Abstract: A final drive for a vehicle is disclosed. The final drive includes a motor assembly, a planetary gear train and a drive sprocket. The motor assembly includes a hydraulic motor, an output shaft, a housing, a thrust bearing, a brake and first, second and third chambers. The housing includes a supply port, a first passageway, a second passageway and a drain port.

Abstract: A standard bearing unit (1) for different exhaust-gas turbocharger designs (8), having a shaft (2); having a shaft nut (18); having sealing devices (14, 15); having a compressor wheel (3) which is arranged on a first end (4) of the shaft (2); and having a turbine wheel (5) which is arranged on a second end (6) of the shaft (2), wherein the shaft (2) is mounted in a standardized bearing sleeve (7) which has predefined, unchangeable outer dimensions (19, 23) which are independent of the exhaust-gas turbocharger embodiment.

Abstract: A bearing support apparatus for a gas turbine engine, including: a first annular member; a second annular member disposed within the first annular member; first and second axially spaced-apart rolling-element bearings disposed between the first and second annular members so as to enable relative rotation of the first and second members; a first spring element mounting the first bearing to the first member; and a second spring element mounting the second bearing to the first member through the first spring element, such that the first and second bearings are physically supported in series relative to the first member.

Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A turbomachine with a shaft supporting a turbine wheel is supported for rotation in a housing. The shaft extends through a bore in the housing and a bearing assembly is disposed in the bore. The turbomachine has a first lubricating fluid slinger comprising a screw thread that is engageable with a threaded section of the shaft such that the first lubricating fluid slinger is screwable along the threaded section of the shaft so as to apply a compressive preload to the bearing assembly.

Abstract: A turbomachine including a shaft, a bearing for supporting the shaft and including an outer ring, and a support for the bearing, the support having a flange to which the outer ring is fastened by fasteners, is provided. Each fastener includes a fastener bolt and a nut screwed together. The turbomachine further includes, for each fastener, a position-retention device for retaining the bolt, and suitable for retaining the bolt in a position that is stationary relative to the bearing support or the outer ring, even in the absence of the nut. The head of the fastener bolt and the position-retention device may be of small dimensions, thereby enabling the fastening of the flange to the bearing support to be optimized, and in particular enabling the weight of the fastening to be optimized. A method of mounting the bearing of the turbomachine is also provided.

Abstract: A pumping apparatus comprises a rotatable shaft coupled to a motor. At least one control structure is mounted on the shaft, and at least one impeller is carried by the shaft. The impeller is adapted to rotate independently of the shaft so as to pump a fluid. The apparatus also comprises a magnetic coupling between the control structure and the impeller. Further, the impeller is adapted to translate axially along the shaft in response to a change in downstream pressure to alter the strength of the magnetic coupling.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the sealing device segments includes a stator interface element. The sealing device segment also includes a shoe plate having one or more labyrinth teeth facing the rotor and a load-bearing surface region, wherein the shoe plate allows a high pressure fluid to an upstream portion of the forwardmost labyrinth tooth and a low pressure fluid to a downstream portion of the aftmost labyrinth tooth. The sealing device segment further includes a secondary seal in contact with the stator interface element at a radially outer end and in contact with an elevated nose of the shoe plate on a radially inner end; and multiple bellow springs or flexures attached to the shoe plate and to the stator interface element.

Abstract: A bearing compartment for a gas turbine engine comprises a housing that surrounds an engine axis of rotation and has an inner surface and an outer surface spaced radially outward of the inner surface. The housing defines an open volume for a lubricant and includes a bearing seat to seat a bearing for rotation about the engine axis of rotation. The housing includes at least one cooling protuberance extending into the open volume.

