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.

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 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.

An engine assembly defining an axial direction (A) and including a gearbox, an engine core including at least one rotor, and a flexible coupling shaft having a first end and a second end along the axial direction (A). The first end of the flexible coupling shaft is connected to the engine core and the second end of the flexible coupling shaft is connected to the gearbox. A damper system is positioned at the second end of the flexible coupling shaft. The damper system is configured to reduce vibrations to the flexible coupling shaft during operation of the engine assembly.

A rocket engine propulsion system having improved engine performance is described herein. The rocket engine propulsion system includes an axial counterbalance to reduce or eliminate axial thrust exerted on components of a turbopump. The axial counterbalance can allow for a larger range of axial thrust forces while coupling this ability to a rotational speed (e.g., rotations per minute, or RPM) of a shaft. The axial counterbalance includes a rack and pinion system in which the rack can be teeth extending circumferentially around a shaft and the pinon can be teeth extending outwardly from a swing arm perpendicular to the shaft. The swing arm is rotatably attached to a bracket which is constrained by a static support. The swing arm can also include a weight on an end of the swing arm opposite the end of the swing arm including the pinion.

A noncontacting intershaft seal system includes force generating mechanisms to reduce contact related effects. A sealing system includes an outer shaft that has a hollow interior. An inner shaft extends through the hollow interior of the outer shaft. Spaced apart end plates encircle and rotate with the inner shaft. A gland opening is defined between the inner and outer shafts and between the end plates. A ring is disposed in the gland opening. The end plates and/or the ring include force generating elements that generate force to separate the ring from the end plates, reducing contact related heat generation and wear.

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 turbomachine includes a first housing member having a first journal bearing portion and a first radial control surface. The turbomachine also includes a second housing member with a second journal bearing portion and a second radial control surface. The second radial control surface has an interference fit with the first radial control surface that radially aligns the second journal bearing portion and the first journal bearing portion along a common axis.

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).