A turbocharger is provided with: a rotational shaft; a rolling bearing rotatably supporting the rotational shaft; an oil film damper disposed radially outward of an outer ring of the rolling bearing; and a housing having a first axial retaining portion and a second axial retaining portion, disposed adjacent to both ends of the oil film damper in the axial direction, respectively, for restricting movement of the outer ring in the axial direction. An axial end surface of the outer ring, or a facing surface of the first axial retaining portion or the second axial retaining portion facing the axial end surface of the outer ring has: a coefficient of static friction smaller than that of a portion of the housing excluding the first axial retaining portion and the second axial retaining portion; or has a recess where oil of the oil film damper can enter.

The present disclosure relates to a bearing supporting assembly and a machining method thereof, and a centrifugal compressor. The bearing supporting assembly includes: bearing supports, provided with through holes for mounting radial bearings; and a fixing plate, detachably mounted at one end of each of the bearing supports along an axial direction, sides, away from the bearing supports, of the fixing plates being configured to mount first thrust bearings.

A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.

Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine discs that are interleaved between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between this first shaft and a stator casing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between this second shaft and another stator casing (28).

A flexible cartridge assembly can include a flexible shell that includes a flexible portion disposed between a compressor-side portion and a turbine-side portion, where the flexible portion includes a series of arc-shaped cutouts disposed axially along at least a portion of the flexible portion; a compressor-side bearing assembly; and a turbine-side bearing assembly.

A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.

A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

When the compressed air is not applied, an inclined surface, which is positioned at an upstream side with respect to the supply direction of the compressed air, of the lip part is in contact with the inclined surface of the inner ring. When the compressed air is applied, a contact area between the inclined surface, which is positioned at the upstream side with respect to the supply direction of the compressed air, of the lip part and the inclined surface of the inner ring becomes smaller, as compared to when the compressed air is not applied.