turbine stage and stiffening mass. The torque tube comprises a shaft extending from a forward location to an aft end, and a shaft fastening flange disposed at the aft end. The turbine stage comprises a disc, a disc adapter extending forward from the disc, and a disc fastening flange extending from the disc adapter and couplable to the shaft fastening flange at an interface. The stiffening mass is positioned proximate the interface to reduce operational stress in the torque tube. A method of reducing operational stress in a rotor assembly comprises de-stacking a rotor stack, separating a first stage rotor disc adapter from a torque tube, attaching a stiffening mass to an inner diameter of one or both of the disc adapter and the torque tube, attaching the disc adapter to the torque tube, and re-stacking the rotor stack.

The present invention generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival under conditions of either high temperature or oxidation resistance or saturated fluid abrasion.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. Each of the disk mounts connects the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount that further supports the first rotor blade.