Abstract: A fan assembly includes a bushing, a stator, a first bearing, and a rotor. The stator surrounds the bushing, and includes at least one hook. The hook extends into the bushing. The first bearing is disposed in the bushing and presses against the hook. The rotor is pivotally connected to the first bearing.

Abstract: A bearing support is disclosed herein. The bearing support includes a pilot ring encircling an axis. The pilot ring is operable to be substantially-fixed in operation. The bearing support also includes a damper ring operable to receive an outer race of a bearing assembly. The bearing support also includes a fuse pin extending through aligned apertures in the pilot ring and the damper ring to prevent relative radial movement between the pilot ring and the damper ring up to a predetermined amount of loading. The fuse pin is operable to fracture in response to loading beyond the predetermined amount. The bearing support also includes a retainer extending through one of the pilot ring and the damper ring and fixed to the other of the pilot ring and the damper ring. The fuse pin is engaged with at least one of the first and second apertures through a heat shrink fit.

Abstract: A plain bearing for a turbomachine rotor is proposed. The plain bearing has a bearing body for mounting the turbomachine rotor and has a solid lubricant powder for lubricating a bearing contact area between the bearing body and the turbomachine rotor. The bearing body is produced from an acid-gas-resistant, solid-solution-strengthened powder of a nickel-based material or from a martensitic, austenitic or ferritic-austenitic non-rusting powder of a steel material, and the solid lubricant powder is produced from an acid-gas-resistant material. The bearing body has a hardness of at most 40 Rockwell hardness HRC.

Abstract: A compressor is provided and may include a shell having an inner surface and an outer surface and a bearing housing disposed within the shell and having an engagement surface opposing the inner surface. The engagement surface may include a first channel formed substantially perpendicular to a longitudinal axis of the shell and a second channel formed substantially parallel to the longitudinal axis of the shell and in communication with the first channel. The first channel and the second channel may receive a deformed portion of the shell therein to fix a position of the bearing housing relative to the shell.

Abstract: A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame.

Abstract: A bearing support housing for a gas turbine engine includes: an annular mounting flange; a first bearing cage including: an annular first bearing support ring; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the mounting flange; and a second bearing cage including: an annular second bearing support ring; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the mounting flange, the second spring arms defining spaces therebetween. The first spring arms are received between the second spring arms, and the bearing cages are sized so as to permit independent flexing motion of the first and second spring arms.

Abstract: A turbocharger arrangement in an internal combustion engine is provided. The turbocharger arrangement includes a turbocharger housing surrounding a sealed inner space and a shaft extending through the turbocharger housing. The turbocharger arrangement further includes a turbine wheel arranged on the shaft and driving a compressor unit, a bearing arrangement mounting the shaft in the turbocharger housing, an oil supply device lubricating the bearing arrangement, and a pressure changing unit in fluidic communication with the sealed inner space configured to adjust the pressure in the sealed inner space based on engine operating conditions.

Abstract: A multi-stage pump rotor (10) for a turbomolecular pump has at least two separate blade disk rings (17), each having a motor ring (12) and at least one blade disk (14). A cylindrical reinforcement pipe (18), which surrounds the rotor rings (12) of the blade disk rings (17) on the outside without clearance, is provided between the blade disks (14) of adjacent blade disk rings (17). The reinforcement pipe (18) absorbs a large part of the tangential forces occurring during operation such that the pump rotor (10) has improved stability at high rotor speeds.

Abstract: In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure-supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on fixed structure of the engine located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

Abstract: An assembly for sealing an inlet into a to-be-sealed space, comprising the following features: at least one charging electrode that is connectable to one pole of a high voltage source is disposed in a first area of the inlet, an opposing electrode is disposed in a second area of the inlet that lies opposite of the first area, and the electrodes are disposed in a manner aligned with each other such that an influencing zone, which is formed between the electrodes, acts on influencible particles that penetrate from the outside in the direction towards the to-be-sealed space, such that these particles are accelerated in the direction away from the to-be-sealed space.

Abstract: A thrust shaft for a fan has a shaft body with an enlarged disk adjacent one axial end to provide a rotating surface in a pair of thrust bearings. A first cylindrical portion extends from the disk in a first direction, and a second cylindrical portion extending from the disk in a second opposed direction. The second cylindrical portion has a hollow bore, and there are a plurality of holes extending through the second cylindrical portion to communicate an outer periphery with the bore. A ratio of the diameter of the bore to a diameter of the plurality of air holes is between 6.60 and 7.00. A ratio of an overall length of the second cylindrical portion, and a distance from a face of the enlarged disk to a center of the holes is between 14.4 and 15.2. A thrust bearing assembly, a fan, a cabin air supply system, and a method are also disclosed.

