A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

Heat engines employing fluid bearing assemblies hermetically sealed with a closed flowpath for a working fluid are generally disclosed. For example, the heat engine includes a rotating drivetrain and a fluid bearing assembly. The rotating drivetrain includes a compressor section, an expander section, and a heat exchanger. The compressor section and expander section together define at least in part a closed flowpath for the flow of a working fluid. The heat exchanger is thermally coupled to the closed flowpath for adding heat to the working fluid. The fluid bearing assembly is configured to utilize the working fluid to support the rotating drivetrain. Further, the fluid bearing assembly is hermetically sealed with the closed flowpath.

A bearing bush of a turbocharger for radially mounting a shaft of the turbocharger. The bearing bush on an inner surface facing the shaft to be mounted, which forms a running surface of the bearing bush, has a microstructuring of multiple cup-shaped recesses at least in sections. The recesses have a maximum depth.

A heat transfer circuit includes a compressor, a condenser, an expander, and an evaporator. The compressor includes a shaft that is rotated to compress a working fluid and a gas bearing to support the shaft. A conduit is configured to supply a portion of the working fluid to the compressor to cool the gas bearing. A method of controlling a heat transfer circuit includes directing a working fluid through a main flow path of the heat transfer circuit that directs the working fluid through a compressor, a condenser, an expander, an evaporator, and back to the compressor. The method also includes suppling supplying a portion of the working fluid in the main flow path to the compressor to cool a gas bearing of the compressor.

Provided is a rotor system, including a rotating shaft, a shaft body of the rotating shaft being of an integrated structure and the rotating shaft being horizontally arranged; and a motor, an air compressor, a turbine, a thrust bearing and at least two radial bearings which are arranged on the rotating shaft. The thrust bearing and the at least two radial bearings are all non-contact bearings. The thrust bearing is arranged at a preset position on one side of the turbine close to the air compressor. The preset position is such a position that the center of gravity of the rotor system can be located between two radial bearings that are farthest apart among the at least two radial bearings.

The disclosure relates to a turbocharger for an internal combustion engine, comprising a housing (2) with a compressor blade (3) on the air side, a shaft (1) driving the blade (3), and at least one radially acting rotary bearing (5) for mounting the shaft (1). The bearing (5) is designed as a hydrodynamic sliding bearing, and a stationary bearing element (6) is penetrated by the shaft (1) and a first mounting is formed on one first side of the bearing element (6) and acts axially against a bearing collar (7) rotating with the shaft (1). The bearing element (6) forms a second mounting on an opposite second side which acts axially against a sealing bushing (8) rotating with the shaft (1). An oil supply (9) is designed in the bearing element (6), a plurality of flow surfaces (10) is formed on one surface of the bearing element (6) facing the collar (7) in the axial direction, and an individually dimensioned throttle element (11, 12) is designed in the oil supply (9) for each of the two mountings.

A bearing assembly may include a first bearing ring, a second bearing ring, and at least one row of rolling elements having a plurality of rolling elements that are disposed so as to be capable of rolling on a first raceway of the first bearing ring and on a second raceway of the second bearing ring. At least one hydrostatically supported first sliding bearing segment may be disposed on the first bearing ring. Further, the hydrostatically supported first sliding bearing segment may interact with a first bearing face that is disposed on the second bearing ring. The hydrostatically supported first sliding bearing segment may be mounted so as to be movable in a movement direction that is perpendicular to the first bearing face.

Provided is a bearing structure for a turbocharger including a turbine and a compressor provided at both ends of a rotation shaft and supporting the rotation shaft to a housing, including: a first radial bearing of an oil lubrication type provided on the side of the turbine of the rotation shaft; a second radial bearing corresponding to an air bearing provided on the side of the compressor of the rotation shaft; a gas seal portion provided in the periphery of the rotation shaft between the first radial bearing and the turbine; and a thrust bearing corresponding to an air bearing provided on the side of the compressor of the rotation shaft.

A fluid bearing for operably connecting a shaft to a center housing of a turbocharger is provided. The fluid bearing includes a single-piece bearing sleeve defining a bore between first and second ends that each form a thrust face. The sleeve includes first and second bearing portions proximal to an associated one of the first and second ends, and a shank connecting the first and second bearing portions. Each of the first and second bearing portions includes an outer bearing surface defining a maximum outer diameter, and each of the first and second bearing portions includes an inner bearing surface defining a minimum inner diameter for radially supporting the shaft in the bore. The inner bearing surface is a continuous surface free of grooves. The sleeve has a wall thickness defining oil passages spaced from the inner bearing surface and configured to supply oil to the thrust face.

A multi-film oil damper has a housing defining an annular damper cavity having an oil inlet in communication with a source of pressurized oil. A plurality of nested damper rings is disposed within the annular damper cavity, the plurality of nested damper rings defining a plurality of squeeze film annuli. Spacer rings are disposed adjacent opposed ends of the damper rings. A contact surface of the spacer rings extends radially beyond a first cylindrical surface of an associated damper ring for engaging a second cylindrical surface of an adjacent damper ring. Recesses are defined in the second cylindrical surface of the damper rings, the recesses fluidly communicating between the squeeze film annuli and the oil inlet.