Abstract: A bearing structure includes a non-metallic column-shaped main body having a through hole, an inner wall surrounding the through hole and an outer wall surrounding the inner wall. The outer wall has at least two protruding blocks extending outward and at least one groove, wherein the groove is arranged between the two neighboring protruding blocks. A fan includes a housing a stator winding, a bearing structure and a rotation piece. The housing has a base and an accommodating space. The stator winding is disposed in the accommodating space and surrounding the base. The bearing structure is disposed in the base. The rotation piece is disposed in the accommodating space, and has a rotation case, an axial shaft connected to the rotation case and a plurality of blades each connected to the rotation case.

Abstract: A shaft (120) configured to be mounted within a centrifugal gas compressor (100) includes a suction end (116), a discharge end (117), and a shaft surface. The shaft surface includes a hardened surface (123) located between the suction end (116) and the discharge end (117). The hardened surface (123) is a localized portion of the shaft surface having a different surface treatment than a remainder of the shaft surface. The hardened surface (123) is harder than the remainder of the shaft surface. The hardened surface (123) is configured to axially align with a central auxiliary bearing (137).

Abstract: A bearing for a turbocharger includes a bearing housing having a bearing portion of the turbocharger, a rotor shaft penetrating the interior of the bearing housing, a floating bush interposed between the bearing portion and the rotor shaft and configured to supply lubricating oil to an outer peripheral surface and an inner peripheral surface via an oil supply hole interconnecting the outer and inner peripheral surfaces, and a pressure receiving part for generating pressure by catching the flow of the lubricating oil, which is provided at a position on the inner peripheral surface of the floating bush not communicating with the oil supply hole.

Abstract: A thrust collar (161) includes a central disk (162), a forward wing (163), and an aft wing (164). The central disk (162) is a disk shaped hollow cylinder with a central axis (97). The forward wing (163) and the aft wing (164) are thin walled hollow cylinders extending axially from an inner portion of the central disk (162) about the central axis (97) in opposite directions. The forward wing (163) includes a forward mounting pilot (165) extending radially inward from the forward wing (163) distal to the central disk (162). The aft wing (164) includes an aft mounting pilot (167) extending radially inward from the aft wing (164) distal to the central disk (162).

Abstract: A clamping assembly comprising a bearing support member (16), the bearing support member being clampable to a shaft (2) by virtue of a clamping member (24) adaptable to tighten the bearing support member to the shaft, wherein at least a portion (16?) of the bearing support member (16) is disposable between a first abutment surface (28) provided on the clamping member and a second abutment surface (25) provided on the shaft; and wherein the portion (16?) of the bearing support member (16) comprises one or more protrusions (30) and one or more depressions (32) provided on an end face (16a, 16b) of the portion of the bearing support member, the protrusions and depressions being arranged to interface with one or more corresponding depressions (36) and protrusions (34) provided on one of the first abutment surface of the clamping member and the second abutment surface of the shaft, the respective protrusions and depressions being disposed so as to resist relative rotation between the shaft and the bearing support

Abstract: Bearing components, bearing assemblies and related methods are provided. In one embodiment, a bearing element includes a base layer and a polycrystalline diamond (PCD) layer comprising a plurality of PCD elements coupled with the base layer wherein each PCD element comprising a substrate and a diamond table. The plurality of PCD elements may be fit together to form a substantially continuous bearing surface. For example, the diamond tables may exhibit substantially square or rectangular geometries that are fit together to define the bearing surface. In other embodiments, the bearing elements may be spaced apart from one another. In other embodiments, the bearing element may include a single PCD element formed from a prefabricated PCD compact or cutting tool blank. Various bearing assemblies may incorporate such a bearing element including, for example, thrust bearings, journal bearings, and tilting pad bearing assemblies.

Abstract: A wind turbine is provided comprising a rotatable main shaft having a centre axis and being at least indirectly connected to a wind turbine rotor of the turbine and a main bearing supporting the rotatable main shaft at least indirectly against a first stationary part of the turbine, wherein fastening unit are provided for fastening the rotor to the first or a second stationary part of the turbine during replacement of the main bearing and tappet unit are provided which are able to act on the main bearing and permit a movement of the main bearing relatively to the first stationary part in the direction of the centre axis. A method for replacement of a main bearing is also provided.