Abstract: An exemplary multi-piece bearing for a turbocharger includes a cylindrical piece that has a coefficient of thermal expansion, opposing ends and an outer surface and an inner surface that extend between the opposing ends where the outer surface includes one or more lubricant openings; an end piece that has a different coefficient of thermal expansion and a face where the face includes one or more lubricant openings; and lubricant passages formed by the cylindrical piece and the end piece for passage of lubricant between the one or more lubricant openings of the outer surface of the cylindrical piece and the one or more lubricant openings of the face of the end piece. As described herein, such an exemplary multi-piece bearing can, upon selection of coefficients of thermal expansion, help maintain axial clearances between various components during operation of a turbocharger. Other exemplary bearings, arrangements and methods are also disclosed.

Abstract: A two-row tapered roller bearing includes an outer ring (1) having an outer diameter of at least one meter, a first inner ring (2) and a second inner ring (3) that is disposed axially adjacent the first inner ring (2). A first set of conically-formed roller bodies (4) roll between the outer ring (1) and the first inner ring (2) and a second set of conically-formed roller bodies (5) are disposed axially adjacent the first roller bodies (4) and roll between the outer ring (1) and the second inner ring (3). A first sealing ring (11) is disposed axially adjacent the outer ring (1), is connected with the outer ring (1) and slips on a slip surface (16) of the first inner ring (2) in a contacting manner.

Abstract: A bearing device includes a turbine-side bearing 21 and a compressor-side bearing 22 each of which is a floating-bush type sliding bearing. A gap (turbine-side inner peripheral clearance TI) between the turbine-side bearing 21 and a rotating shaft 13 is set to be larger than a gap (compressor-side inner peripheral clearance CI) between the compressor-side bearing 22 and the rotating shaft 13. In the bearing structure, unstable vibration including self-excited vibration can be suppressed.

Abstract: A thrust bearing shaft has an enlarged disk at one axial end to provide a rotating surface in a thrust bearing. A first cylindrical portion extends from the disk. A second cylindrical portion has a smaller diameter than the first cylindrical portion and extends from the first cylindrical portion to an end of the thrust shaft remote from the disk. The thrust shaft has a hollow bore with a ledge extending across the bore at a location within the first cylindrical portion. The ledge is formed with a central hole of a first hole diameter, and twelve air holes spaced circumferentially about the central hole. The twelve holes are formed of a second hole diameter, with a ratio of the first hole diameter to the second hole diameter being between 2.55 and 2.71. In addition, a bearing assembly, a compressor, and a method of assembling a compressor are disclosed.

Abstract: Apparatus for sealing and purging a bearing region includes a bearing housing having at least one hole that allows a flow of air to flow through the at least one hole, and at least one bearing seal that allows the flow of air to flow through the at least one bearing seal, thereby creating a pressure difference across the bearing seal. The apparatus also includes an air directional device having at least a portion of the flow of air to flow adjacent to the air directional device, and a pair of components having a gap between the pair of components that allows the at least a portion of the flow of air to flow through the gap, thereby purging the gap.

Abstract: A compressor rotor compresses and delivers compressed air across a turbine rotor. The turbine rotor is connected to the compressor rotor such that rotation of the turbine rotor drives the compressor rotor. A shaft is connected to rotate with the turbine rotor and the compressor rotor. A thrust bearing is provided by a member extending perpendicular and radially outwardly of the shaft. The member rotates with the shaft and faces a first housing wall. A hollow chamber is formed on an opposed side of the first housing wall. A cooling air path supplies air across a thrust bearing surface, and between the member and the first housing wall. The first housing wall has a communication hole for communicating cooling air from the cooling air path into the hollow cavity to drive air within the hollow chamber. Also, a housing incorporating the communication hole is disclosed.

Abstract: Turbocharger comprising a shaft, a housing, a turbine wheel and a compressor wheel mounted onto the shaft, at least one rolling bearing located between the shaft and the housing and comprising an inner ring, an outer ring and at least one row of rolling elements between raceways provided on the rings. Said turbocharger comprises at least one intermediate sleeve radially located between the shaft and the inner ring of the rolling bearing.

Abstract: A thrust bearing shaft has a radially enlarged thrust disk to be mounted between two static housing surfaces in an air cycle machine. A first portion of the thrust bearing shaft extends from a first face of the thrust disk. A second portion extends from a second opposed face of the thrust disk. The second portion has sealing ribs and six holes. The sealing ribs are spaced closer to the thrust disk than are the holes. A ratio of a distance from an end of the second portion to a center of the holes compared to a distance from the end of the second portion to the second face of the thrust disk is between 0.20 and 0.22. In addition, an air cycle machine incorporating the thrust bearing shaft, and a method of assembling the thrust bearing shaft into an air cycle machine are disclosed.

