A sealing device includes a sealing main body surrounding a rotor shaft rotating about an axis from an outer periphery side. The sealing main body includes an inside surface facing an outside surface of the rotor shaft with clearance and a plurality of hole parts formed recessed to an outer side in a radial direction from the inside surface and arrayed in a circumferential direction of the inside surface and in a direction of the axis. The hole parts have an inner peripheral wall in which a spiral groove extending twisting toward the outer side in a radial direction is formed.

A rotating machine includes a shaft, a first impeller wheel, and a second impeller wheel. The rotating machine also includes a first seal assembly including a first carbon ring disposed about the shaft, with the first carbon ring having a first carbon surface. The first seal assembly also includes a first mating ring disposed about the shaft, with the first mating ring having a first mating surface facing and configured to contact the first carbon surface. The rotating machine additionally includes a second seal assembly including a second carbon ring disposed about the shaft, with the second carbon ring having a second carbon surface. The second seal assembly also includes a second mating ring disposed about the shaft, with the second mating ring having a second mating ring surface facing and configured to contact the second carbon surface.

Provided is a combustible gas compressor for compressing combustible gas. The combustible gas compressor comprising: a compressor housing having an impeller rotatably disposed therein; a motor housing having a motor for driving the impeller therein; and a bearing rotatably supporting a rotational shaft transmitting rotation driving force of the motor to the impeller, wherein the compressor housing is integrally formed with the motor housing, the bearing is a self-lubricating type bearing not using lubricant oil, the self-lubricating type bearing being configured to lift the rotational shaft using gas.

A seal system for a bearing chamber of a turbomachine includes a baffle element encircling the axis of the machine. The baffle element is formed with front surface including a plurality of gutter surfaces which are angularly spaced about the rotational axis. The seal system can thus be mounted in any one of a plurality of orientations with respect to the direction of gravity, such that in any of the orientations one of the gutter surfaces is directed downwardly.

A gas compression device comprises a first impeller, a rotary shaft on which the first impeller is mounted, and a plurality of rotating members through which the rotary shaft is inserted so that the plurality of rotating members rotate with the rotary shaft. The rotary shaft includes a flange having a first surface perpendicular to an axial direction and projecting in radial directions of the rotary shaft, a rear surface of the first impeller is in contact with the first surface, and the plurality of rotating members are disposed on an opposite side of the flange from the first impeller.

A number of variations may include a product comprising: a turbomachinery device comprising: an electric motor surrounding a portion of a shaft constructed and arranged to selectively drive the shaft in rotation about a rotational axis, wherein the electric motor further comprises a stator comprising a lamination stack; a housing surrounding the electric motor, wherein the housing includes a plurality of channels constructed and arranged to lubricate a first bearing; and wherein the lamination stack includes at least one retention component wherein the retention component is constructed and arranged to locking the stator in an axial direction while locking rotation of the stator about the rotational axis and wherein the retention component further comprises at least one conduit constructed and arranged to pass fluid through the electric motor to a second bearing.

A gas turbine engine includes a spool which rotates in use, a static structure and an air bearing, the air bearing being provided at an interface between the spool and the static structure.

An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.

A centrifugal compressor including: a impeller; a wall portion having an opposed surface that is spaced apart from and opposed to a back surface of the impeller; an insertion hole, which is formed in the wall portion, and is configured to receive a shaft inserted into the insertion hole; a bearing, which is provided in the insertion hole or apart from the impeller with respect to the insertion hole, and is configured to axially support the shaft through interposition of grease being a lubricant inside; an electric motor which is provided on a side opposite to the impeller over the wall portion; and an opposed hole, which is formed in the wall portion, is disclosed. The opposed hole has one end opened in the opposed surface and another end opened at a position opposed to a stator of the electric motor on a side opposite to the impeller.

A turbo compressor of an exhaust gas recirculation of an internal combustion engine, with a compressor housing, a compressor rotor, a shaft that is coupled to the compressor rotor and mounted in the compressor housing, a piston ring seal to prevent an exhaust gas blow-by flow in the direction of bearings, and a labyrinth seal, which seen in the direction of the exhaust gas blow-by flow, is positioned upstream of the piston ring seal.