The present invention relates to a two-layered blower unit of an air conditioner for a vehicle, which includes a means for smoothly guiding axially flowing air to flow in a radial direction and has optimized structure and arrangement for fixing the guide means.

A centrifugal rotating machine includes a rotor in which impellers are attached to the axial ends of a rotating shaft that extends in the axial direction, said impellers rotating in a rotating direction around the rotating shaft so as to draw in fluid from an intake side in the axial direction and discharge fluid from the outer side thereof in the radial direction. According to this device for measuring dynamic characteristics of said centrifugal rotating machine, a cover for covering an impeller is attached to a region of the impeller other than an intake opening on the intake side thereof, and a magnetic force generator for vibrating the impeller by magnetic force is disposed so as to face the cover.

A rotating machine includes: a casing, a rotary shaft rotatably supported in the casing and extending in a thrust direction, a first magnet installed on the rotary shaft, an attenuation mechanism supported by the casing and disposed to face the first magnet in the thrust direction, a second magnet installed in the attenuation mechanism to face the first magnet in the thrust direction and that repels the first magnet, an impeller installed on one end of the rotary shaft, and support sections that support the attenuation mechanism with respect to the casing. Furthermore, the attenuation mechanism includes: an attenuator that attenuates vibrations of the second magnet in the thrust direction, and a pushing-back unit that pushes the second magnet back toward the first magnet.

A compressor for an aircraft engine, has: a dual-impeller having: a first impeller having a first inlet and a first outlet located radially outwardly of the first inlet, and a second impeller rotatable with the first impeller, the second impeller having a second inlet and a second outlet located radially outwardly of the second inlet, the first inlet and the second inlet facing opposite axial directions; and first conduits having first conduit inlets and first conduit outlets, the first conduit inlets fluidly connected to the first outlet of the first impeller, the first conduit outlets fluidly connected to the second inlet of the second impeller; and second conduits having second conduits inlets fluidly connected to the second outlet of the second impeller, a second conduit of the second conduits disposed circumferentially between two adjacent first conduits of the first conduits.

A compressor for an aircraft engine, has: a dual-impeller having: a first impeller having a first inlet and a first outlet located radially outwardly of the first inlet, and a second impeller rotatable with the first impeller, the second impeller having a second inlet and a second outlet located radially outwardly of the second inlet, the first inlet and the second inlet facing opposite axial directions; and first conduits having first conduit inlets and first conduit outlets, the first conduit inlets fluidly connected to the first outlet of the first impeller, the first conduit outlets fluidly connected to the second inlet of the second impeller; and second conduits having second conduits inlets fluidly connected to the second outlet of the second impeller, a second conduit of the second conduits disposed circumferentially between two adjacent first conduits of the first conduits.

A compressor assembly of a turbocharger can include a compressor housing that includes a compressor wheel space and a diffuser section that extends from the compressor wheel space to at least one volute; a dual-faced compressor wheel disposed at least in part in the compressor wheel space where the dual-faced compressor wheel includes a first compressor wheel face and a second compressor wheel face oriented back-to-back; and a diffuser section divider disposed at least in part in the diffuser section where the diffuser section divider includes a first side that defines in part a first diffuser that includes a first set of vanes associated with the first compressor wheel face and a second side that defines in part a second diffuser that includes a second set of vanes associated with the second compressor wheel face.

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

Methods and systems are provided for compound boosted engine comprising an electric supercharger. In one example, the electric supercharger may be double-ended with a compressor arranged on either side of an electric motor and rotationally coupled to the electric motor via shafts. The electric supercharger may be configured to provide boost assist to a twin turbocharger system via a bypass channel adapted with a bypass valve.

A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

A rotating machine includes: a casing, a rotary shaft rotatably supported in the casing and extending in a thrust direction, a first magnet installed on the rotary shaft, an attenuation mechanism supported by the casing and disposed to face the first magnet in the thrust direction, a second magnet installed in the attenuation mechanism to face the first magnet in the thrust direction and that repels the first magnet, an impeller installed on one end of the rotary shaft, and support sections that support the attenuation mechanism with respect to the casing. Furthermore, the attenuation mechanism includes: an attenuator that attenuates vibrations of the second magnet in the thrust direction, and a pushing-back unit that pushes the second magnet back toward the first magnet.