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend outward from the engine case to the fan case. A front frame assembly includes a plurality of vanes extending radially across the gaspath. A transmission couples a shaft to a fan shaft to drive the fan. A bearing assembly couples the shaft to the front frame assembly. A bearing support extends aftward and radially inward from the front frame assembly to the bearing assembly.

Abstract: A turbocharger for an internal combustion engine includes a bearing housing with a bearing bore and a semi-floating bearing disposed within the bore. The turbocharger also includes a shaft having a first end and a second end, wherein the shaft is supported by the bearing for rotation about an axis within the bore. The turbocharger also includes a turbine wheel fixed to the shaft proximate to the first end and configured to be rotated about the axis by post-combustion gasses emitted by the engine. Additionally, the turbocharger includes a compressor wheel fixed to the shaft proximate to the second end and configured to pressurize an airflow being received from the ambient for delivery to the engine. Furthermore, the turbocharger includes a plate secured within the bearing housing and configured to prevent rotation of the bearing about the axis. An internal combustion engine employing such a turbocharger is also disclosed.

Abstract: To solve both axial and rotational constraint problems in turbochargers with rolling element bearings (REBs), a REB sleeve or outer race is mounted to the bearing housing in a way that is not axially and radially rigid, thus allowing for oil damping films both radially and axially. At the same time, the REB sleeve or outer race is held so that the REB sleeve or outer race does not rotate relative to the bearing housing. This dual purpose is achieved using an anti-rotation ring and a damping ring. The anti-rotation ring includes at least one anti-rotation feature for engaging the bearing housing and at least one anti-rotation feature for engaging the REB cartridge, preventing rotation of the REB cartridge sleeve or outer race. The damping ring axially locates the REB cartridge and dampens axial movement and cushions axial thrust.

Abstract: A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.

Abstract: A sealing system is equipped with: a dry gas seal 15 having a rotating ring 16 positioned between a casing 1a and a rotor shaft 11 and around the circumference of the rotor shaft 11, and stationary rings 19, 20 provided on the casing 1a with elastic members 17, 18 interposed therebetween and so as to be capable of contacting the orthogonal edge surfaces of the rotating ring 16 that are substantially orthogonal to the rotor shaft 11; a sealing gas channel 6 having one end connected to a discharge channel 5, the other end connected so as to connect to a space 37 between the casing 1a and the outer perimeter surface 16a of the rotating ring 16 in the dry gas seal 15, and having a sealing gas regulating valve 8 provided therein; and a drain gas channel 26 having one end connected so as to connect to the space 37 via a through hole 35 formed in the casing 1a below the rotating ring 16, and the other end connected to an intake channel 3.

Abstract: An example gas turbine engine includes a housing and first and second spools coaxial with one another and arranged within the housing. 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. First and second bearings support the aft end of the first spool relative to the housing. An example method of assembling the gas turbine engine includes arranging a first spool within a second spool. First and second bearings are mounted between an aft end of the first spool and a fixed housing.

Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.

Abstract: A gas turbine engine includes a shaft supported by first and second bearings for rotation relative to an inlet case. The first and second bearings are positioned within a common bearing compartment.

Abstract: A compressor rotor compresses and delivers compressed air across a turbine rotor. The turbine rotor is connected to the compressor rotor such that rotation of the turbine rotor drives the compressor rotor. A shaft is connected to rotate with the turbine rotor and the compressor rotor. A thrust bearing is provided by a member extending perpendicular and radially outwardly of the shaft. The member rotates with the shaft and faces a first housing wall. A hollow chamber is formed on an opposed side of the first housing wall. A cooling air path supplies air across a thrust bearing surface, and between the member and the first housing wall. The first housing wall has a communication hole for communicating cooling air from the cooling air path into the hollow cavity to drive air within the hollow chamber. Also, a housing incorporating the communication hole is disclosed.

Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.

Abstract: A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet.

Abstract: A turbomachine includes a housing and a rotatable shaft, where at least a portion of the rotatable shaft is located in the housing. The turbomachine also includes a magnetic thrust bearing that axially positions the rotatable shaft and a radial bearing that centers the rotatable shaft. The turbomachine includes a flexure including a first portion secured to the housing and a second portion axially moveable relative to the first portion. The second portion of the flexure is connected to the radial bearing, and the second portion moves axially to eliminate thrust loads on the radial bearing and allow the magnetic thrust bearing to carry axial loads.