Abstract: A bearing system has first and second bearings each having an inner race. The inner races are mounted to a shaft. The first bearing inner race has a plurality of first ports. The second bearing inner race has a plurality of second ports. The shaft is insertable into the inner races in a plurality of orientations and has a plurality of outer diameter (OD) channels positioned to cooperate with at least the first bearing inner race to communicate with at least some of the first ports and at least some of the second ports. Regardless of said installed orientation, at least one of the second ports are in communication with at least one said inlet port along a flowpath bypassing all the first ports.

Abstract: A compact, strengthened rotor assembly of a radiator fan, the radiator fan having a baseplate, a stator assembly, a rotor assembly and a reverse axle. The reverse axle is erected at the center of the baseplate or stator assembly and protruded upwards. The rotor assembly has a hub with a top wall and a circumferential wall. A magnetic ring is set annularly into the circumferential wall. Several blades are set annularly onto the exterior of the circumferential wall. A metal sleeve is located at the center of the top wall and protruded downwards. A mating portion is set at the top of the metal sleeve for mating with the top wall. A holding portion is formed within the metal sleeve for assembly and positioning of a bearing, and the bearing is used for pivoting of the reverse axle. The thickness of the top wall ranges between 0.2 mm and 0.5 mm.

Abstract: Enhanced abrasion resistance in well fluid wetted assemblies is described. The bearing set of the invention provides an enhanced abrasion resistance that is better capable of withstanding friction from solids in electric submersible pump (ESP) well production applications. The flutes, grooves, sectors and intersections of the invention provide improved fluid and solid flow through assembly components, which improves cooling while the assembly is in operation and reduces body wear, thereby increasing the lifespan of the ESP system.

Abstract: A semiconductor package is provided for carrying a sleeve member and a fan wheel axially coupled to the sleeve member so as to provide a heat dissipating function. The semiconductor package includes: a substrate; a coil module and at least an electronic component disposed on the substrate; and an encapsulant formed on the substrate for encapsulating the coil module and the electronic component so as to prevent the coil module and the electronic component from disturbing air flow generated by the fan wheel during operation, thereby avoiding generation of noises or vibrations.

Abstract: A pump device for applying a force opposing axial movement of a pump rotor shaft relative to a pump housing, the pump device having a first housing part, a second housing part axially moveable relative to the first housing part, and a biasing member coupled between the first housing part and the second housing part.

Abstract: Disclosed is a gas turbine engine configured to include a propulsor section having a fan drive geared architecture. The gas turbine engine includes a gas generator section that includes a compressor section having a first rotor rotationally mounted to a first spool. The engine further includes a bearing package adapted for rotationally supporting the first spool. The bearing package is configured for supporting the first rotor during at least one of (1) a period prior to installation of the fan drive geared architecture into the engine and (2) a period after removal of the fan drive geared architecture from the engine.

Abstract: The invention relates to a unit assembly system for the manufacture of exhaust-gas turbochargers (1) for internal combustion engines, of motor vehicles in particular, wherein the respective exhaust-gas turbocharger (1) has at least one hydrodynamic axial plain bearing (6) for supporting axial forces of a turbine wheel and/or of a compressor wheel (5) on a housing (7), said axial plain bearing having with regard to an axis of rotation (3) of a shaft (2) supporting the turbine wheel and/or the compressor wheel (5) a plurality of wedge-shaped bearing segments (9) distributed in the circumferential direction, which bearing segments work together with at least one level, annular thrust surface (10, 11) that extends transversely to the axis of rotation (3).

Abstract: An assembly for a turbocharger can include a locating washer having an axis and a perimeter that includes a chord segment defined by an apothem measured from the axis; a bearing assembly that includes an outer race having an axis and a perimeter that includes a chord segment defined by an apothem measured from the axis; and a housing that includes a bore for receipt of the bearing assembly and a recess for receipt of the locating washer to space apart the axes of the locating washer and the outer race by a distance greater than the sum of the apothems that provides for contact between the chord segments upon rotation of at least one of the locating washer in the recess and the outer race in the bore. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.

