A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.

A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.

An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.

A device for assembling a turbine engine is configured for centering a shaft of a second module relative to a longitudinal axis of a hollow hub placed in front of a first module, the first module including a longitudinal cavity opening at the front into the hollow hub and passing through the first module until a rear end, the shaft configured to be inserted into the longitudinal cavity. The device includes a centering element and a guiding tube. The centering element is configured to be placed in the hollow hub. The guiding tube is configured to enter into at least one portion of the longitudinal cavity of the first module. The device is arranged so that the guiding tube slides inside the centering element. The invention also relates to the assembly formed by the device and a calibration jig, as well as an assembly method using same.

The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.

A turbocharger shaft includes a connection portion at a connection with a wheel of the turbocharger. The shaft includes a stainless steel cladding at least along one or more grooves of the connection portion to reduce the risk of cold cracking and bending fatigue.

An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a shaft base, a flange and a plurality of lobes. The shaft base extends axially along an axis between a shaft first end and a shaft second end. The flange is connected to the shaft base at the shaft first end. The flange projects radially out from the shaft base. The flange includes a plurality of fastener apertures, and the fastener apertures include a first fastener aperture. The lobes are arranged circumferentially about the axis. Each of the lobes is connected to and projects radially away from the shaft base. Each of the lobes is connected to and projects axially out from the flange. The lobes include a first lobe and a second lobe. The first fastener aperture is arranged circumferentially between the first lobe and the second lobe. The second lobe radially overlaps the first fastener aperture.

An impeller for a centrifugal compressor, the impeller rotatable about a central axis, has: an outer hub body including a first material and extending around the central axis, the outer hub body defining a gaspath face extending from an inlet to an outlet, the gaspath face extending radially away from the central axis from the inlet to the outlet; blades protruding from the gaspath face and circumferentially distributed around the central axis; and an inner hub body extending around the central axis, the inner hub body secured to the outer hub body, the outer hub body axially overlapping and extending around the inner hub body, the inner hub body made of a second material being more cold dwell resistant than the first material.

A process for cold working of the inner surface of a bore in a centrifugal compressor wheel along only a fractional portion of the bore length (i.e., along less than a full axial length of the bore), thereby creating a zone of compressive residual hoop stress in the metal surrounding the bore where the wheel needs the beneficial residual stress. The process purposefully avoids cold working of the bore at locations adjacent to high-stress areas and features of the wheel, where cold working in such locations could negatively impact the wheel's overall life.

A forced induction device for an internal combustion engine is provided, which includes a shaft, and a compressor wheel that is threadably mounted to the shaft, and a tool that is configured to engage one or more through bores in the compressor wheel to thread and unthread the compressor wheel onto and off of the shaft. The compressor wheel has a plurality of blades with leading edges that converge at an apex. The apex is aligned with a centerline of the shaft. The tool allows a technician to rotate the compressor wheel relative to the shaft to install or remove the compressor wheel from the shaft without applying any pressure to the blades of the compressor wheel. An associated assembly method is also provided.