Abstract: A system having an axial brush seal assembly is provided, having a first component, a second component, at least two plates that generally oppose one another, a plurality of seal bristles, and a base plate. The first component has a first sealing surface. The second component has a second sealing surface. The plurality of seal bristles are received between the at least two plates. The plurality of seal bristles include a first end portion and a second end portion. The first end portion is configured to selectively seal against the first sealing surface and the second end portion is configured to selectively seal against the second sealing surface. At least one of the at least two plates is connected to the base plate, and the base plate supports the brush seal assembly. The axial brush seal assembly provides sealing for two leakage paths simultaneously.

Abstract: An air cycle machine includes a shaft formed from end sections attached to a center section. The center section includes a first diameter that is supported on bearings within the air cycle machine and a second diameter that forms a part of an interface with a corresponding end section. The second diameter is less than the first diameter and extends an axial distance from an end of the center section and provides for the weld beam to be directed normal to the interface location such that weld quality and manufacturing efficiencies are improved.

Abstract: A charging device may include a shaft rotatably mounted on at least one slide bearing in a shaft bearing region. At least one flow opening for introducing and discharging a fluid may be defined on the shaft bearing region, wherein the shaft in the shaft bearing region may have two outer portions each running in a circumferential direction and axially binding an inner portion. At least one of the outer portions on its surface may include at least one microstructure.

Abstract: A fan structure at least includes a bearing module and a rotor, the bearing module includes a hollow cylinder body, a bearing, a limiting member and a blocking member. The hollow cylinder body comprises a ring wall and an accommodating hole, wherein the bearing, the limiting member and the blocking member are disposed at the accommodating hole in sequence. The ring wall comprises an inner ring wall and a limiting slot recessed from the inner ring wall. The blocking member comprises a body portion and a blocking portion extendedly formed at the body portion, the body portion embedded into the limiting slot, and the blocking portion is in contact against the limiting member. A rotating shaft of the rotor penetrated through the limiting member and the bearing, and a plurality limiting plates of the limiting member inserted into a ring slot of the rotating shaft.

Abstract: A fan includes a stationary portion, a rotating portion, and a plurality of blades. The stationary portion includes a stator, an integral one-piece molded metal bearing housing, a bearing portion in the bearing housing, and a molded resin base portion supporting the bearing housing. The rotating portion includes a rotor holder, a rotor magnet, and a shaft. The bearing housing includes a cylindrical portion, and a protruding portion extending radially outwards from a lower portion of the cylindrical portion. The cylindrical portion includes a groove portion extending in an axial direction and arranged in a circumferential direction. The groove portion is joined to a region on the lower side of the protruding portion along a connecting position between the cylindrical and protruding portions. A resin on an upper side of the protruding portion, a resin on a lower side, and a resin in the groove portion are continuous.

Abstract: A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring.

Abstract: A bearing arrangement 2 comprising an outer race 10, a shaft 4 arranged to rotate with respect to the outer race 10 thereby defining an axis of rotation 8 of the shaft 4. The shaft 4 and the outer race 10 are arranged to define a region of overlap between the shaft 4 and the outer race 10 along the axis of rotation. An inner race 12 is disposed between the outer race 10 and the shaft 4 in the region of overlap and coupled for rotation with the shaft 4, the inner race 12 and the shaft 4 defining an annular reservoir 40 between them for accommodating radial expansion of the shaft 4 or radial displacement of the shaft 4 with respect to the axis of rotation 8.

Abstract: In a sliding bearing, load carrying capacity and bearing rigidity is increased without increasing a size of the bearing and the pressure of the fluid. The sliding bearing comprises a cylindrical-shaped sleeve supporting a rotatable shaft via fluid, and hydrostatic pressure pockets provided in the inner periphery of the sleeve. The hydrostatic pressure pockets constitute a plurality of rows of circumferentially disposed hydrostatic pressure pockets via orifices. At least one of the hydrostatic pressure pocket rows is arranged adjacently to each of both end portions of the inner periphery of the sleeve. And a circular cylindrical inner peripheral surface region without the hydrostatic pressure pockets is provided at a center portion of the sleeve. A width of the circular cylindrical inner peripheral surface region provided in the axial direction of the shaft is made wider than a sum of widths of the hydrostatic pressure pocket rows.

Abstract: A bearing structure includes a main body internally defining a shaft space; the shaft space axially extends a full length of the main body and communicates with at least one extension space; and the extension space is radially outward extended from the shaft space and also axially extends a full length of the main body. The shaft space has a non-circular cross section. In a cooling fan using the bearing structure, a rotor shaft is inserted in the shaft space. With the shaft space having a non-circular cross section, it is possible to largely increase the support pressure of a lubricant filled between the rotor shaft and the shaft space and accordingly, reduce the frictional contact between the rotor shaft and the shaft space as well as the noise and vibration produced during the operation of the cooling fan.