Abstract: An exhaust-gas turbocharger (1) having a turbine (2); having a compressor (3); and a bearing housing (4) which is arranged between the turbine (2) and the compressor (3) and a compressor-side flange (5) of which adjoins the compressor (3). A heat throttle (6, 6?) is arranged in the compressor-side flange (5) of the bearing housing (4).

Abstract: A vacuum pump comprises a housing, a drive shaft supported by a beating arrangement for rotation relative to the housing about an axis, and a pumping mechanism comprising a stator component mounted on the housing and a disk-shaped rotor component mounted on the drive shaft axially proximate the stator component. The bearing arrangement comprises a bearing supported in both radial and axial directions by a resilient support, comprising inner and outer annular portions connected by a plurality of flexible members, so that there is a fixed relation between the inner race of the bearing and the outer portion of the resilient support to determine the axial clearance between the rotor and stator components of the pumping mechanism.

Abstract: A ball bearing for a cryogenic application including an inner ring and an outer ring positioned around the inner ring. The inner ring and the outer ring define a raceway therebetween. The ball bearing includes a plurality of rolling balls disposed in the raceway and a slug separator positioned between and slidingly engaging each of adjacent pairs the rolling balls. The slug separator defines an exterior surface thereon, which has a recess extending at least partially into the slug separator. The recess is configured to flow cryogenic fluid therethrough.

Abstract: A thrust bearing structure is equipped with a thrust collar having a collar pad, and a thrust bearing having a bearing pad at a position corresponding to the collar pad on a surface facing the thrust collar. The bearing pad has a tapered section, and a land section continuously formed on the outer edge of the tapered section. Assuming that oil droplets are supplied between the bearing pad and the collar pad, and assuming that the rotation speed of a rotor shaft is constant, the tapered section would have a sloping surface formed in such a manner that a wall thickness gradually becomes thicker toward the downstream side along the trajectory of given oil droplets based on the centrifugal forces acting on the droplets due to the rotation of the rotor shaft.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A gas turbine engine includes a jumper tube that extends through a first passage and a second passge.

Abstract: A bearing housing (1) of an exhaust-gas turbocharger (EGT), having a mounting bore (2); a bearing device (3) which has two bearing bushes (4, 5) which are arranged in the mounting bore (2), between which bearing bushes is arranged a spacer (6); a rotational speed sensor (7) which engages into a sensor recess (8) of the spacer (6); and a locating pin (9) which is screwed into a pin bore (10) and which engages with its pin head (12) into a pin recess (11) of the spacer (6); wherein the pin recess (11) is formed as a slot.

Abstract: A fan structure at least includes a cap, an impeller, a bearing and a fixing shaft, wherein the cap comprises a bottom portion, a body and an accommodating space. The impeller comprises a hub and a coupling base having a ring wall and an accommodating slot. The bearing couples to the accommodating slot, and the fixing shaft penetrates through an axial hole of the bearing. The ring wall of the coupling base comprises at least one guidance hole exposing the fixing shaft. The guidance hole is in communication with the accommodating space and the accommodating slot. The lubricants can be collected inside the accommodating space of the cap through the guidance of the guidance hole to prevent the lubricants from leakage when the impeller is in rotation.

Abstract: A gas turbomachine includes a turbine portion including at least one turbine wheel, and a wheel shaft operatively connected to the at least one turbine wheel. The wheel shaft includes an outer surface. A stationary member includes an inner surface positioned outward of the outer surface of the wheel shaft to form a purge flow passage. A bearing housing is linked to the stationary member and spaced radially outward of the wheel shaft. The bearing housing includes at least one purge flow passage configured and disposed to guide a purge flow toward the wheel shaft. At least one of the outer surface of the wheel shaft and the inner surface of the stationary member includes a roughness inducing coating configured and disposed to increase drag and residence time of purge flow in the purge flow passage.

