A turbine rotor includes a base and a plurality of blades. The base and the blades curve such that radially outward portions of the base and the blades extend in a direction with a greater component in a radial direction than in an axial direction. Radially central portions of the base and the blade extend in a direction with the two components being closer. Radially inner sections of the base and the blades extend in a direction with a greater component in the axial direction than in a radial direction. There is a cooling channel arrangement in the turbine rotor. The cooling channel arrangement includes impingement cooling for a nose and serpentine passages for cooling sections of the platform circumferentially intermediate the blades, and distinct serpentine passages for cooling the plurality of blades. A turbomachine and method are also disclosed.

An impeller of a rotating machine according to at least one embodiment includes: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. A back surface of the disc has a recess extending in a circumferential direction in a radial range where the blade is disposed.

A high-efficiency, high specific power electric motor/generator for aircraft use provides a cantilevered external rotor removed from load thrust. and vibration by an isolator and hearing set between the rotor and stator reducing material demands and weight otherwise required for stiffness to preserve close rotor/stator proximity.

A high-efficiency, high specific power electric motor/generator for aircraft use provides a cantilevered external rotor removed from load thrust. and vibration by an isolator and hearing set between the rotor and stator reducing material demands and weight otherwise required for stiffness to preserve close rotor/stator proximity.

A forced induction device (100) includes: a rotor (1) which includes a turbine side shaft portion (11), a compressor side shaft portion (12), and a connection shaft portion (13) connecting these to each other; a turbine side bearing (5) which supports the turbine side shaft portion (11); and a compressor side bearing (6) which supports the compressor side shaft portion (12). A rigidity of the connection shaft portion (13) is lower than that of the turbine side shaft portion (11) and the compressor side shaft portion (12) so that a node in a mode shape at each critical speed involving with an operating rotational speed region of the rotor (1) is located between the turbine side bearing (5) and the compressor side bearing (6).

An exhaust turbocharger turbine wheel can include a hub that includes a nose, a backdisk with a shaft joint portion, and a rotational axis; blades that extend from the hub to define exhaust flow channels where each of the blades includes a leading edge, a trailing edge, a hub profile, a shroud profile, a pressure side, and a suction side; where the backdisk includes an outer perimeter radius measured from the rotational axis of the hub, an intermediate radius at the shaft joint portion measured from the rotational axis of the hub, and an annular recess disposed between the intermediate radius and the outer perimeter radius and defined in part by three-dimensional bolster regions, where each of the three-dimensional bolster regions includes a footprint and a height measured at least in part in a direction of the rotational axis of the hub.

A portable system is disclosed for collecting a sample from exhaled breath of a subject. Drug substance in the exhaled breath are detected or determined. The sample is collected for further analysis using mass-spectroscopy. The system comprises a sampling unit and a housing arranged to hold the sampling unit, the sampling unit is adapted to collect non-volatile and volatile compounds of the at least one drug substance from the exhaled breath from the subject. The housing has at least one inlet for the subject to exhale into the housing to the sampling unit and at least one outlet for the exhaled breath to exit through.

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 method of manufacturing an impeller includes attaching blades to a hub. The impeller includes the blades, the hub, and a shroud. The blades each include a tip, and the shroud includes an inner surface and at least one ring extending from the inner surface. The method also includes applying a brazing compound to the tips of the blades and to the inner surface of the shroud. The method includes inserting the blades and the hub into the shroud such that the tips of the blades press against the rings. The rings and the tips of the blades form an interference fit between the rings and the tips of the blades that maintains a consistent gap between the shroud and the blades during manufacture of the impeller. A compressor including the impeller is also disclosed.

A method of manufacturing an impeller includes attaching blades to a hub. The impeller includes the blades, the hub, and a shroud. The blades each include a tip, and the shroud includes an inner surface and at least one ring extending from the inner surface. The method also includes applying a brazing compound to the tips of the blades and to the inner surface of the shroud. The method includes inserting the blades and the hub into the shroud such that the tips of the blades press against the rings. The rings and the tips of the blades form an interference fit between the rings and the tips of the blades that maintains a consistent gap between the shroud and the blades during manufacture of the impeller. A compressor including the impeller is also disclosed.