This impeller is provided with: an impeller body formed in a disk-like shape and having a boss hole section formed therein, the boss hole section allowing a rotating shaft to be fitted therein; and compressor blades provided on the front surface side of the impeller body so as to protrude from the hub surface of the impeller body. The impeller consists either of a first resin member and a second resin member, which are engaged with each other and which consist of a resin, or of a resin member and a metallic member, which are engaged with each other.

This impeller is equipped with: an impeller body formed from a resin and shaped as a disk with an axis as the center thereof, and having a boss hole section formed therein which a rotating shaft for rotating around the axis engages; compressor blades provided on the front-surface side of the impeller body; and a ring-shaped reinforcing ring provided inside the impeller body in the circumferential direction of the impeller body.

This impeller is equipped with: an impeller body formed from a resin and shaped as a disk with an axis as the center thereof, and having a boss hole section formed therein which a rotating shaft for rotating around the axis engages; compressor blades provided on the front-surface side of the impeller body; and a ring-shaped reinforcing ring provided inside the impeller body in the circumferential direction of the impeller body.

A rotary machine includes a machine stator and a machine rotor rotatable relative to the machine stator and having a metal shaft portion, a composite impeller portion, and at least a first metal ring portion securing the composite impeller portion to the metal shaft portion, the metal ring portion having a first interface with the composite impeller portion and a second interface with the metal shaft portion.

A radial turbomachine has: a fixed casing; at least one rotor disc installed in the casing and rotatable in the casing around a respective rotation axis; a plurality of annular rotor elements coaxial with the rotation axis, axially projecting from a front face of the rotor disc and/or from a rear face of the rotor disc; a plurality of annular fixed elements coaxial with the rotation axis, axially projecting from the casing and each positioned in a radially external position with respect to a respective annular rotor element; a plurality of sealing devices radially interposed between at least some of said annular rotor elements and the respective annular fixed elements.

An object of the present invention is to provide a bearing structure of a turbocharger that can prevent generation of unusual noise and a decrease in operation efficiency and that can reduce manufacturing costs. The bearing structure of a turbocharger to accomplish such an object, includes a rotor shaft, a ball bearing, a retainer, and a housing. The rotor shaft is provided with a turbine impeller mounted on a first end and a compressor impeller mounted on a second end.

The ball bearing includes an inner ring and an outer ring that are supported in relatively rotatable manner. The retainer holds the outer ring. Between the inner ring and an outer peripheral surface of the rotor shaft, oil in a film state is interposed to form an oil film damper.

A turbomachine includes a turbine impeller having a rotational axis, a first end portion, and a second end portion. The turbine impeller includes main blades and splitters. Each of the main blades has a blade first edge provided at the first end portion and a blade second edge provided at the second end portion and extends from the blade first edge to the blade second edge. Each of the splitters has a splitter first edge and a splitter second edge and extends from the splitter first edge to the splitter second edge. The blade first edge and the splitter first edge are arranged on a plane perpendicular to the rotational axis. The splitter second edge is positioned between the splitter first edge and the blade second edge along the rotational axis. The main blades and the splitters are arranged alternately in a circumferential direction around the rotational axis.

A vane is provided for use in a fluid flow of a turbine engine. The vane includes a thin-walled radially extending aerodynamic vane body having axially spaced leading and trailing edges, and a radially outer platform. The wall of the vane body includes an outer shell and an inner shell and defines an interior cavity therein for flowing a cooling medium. A radially extending load strut is arranged at the inner shell of the wall of the leading edge of the vane body.

An electric machine (212) comprises a turbomachine rotor (203) having a hub (302) and an axis of rotation (A-A) about which the turbomachine rotor is arranged to rotate. The turbomachine rotor includes a plurality of blades (301). Each blade has a root (303) attached to the hub, a tip (304) remote from the hub, a leading edge (305) and a trailing edge (306), a pressure side and a suction side (307). A stator (502) is located circumferentially around the turbomachine rotor. Each blade further comprises a rotor element at the tip comprising a permanent magnet having a first pole (401) and a second pole (402), the first pole being located adjacent the suction side of the blade and the second pole being located adjacent the pressure side such that a magnetic flux path extends perpendicularly through the blade tip.

An electric machine (212) comprises a turbomachine rotor (203) having a hub (302) and an axis of rotation (A-A) about which the turbomachine rotor is arranged to rotate. The turbomachine rotor includes a plurality of blades (301). Each blade has a root (303) attached to the hub, a tip (304) remote from the hub, a leading edge (305) and a trailing edge (306), a pressure side and a suction side (307). A stator (502) is located circumferentially around the turbomachine rotor. Each blade further comprises a rotor element at the tip comprising a permanent magnet having a first pole (401) and a second pole (402), the first pole being located adjacent the suction side of the blade and the second pole being located adjacent the pressure side such that a magnetic flux path extends perpendicularly through the blade tip.