Abstract: Radial magnetic bearings (125) of a centrifugal gas compressor (100) may lose power and fail to support the shaft (120) resulting in damage to the shaft (120). Auxiliary bearings (135) may be used to support the shaft (120) during such a failure. A landing guard (140) may be installed as a sacrificial piece between the shaft (120) and the auxiliary bearings (135). Landing guard (140) includes slots (144) that may be used with pins (121) in the shaft (120) to prevent an angular displacement between the landing guard (140) and the shaft (120).

Abstract: A fan structure includes a cap, a fixing shaft, a bearing, an impeller and a protection lid, wherein the cap comprises a bottom portion, a body and an accommodating space. The fixing shaft is disposed within the accommodating space, a first end portion of the fixing shaft couples the bottom portion, and a second end portion of the fixing shaft protrudes to the body. The bearing couples to the fixing shaft, the second end portion of the fixing shaft protrudes to the bearing, and a hub of the impeller couples to the bearing. The second end portion of the fixing shaft protrudes to the hub. The protection lid couples to the second end portion of the fixing shaft to prevent lubricants for lubricating the bearing from splashing. The protection lid provides the impeller with protection to prevent the impeller from being compressed by external force to avoid destruction.

Abstract: According to one aspect of the invention, a turbine assembly includes a frame coupled to a ground surface, a bearing housing supporting a rotor bearing and a sleeve assembly attached to the frame and the bearing housing. The sleeve assembly includes an outer sleeve with a first flange on a first end that is positioned in an opening in the bearing housing and a second end that abuts the shim, an inner sleeve positioned within a portion of the outer sleeve and a bolt positioned within the inner sleeve and threadably coupled to the frame, wherein the bolt compressively loads the inner sleeve thereby loading a portion of the outer sleeve at the second end between the inner sleeve and the frame and wherein a first gap dimension is substantially maintained between the first flange and bearing housing as the bolt is preloaded and coupled to the frame.

Abstract: A turbocharger and a method of manufacturing a floating bush with which noise can be reduced, and the rotation speed can be increased. In a turbocharger in which a rotating shaft having a circular cross-section and connecting a turbine rotor and a compressor rotor is supported in a freely rotatable manner, at two axially separated positions via floating bushes, by an inner circumferential surface disposed so as to surround the rotating shaft in a bearing housing, an inner circumferential surface of each of the floating bushes has a non-circular shape in which the curvature of the cross-sectional shape varies in the circumferential direction.

Abstract: The invention provides a supercharger which is provided with a thrust bearing in an outer side of a radial bearing, and can smoothly discharge a fed lubricating oil from a bearing portion so as to reduce a resistance generated by the lubricating oil. The supercharger is provided with a thrust bearing (30) rotatably supporting a thrust force applied to a turbine shaft (12). The thrust bearing (30) is constituted by a disc-shaped thrust collar (32) rotating together with the turbine shaft, and a turbine side thrust bearing (34) and a compressor side thrust bearing (36) inhibiting a movement in an axial direction of the thrust collar.

Abstract: A cooling fan structure includes a hub, a rotary shaft, a fan seat, and a stator assembly. The fan seat is provided on around a front end corresponding to a rear end of the hub with a forward protruded annular rim portion and a sunken annular groove portion adjoining an inner lower side of the rim portion. The protruded annular rim portion reduces a gap between the hub and the fan seat to reduce the amount of air flowing into the hub via the gap and accordingly prevents external foreign matters from invading the hub via the same gap to adversely damage components inside the hub or cause a stuck hub; and the groove portion provides an additional space for receiving invaded and accumulated foreign matters to thereby reduce the possibility of a stuck hub. With these arrangements, the cooling fan can have prolonged service life.

Abstract: A bearing support for a turbocharger assembly is provided. The bearing support may include a cylindrical body with a tip end, a base end, and a conical outer surface extending from the tip end to the base end. The bearing support may also include an annular protrusion extending from the base end in a direction away from the tip end, and a stepped bore formed within the cylindrical body and passing from the tip end through the annular protrusion. The bearing support may also include a first conduit disposed within the cylindrical body and extending from an intersection of the annular protrusion and the base end of the cylindrical body toward the tip end.

