A radial turbine rotor associated with an engine includes a disk, and a plurality of blades spaced apart about a perimeter of the disk. Each blade includes a forward end, an aft end and a root. The radial turbine rotor includes a plurality of sectors, with each sector coupled to the root of a respective blade of the plurality of blades. Each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, and each sector of the plurality of sectors defines at least one pocket between the first surface and the second surface proximate the forward end that extends toward the aft end. The radial turbine rotor includes a feather seal slot defined between adjacent sectors of the plurality of sectors proximate the first surface.

A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.

Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality of radial members radially extending from the hub portion. The hub portions having a groove extending circumferentially about the rotational axis. The vibrational absorber having a ring member having a plurality of repetitive cellular structures each defining a hollow interior section and a plurality of deformable members each extending from the ring member and disposed in a corresponding one of the repetitive cellular structures. Each of the deformable members is configured to interact with the cyclic symmetric structure to damp vibration thereof.

A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality of radial members radially extending from the hub portion. The hub portions having a groove extending circumferentially about the rotational axis. The vibrational absorber having a ring member having a plurality of repetitive cellular structures each defining a hollow interior section and a plurality of deformable members each extending from the ring member and disposed in a corresponding one of the repetitive cellular structures. Each of the deformable members is configured to interact with the cyclic symmetric structure to damp vibration thereof.

A gas dispersion system may include a drive mechanism, a drive shaft having a proximal end operably coupled to the drive mechanism, extending to a distal end, and configured to transfer rotational motion and torque, a mixing element arranged at or near the distal end of the drive shaft including a hub and multiple blade pairs, each blade pair including an upper blade and a lower blade secured to the hub and cantilevering freely and generally radially away from the hub.

A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality of radial members radially extending from the hub portion. The hub portions having a groove extending circumferentially about the rotational axis. The vibrational absorber having a ring member having a plurality of repetitive cellular structures each defining a hollow interior section and a plurality of deformable members each extending from the ring member and disposed in a corresponding one of the repetitive cellular structures. Each of the deformable members is configured to interact with the cyclic symmetric structure to damp vibration thereof.

A vibration absorber damper and method of dissipating vibration energy in a rotatable structure which is nominally cyclic symmetric. The nominally cyclic symmetric structure includes a hub portion having a rotational axis and a plurality of radial members radially extending from the hub portion. The hub portions having a groove extending circumferentially about the rotational axis. The vibrational absorber having a ring member having a plurality of repetitive cellular structures each defining a hollow interior section and a plurality of deformable members each extending from the ring member and disposed in a corresponding one of the repetitive cellular structures. Each of the deformable members is configured to interact with the cyclic symmetric structure to damp vibration thereof.

A compressor wheel includes a shaft portion, which extends in the rotation axis direction of the compressor wheel. Blades protrude in the radial direction from the shaft portion. The blades are spaced apart from each other in the circumferential direction of the compressor wheel. The compressor housing has an accommodation space that accommodates the compressor wheel. The compressor housing also has an introduction passage defined therein. The introduction passage is connected to the accommodation space from the intake side and introduces intake air into the accommodation space. Plate-shaped guide vanes protrude from the inner wall surface of the introduction passage. The guide vanes are spaced apart from each other in the circumferential direction of the introduction passage. The number of the guide vanes is the smallest odd number that is greater than the number of the blades.