A turbocharger for an internal combustion engine, comprises a housing (2) with a compressor blade (3) on the air side, a shaft (1) driving the compressor blade (3), and at least one radially acting rotary bearing (5) for mounting the shaft (3), wherein the rotary bearing (5) is designed as a hydrodynamic sliding bearing, wherein 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, wherein an oil supply (9) for supplying the mountings is designed in the bearing element (6), wherein a plurality of flow surfaces (10) with a height (h) varying in the circumferential direction is formed on one surface of the bearing element (6) facing the bearing collar (7) in the axial direction, wherein an individually dimensioned throttle element (11, 12) is designed in the oil supply (9) for each of the two mountings.

A turbo fluid machine includes a rotary shaft configured to rotate in one rotational direction, and a radial foil bearing. The radial foil bearing includes: a bump foil formed of an elastic thin plate having a corrugated shape. The bump foil is divided into first and second foil portions located respectively on one side and on the other side in an axial direction of the rotary shaft. Ridges on the first foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the first foil portion adjacent to the other side toward the one side in the axial direction. The ridges on the second foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the second foil portion adjacent to the one side toward the other side in the axial direction.

A gas turbine propulsion system includes a shroud that defines a fluid flow path. A gas turbine engine in the fluid flow path includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor. An electric generator in the fluid flow path defined by the shroud includes a rotor coaxially aligned with the turbine. A propulsor is upstream from the gas turbine engine, and an electric motor is operably coupled to the propulsor to rotate the propulsor. The propulsor is rotationally isolated from the gas turbine engine so that the propulsor rotates independently from operation of the gas turbine engine.

A planetary gearbox has a sun gear, planet gears, a ring gear and plain bearing pins. A plain bearing pin is arranged in a respective planet gear, wherein the plain bearing pin and the planet gear form a lubricated plain bearing which includes a plain bearing gap, and on its contact face, the plain bearing pin forms a feed pocket which is configured to receive oil and output it to the plain bearing. On its contact face, the plain bearing pin forms an additional feed pocket which is configured to receive oil and output it to the plain bearing, is spaced from the feed pocket in the circumferential direction, and is connected to the feed pocket such that oil from the additional feed pocket can flow on the contact face of the plain bearing pin to the feed pocket.

The invention concerns a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear and a plurality of plain bearing pins. Here, a plain bearing pin is arranged in each planet gear, wherein the plain bearing pin and the planet gear form a lubricated plain bearing, and the plain bearing pin forms a crowning at its contact face, wherein the outer diameter of the contact face decreases from a maximum outer diameter towards at least one axial end of the contact face. The crowning of the contact face is configured such that the contact face is concavely shaped adjacent to at least one axial end of the contact face or to a cylindrical region adjoining the axial end.

An airfoil journal bearing including a bearing housing having an inner surface forming a hollow so that a rotation shaft is insertable in the hollow; an airfoil in the hollow so that, when the rotation shaft is inserted in the hollow, the airfoil encloses at least 180 to 360 degrees of a circumference of the rotation shaft; and a ring member enclosing an outer surface of the bearing housing. The bearing housing includes an insert slit formed through the bearing housing from the inner surface of the bearing housing to the outer surface of the bearing housing. The airfoil includes an insert part bent from a circumferential direction of the airfoil to a radial direction of the bearing housing and extending, through the insert slit, to the outer surface of the bearing housing. The airfoil is engaged with an outer surface of the ring member through the insert part.

A planetary gear mechanism for a gas turbine engine includes a planet carrier and a planet pin rotationally fixedly connected thereto and on which a planet gear is rotatably mounted via a planet bearing. The planet pin is at least approximately hollow cylindrical in regions. A sleeve in the planet pin comprises an oil feed region through which the bearing is supplied with oil. An outer side region of the sleeve and an inner side region of the planet pin are press fit together. The sleeve has a web radially inside the outer side region. The web extends radially through the sleeve and is fixedly connected to the outer side region in an end region of a main load zone of the bearing, and at the other end is fixedly connected to the outer side region on the opposite side thereof in the radial direction of the sleeve.

A planetary gear mechanism for a gas turbine engine includes a planet carrier and a planet pin rotationally fixedly connected thereto and on which a planet gear is rotatably mounted via a planet bearing. The planet pin is at least approximately hollow cylindrical in regions. A sleeve in the planet pin comprises an oil feed region through which the bearing is supplied with oil. An outer side region of the sleeve and an inner side region of the planet pin are press fit together. The sleeve has a web radially inside the outer side region. The web extends radially through the sleeve and is fixedly connected to the outer side region in an end region of a main load zone of the bearing, and at the other end is fixedly connected to the outer side region on the opposite side thereof in the radial direction of the sleeve.

A gas turbine engine with a rotor comprising a turbine and compressor, mounted in a housing surrounding the rotor. The rotor rotates on one or more hydro bearings, the profiles of the outer surface of the rotor and the inner surface of the housing generating the hydro bearing(s). A combustion chamber is formed within the housing, and the combustion products of the fuel/air mixture are directed from the combustion chamber to the turbine. The housing and rotor are formed by an additive manufacturing process in a single procedure, with the rotor enclosed within the housing, and unsupported by any mechanical connections. A gas turbine respiratory ventilator system is described using a compressed oxygen flow to power the turbine which rotates the centrifugal blower for generating the air flow for respiration of the patient. The oxygen exhausted from the turbine can then be used to supplement the air flow.

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.