Abstract: A fan structure includes a sleeve, an impeller, a bearing and a fixing shaft, wherein the sleeve is covered with a hub of the impeller. The sleeve comprises a ring wall, an accommodating slot and a top portion, and a penetration hole is formed at the top portion. The bearing is disposed at the accommodating slot and comprises an axial hole and a top surface, wherein the top surface of the bearing and the top portion are spaced apart from each other by an interval. The fixing shaft penetrates through the axial hole of the bearing, a free end of the fixing shaft is protruded to the top portion via the penetration hole, and an oil storage space can be defined between the top portion of the sleeve, the top surface of the bearing and the fixing shaft.

Abstract: A single-bearing structure, in particular for use in a wind power plant, which has a low friction operating characteristic. The single-bearing structure for mounting a rotor in the wind power plant has two first rows of rolling bodies, which are arranged in the single-bearing structure such that their pressure lines intersect with one another and with a radial plane of a rotation axis of the single-bearing structure. The rolling bodies of the two first rows of rolling bodies are designed as cylindrical rollers.

Abstract: A bearing device (1), in particular for a shaft (2) of a turbocharger (3), including two journal bearings (5) and a bush-like separating element (9) for spatially separating the two bearings (5). The separating element (9) includes a separating bush which is formed in the manner of a cage having a multiplicity of apertures (16) arranged circumferentially and separated from one another by struts (17).

Abstract: A fan shaft support assembly for a gas turbine engine includes first and second bearing assembles supported by a bearing support structure. The bearing support structure includes a first support including a first support end supporting the first bearing assembly and a second support including a second support end supporting the second bearing assembly. The first support end and the second support end are spaced apart to provide a preload on the first and second bearing assemblies.

Abstract: A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.

Abstract: A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through the seal body between the radially outer surface and the radially inner surface.

Abstract: A pump for conveying a pump fluid, wherein the pump fluid provided at an inlet pressure at a low pressure side of the pump can be conveyed in the operating state to a high pressure side of the pump rotor by means of a pump rotor rotatably supported about an axis of rotation in a pump stator and wherein a rotor shaft is arranged with the pump rotor at it drive bearing formed as a shaft bearing, characterized in that a lubricating film which is formed from a lubricating fluid formed from the pump fluid can be formed on a drive side of the rotor shaft between the rotor shaft and a drive bearing in a lubricating ring gap, with a lubricant line being provided such that the lubricating fluid can be supplied to the lubricating ring gap between the rotor shaft and the drive bearing.

Abstract: An assembly and method for an axial compressor includes an axial shaft extending between an inlet casing and a discharge casing along the longitudinal length of a compressor housing. The axial shaft assembly includes a first stub shaft, a second stub shaft, and a hollow shaft drum having a longitudinal axis. The first stub shaft and the second stub shaft are coupled to opposing ends of the shaft drum along its longitudinal axis. A plurality of keys is disposed in a radial arrangement near the outer circumference of the first and second stub shafts and the shaft drum. A plurality of pins engage the plurality of keys, whereby the pins prevent the shaft drum from rotating axially relative to the first stub shaft and the second stub shaft and prevent the shaft drum from axially and radially separating from the stub shafts.

Abstract: A fan bearing retaining structure includes a base and a ring member. The base has a bearing cup projected from one side thereof, and the bearing cup internally defines an axial bore for receiving a bearing therein. The ring member is fitted around an outer side of the bearing cup and defines an opening, such that an inner side of the opening tightly contacts with the outer side of the bearing cup to apply a radially inward compression toward the axial bore. With these arrangements, a portion of the axial bore corresponding to the ring member fitted around the bearing cup has a reduced inner diameter to thereby effectively retain the bearing in the bearing cup, enabling a fan to be manufactured at reduced cost.