Pumps and fluid-handling devices for modifying at least one property of a fluid and related method comprise a compensation assembly including at least one biasing element to enable a hydraulic insert to move within a housing.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more flexible spring flanges, one or more bayonet flanges, and one or more pilot flanges, each configured to engage a respective portion of the turbine machine.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more bayonet flanges, two or more apertures defined by a flange forming an annular hub mating surface of the nose cone and configured to receive an fastener therethrough, and one or more pilot flanges.

In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.

A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

The invention relates to an exhaust-gas turbocharger (1) having a compressor housing (3), having a bearing housing (28) which can be connected at one end to the compressor housing (3) by means of a first fastening device (19), and having a turbine housing (2) which can be connected to the bearing housing (28) at the other end of the latter by means of a second fastening device (20), with the compressor housing (3), the bearing housing (28) and the turbine housing (2) extending along an exhaust-gas turbocharger longitudinal axis (R), wherein the first fastening device (19) is designed as a plug-and-twist connecting device.

A support assembly for a gas turbine engine includes at least one inner support that extends about a circumferential axis and defines a cavity for receiving a control ring. At least one cover plate is attached to at least one inner support to enclose the cavity. At least one of the inner support and the cover plate includes a rail and the other of the inner support and the cover plate includes a groove for engaging the rail.

An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes a mount base and a bayoneted lug on the mount base. The mount base is configured to axially engage the flange where the bayoneted lug extends through the lug aperture. A fastener secures the components together. The fastener projects axially into a fastener aperture in the mount base for an axial length that is less than or equal to an axial length of the bayoneted lug.

A rotor, in particular a gas turbine rotor, having multiple rotor discs, each of which has an axial through-opening, and the rotor discs are axially clamped by at least one tie rod extending through the through-openings and are combined so as to form at least one rotor disc unit. At least one support ring which surrounds the tie rod and is in engagement with a paired rotor disc rests against the outer diameter of the tie rod, and the tie rod is supported against the rotor disc by the support ring. In order to axially secure the at least one support ring, at least one securing ring is provided which is secured to the paired rotor disc by a rotational lock and which holds the support ring against the rotor disc. The securing ring is prevented from unscrewing by a securing plate.

An assembly is provided for a piece of rotational equipment with an axis. This assembly includes a static structure, a bearing within a bore of the static structure, and a centering spring mounting the bearing to the static structure. The static structure is configured with the bore, a slot, a first slot surface and a second slot surface. The slot extends radially into the static structure from the bore. The slot extends axially within the static structure between the first slot surface and the second slot surface. The centering spring includes an annular hub and a mounting tab. The annular hub is within the bore. The mounting tab projects radially from the annular hub into the slot.