A turbocharger includes a housing and a rotating group supported for rotation within the housing. The rotating group includes a compressor wheel disposed within a compressor section of the turbocharger, and the rotating group includes a turbine wheel disposed within a turbine section of the turbocharger. The turbine wheel includes a bleed pressure surface. The turbocharger further includes a bleed passage that extends at least partly through the housing to fluidly connect the compressor section to the turbine section. The bleed passage is configured to direct a bleed flow of fluid from the compressor section to the bleed pressure surface to supply a thrust counterbalance load to the bleed pressure surface.

The balancing system has a balancing body to be mounted on a rotor of a turbomachine and a sealing ring to be mounted on a stator of the turbomachine; the sealing ring is arranged around the balancing body so that the balancing body can rotate about a rotation axis, thus there is a clearance between the body and the ring; furthermore, there is an arrangement for changing an axial position of the sealing ring during operation of the turbomachine so that the clearance can be adjusted. The possibility of adjusting clearance during operation of the turbomachine, such balancing system provides a good balancing action with a small leakage and a small risk of mechanical interference at any time during operation of the turbomachine.

A steam turbine facility includes a rotor shaft, a high-pressure turbine blade row and an intermediate-pressure turbine blade row disposed on the rotor shaft, a first low-pressure turbine blade row and a second low-pressure turbine blade row disposed on the rotor shaft on both sides of the intermediate-pressure turbine blade row, respectively, and a third low-pressure turbine blade row and a fourth low-pressure turbine blade row disposed on the rotor shaft on both sides of the high-pressure turbine blade row, respectively. The steam turbine facility is configured such that steam having passed through the intermediate-pressure turbine blade row is divided to flow into the first low-pressure turbine blade row, the second low-pressure turbine blade row, the third low-pressure turbine blade row, and the fourth low-pressure turbine blade row.

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.

Each of foils (22) includes: a top foil portion (22a) including a bearing surface (S); and a back foil portion (22b), which is formed on an upstream side of the top foil portion (22a), and is arranged so as to overlap behind the top foil portion (22a) of the adjacent foil (22) (on a side opposite to the bearing surface (S)). An angle (E) covering a radially inner end of an overlapping portion (P) between the adjacent foils (22) is smaller than an angle (D) covering a radially outer end of the overlapping portion (P).

Methods and systems are provided for electric turbochargers. In one example, a turbocharger comprises a shaft coupling a compressor wheel to a turbine wheel, an electric machine including a stator encircling the shaft between the compressor wheel and the turbine wheel, and an oil supply passage formed in a housing of the electric machine and fluidly coupled to a first oil nozzle oriented toward the shaft.

A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

A gas turbine engine according to the present disclosure includes, among other things, a propulsor section including a propulsor having a plurality of blades, the plurality of blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine that drives a first compressor and a second turbine that drives the propulsor section. A second inboard boundary of a core flowpath has a radius R1 defined at a first stage of a second compressor and has a radius R2 defined at a splitter rim that guides flow into the core flowpath.

A supercharging device having a housing, at least one impeller, and at least one axial bearing having first and second bearing surfaces. The impeller here forms one of the bearing surfaces of the axial bearing.

A method for shimming a thrust bearing for an accessory power take off shaft to obtain optimal meshing of bevel gears within the internal gearbox (IGB) without disassembly of the IGB is enabled by relocating the thrust bearing from the engine sump. The accessory gearbox (AGB) is driven from a power off-take from the turbine spool via the IGB. The radial position of the power take-off bevel gear is established by a radial position of the thrust bearing attached to the exterior of the casing via a housing. Candidate shims are selected from a set each having different thicknesses, the shims are formed of two halves and placed between the housing and the engine casing to adjust the radial position of the thrust bearing and consequently the power take-off bevel gear, without requiring the disassembly of the IGB.