A component assembly of a propulsion system includes a component housing having a plenum configured to receive a pressurized gas flow of the propulsion system. The component assembly also includes a lug integrally formed with the component housing, a lug base region including a vent hole forming a gas path between the plenum and an interior of the lug, and a pin. The pin is configured to be positioned within the interior of the lug, where a cavity is formed between an interior surface of the lug and an exterior surface of the pin as positioned within the lug, thereby forming a compressed gas layer to reduce vibration of the pin within the cavity based on the pressurized gas flow passing from the plenum through the vent hole into the cavity.

A component assembly of a propulsion system includes a component housing having a plenum configured to receive a pressurized gas flow of the propulsion system. The component assembly also includes a lug integrally formed with the component housing, a lug base region including a vent hole forming a gas path between the plenum and an interior of the lug, and a pin. The pin is configured to be positioned within the interior of the lug, where a cavity is formed between an interior surface of the lug and an exterior surface of the pin as positioned within the lug, thereby forming a compressed gas layer to reduce vibration of the pin within the cavity based on the pressurized gas flow passing from the plenum through the vent hole into the cavity.

The invention relates to a pivot pin (5) for an epicyclic gear train sliding bearing, the pivot pin having axially opposed, laterally open circumferential grooves (25a), providing flexibility to the pivot pin and which radially separate two axially opposite lateral end portions of a central shank from two lateral cantilevered portions (27a,27b) of the pivot pin. At least one of the cantilevered lateral portions is hollowed out by at least one recess (65a).

The method comprises depositing a coating of metal material on the inside surface of the body (4) of the stator (36), impregnating said coating with a self-lubricating composite material (20), machining internal cells (28) in the thickness of the coating (10), and machining orifices (34) leading into the cells.

The invention relates to a compressor machine (10; 10a), in particular a generator or a compressor unit for compressing a gas, comprising a shaft (12) which is arranged in a housing (18) so as to be able to rotate about a longitudinal axis (11) and which is mounted in at least two radial bearings (20, 22) and a thrust bearing (24), the radial bearings (20, 22) and/or the thrust bearing (24) being in the form of an aerodynamic or aerostatic bearing, the shaft (12) being at least indirectly connected to a compressor stage (15) or driving stage comprising an impeller wheel (13).

A bearing includes a thrust gas bearing attached to a journal bearing and two or more converging-diverging orifices defined in a surface of at least one of the thrust gas bearing and the journal bearing. The converging-diverging orifices supply at least one pressurized gas to an interior of the bearing. Hydrodynamic lifting grooves are provided on the faces of the thrust gas bearing and the journal bearing and provide improved load capacity and sealing capabilities. Control over the ratios of the pressurized gases provides for additional sealing capabilities and reduced leakage. A metal mesh damper provides increased damping of the gas bearing.

A combined bearing for a turbomachine is disclosed. The combined bearing comprises in combination: a radial bearing member, a thrust bearing member and a bearing-fluid impeller of a bearing-fluid boosting pump in fluid communication with the thrust bearing member and the radial bearing member.

The invention relates to a turbocharger for an internal combustion engine, comprising a housing (1) with an exhaust-gas-side and an air-side turbine blade (2), a shaft (3) connecting the turbine blades, and at least one radially acting rotary bearing for mounting the shaft (3), wherein the rotary bearing is designed as a hydrodynamic floating bearing, wherein a lubricant flows in a completely surrounding bearing gap (8) of the rotary bearing in the direction of rotation and has a local lubricant pressure, the bearing gap (8) has a contouring (10, 11, 10a, 11a, 12, 13, 14, 15) due to which the at least two local maxima (PM1, PM2) of the lubricant pressure are formed at two defined angular positions (W1, W2) in the direction of rotation.

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).

A turbocharger includes: a bearing; a bearing wall portion having a bearing hole in which the bearing is arranged; a separation wall portion, which is provided on a radially outer side of the bearing hole with respect to the bearing wall portion, and forms an internal space with the bearing wall portion; an oil discharge port, which is formed in the separation wall portion, and communicates with the internal space; and a guide portion, which is provided to the bearing wall portion facing the internal space, and separates away from the oil discharge port in a direction of a plane perpendicular to a center axis of the bearing as approaching the oil discharge port in a direction of the center axis.