Abstract: A bearing device of a gas turbine power generation equipment provides damping vibration of a shaft and lubricates and cools the bearing main body. The bearing devices have sleeves provided on the outer circumference sides of the bearing main bodies and bearing housings holding the respective sleeves via O-rings while each forming an annular clearance passage between each of the outer circumferences of the sleeves and a corresponding one of the bearing housings. The bearing housing has a feed-water hole communicating with the clearance passage and adapted to feed water thereto. The sleeve has a lead water hole communicating with the clearance passage and is adapted to lead water to the bearing main body, and a discharge hole which communicates with the clearance passage and is adapted to discharge water therefrom.

Abstract: An oil-retaining bearing fan structure includes a fan base seat, an oil-retaining bearing and at least one magnetic member. The oil-retaining bearing is disposed in a bearing hole of the fan base seat. The magnetic member is disposed between the oil-retaining bearing and a wall of the bearing hole. The magnetic member serves to apply a magnetic attraction force to a shaft of the fan structure to make the shaft quickly restore to its optimal operation position so as to reduce wear and lower the noises and vibration of the fan structure in operation. Therefore, the lifetime of the fan structure can be prolonged.

Abstract: A bearing housing (1) of an exhaust-gas turbocharger, having a compressor-side housing flange (2), a central housing section (3) which is integrally connected to the housing flange (2) and in which a first partial section (4) of an oil chamber (5) is arranged; and a turbine-side housing section (6) which has a turbine-side housing flange (7) and in which a second partial section (8) of the oil chamber (5) is formed. The central housing section (3) and the turbine-side housing section (6) are formed in one piece. A bearing housing (9) which forms a separate component is inserted into the central housing section (3) and into the turbine-side housing section (6), with these delimiting the oil chamber (5).

Abstract: An oil-retaining bearing fan device includes a fan base seat, at least one oil-retaining bearing and at least one magnetic member. The oil-retaining bearing is disposed in a bearing hole of the fan base seat. The oil-retaining bearing has at least one receiving hole for receiving the magnetic member therein. The magnetic member serves to apply a magnetic attraction force to a shaft of the fan device to make the shaft quickly restore to its optimal operation position so as to reduce wear and lower the noises and vibration of the fan device in operation. Therefore, the lifetime of the fan device can be prolonged.

Abstract: A wind turbine comprising an electrical generator that includes a rotor assembly. A wind rotor that includes a wind rotor hub is directly coupled to the rotor assembly via a simplified connection. The wind rotor and generator rotor assembly are rotatably mounted on a central spindle via a bearing assembly. The wind rotor hub includes an opening having a diameter larger than the outside diameter of the central spindle adjacent the bearing assembly so as to allow access to the bearing assembly from a cavity inside the wind rotor hub. The spindle is attached to a turret supported by a tower. Each of the spindle, turret and tower has an interior cavity that permits personnel to traverse therethrough to the cavity of the wind rotor hub. The wind turbine further includes a frictional braking system for slowing, stopping or keeping stopped the rotation of the wind rotor and rotor assembly.

Abstract: An exemplary turbomachine securing apparatus includes a coupling member that couples a first component to a second component within a turbomachine. The first component and the second component are both non-rotating components during operation of the turbomachine. The coupling member limiting relative circumferential movement between the first component and the second component, and permitting relative radial movement.

Abstract: A vertically mountable shaft and bearing assembly includes a thermally insulated housing that protects the shaft, bearing(s), and lubricant from overheating due to a surrounding process fluid that is above 65° C. This allows a bearing to be located near the shaft's distal end, thereby reducing shaft and bearing size requirements. The housing also serves as a reservoir for bearing lubricant that can be cooled by a lubricant cooling system normally used for processes at much lower temperatures. The lubricant can be circulated by an impeller that is actuated by the shaft or driven separately. The thermal insulation, can include vacuum, air, and/or a thermally insulating material. Additional rolling element and/or journal bearings can be included. Lubricant within the shaft housing can be pressurized, for example by pressurized gas or by filling the lubricant above the surrounding process fluid level. The shaft can operate a process fluid pump impeller.

Abstract: A bearing device with an arrangement of at least two bearings is provided. A filling made of an amorphous/solid active medium as a mechanism of compensating for axial loads is arranged between a bearing race of at least one of the bearings and a surrounding component of the bearing arrangement.