Abstract: Stator structure (22) extending around an axis of the turbomachine and comprising: —a support (50) having an inner surface centred on the axis and—a flange (60) defining an air chamber (A2) and having an outer surface centred on the axis, the support (50) extending around the flange (60) such that the inner and outer surfaces are opposite to each other, the structure (22) defining an oil circuit and an air circuit which are formed by upstream channels (64, 65) and downstream channels (54, 55), —each upstream channel (64, 65) defining an outer opening in the outer surface, —each downstream channel (54, 55) defining an inner opening in the inner surface, each circuit being oriented between the outer and inner openings in a direction comprising a component radial to the axis.

Abstract: A rotor support configured to rotatably mount a rotor shaft in a vacuum pump is disclosed. The rotor support comprises: a rolling bearing for rotatably supporting the shaft; an insert and at least one resilient damping member, the insert and the at least one resilient damping member surrounding the rolling bearing. The insert comprises inner and outer annular portions connected by a plurality of flexible members, the plurality of flexible members being configured to flex in a radial plane and resist movement in an axial plane, thereby absorbing radial movement of the shaft. The at least one resilient damping member is formed of an elastomeric material configured to flex in both a radial and axial direction.

Abstract: A method and system for controlling a vibration of a rotor in a turboshaft engine are provided. The method includes: establishing, based on a kinetic model for a rotor-casing system, a mapping matrix indicating a correspondence among an unbalance, an oil film clearance, and a vibration response; performing determination on a real-time vibration response, and skipping adjustment if the real-time vibration response is smaller than a response threshold; otherwise, approximately matching a real-time oil film clearance and the real-time vibration response with the mapping matrix to obtain a real-time unbalance; obtaining, based on the real-time unbalance and the mapping matrix, a preferred vibration response, and further obtaining a preferred oil film clearance; based on the preferred oil film clearance and the real-time oil film clearance, obtaining a clearance adjustment amount; generating a control signal based on the clearance adjustment amount, and performing adjustment based on the control signal.

Abstract: A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.

Abstract: A turbo device provides a flow-path arrangement in a generator device. Part of a working fluid are used to lubricate at least one of a first bearing part, a second bearing part and a bearing assembly, or the working fluid of an auxiliary flow channel is led to a generator housing for cooling the generator device. In addition, a circulatory system is also provided to include bearing loops and auxiliary loops for leading the working fluid to lubricate at least one of the first bearing part, the second bearing part and the bearing assemble part, and to cool the generator device.

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A wind turbine includes a rotor shaft. The rotor shaft is mounted via a bearing assembly having a first bearing ring and a second bearing ring mounted to rotate in relation to the first bearing ring. A hydrostatically supported first friction bearing segment is disposed on the first bearing ring and interacts with a first friction face that is disposed on the second bearing ring. The first friction bearing segment is received in a receptacle pocket of the first bearing ring such that a first compression chamber is formed between the first bearing ring and the first friction bearing segment. The first friction bearing segment is configured such that a second compression chamber is formed between the first friction bearing segment and the second bearing ring, wherein the first compression chamber and the second compression chamber are connected by a duct that runs through the first friction bearing segment.

Abstract: A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

Abstract: A turbocharger assembly including a housing, a shaft, and turbine and compressor wheels mounted on opposite ends of the shaft. The shaft is rotatably supported within the housing by a bearing cartridge that includes turbine-side and compressor side ball-bearing assemblies that are longitudinally spaced by a spacer. There are two times as many rows of ball-bearings included in the turbine-side ball-bearing assembly compared to the compressor-side ball-bearing assembly. The spacer slides over and rotates with the shaft and has at least one flat. An optical sensor extends through the housing and an optical sensor opening in the bearing cartridge to prevent the bearing cartridge from rotating within the housing. The optical sensor detects rotational speed of the spacer by counting the number of times the flat(s) passes by the optical sensor during a pre-determined time interval.

Abstract: A gas turbine engine having a damping system that includes features for optimizing the damping response to vibrational loads on a rotary component for a wide range of operational conditions is provided. In one aspect, the damping system includes a damper control valve. The damper control valve receives working fluid from a working fluid supply and has a valve plunger movable between a first position and a second position. When the valve plunger is in the first position, the damper control valve permits working fluid to flow to a first damper associated with a first bearing coupled with the rotary component and to a second damper associated with a second bearing coupled with the rotary component. When the valve plunger is in the second position, the damper control valve permits working fluid to flow to the first damper but not the second damper.

Abstract: A dual-film damper has a housing defining an annular damper fluidly connected to a source of pressurized oil. First and second damper rings are coaxially nested within the damper cavity. A first set of spacers allows for the formation of a first oil film annulus between the first and second damper rings. A second set of spacers allows for the formation of a second oil film annulus between the second damper ring and the housing. The first and second oil film annuli have a thickness-to-length ratio (T/L) selected to provide a desired damping capacity.

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A planet gear housing assembly is disclosed in an epicyclical gear system of a gas turbine engine. The planet gear housing assembly comprises an aft planet carrier assembly, a forward planet carrier assembly, and a plurality of planet gears. The planet gear housing assembly includes one or more of the following features: a stiffening member positioned between the forward and aft planet carrier assemblies, a static curvic joint coupling the forward and aft planet carrier assemblies, a plurality of roller element bearings to carry the plurality of planet gears, and one or more bearing springs disposed between a bearing and a carrier housing to accommodate relative movement.

Abstract: A vacuum pump comprises stator elements in a pump housing. The stator elements cooperate with rotor elements. The rotor elements are held by a rotor shaft, wherein the rotor shaft is mounted in the pump housing via bearing elements. The bearing element is surrounded by a supporting element, wherein the supporting element comprises an inner portion, an outer portion and a plurality of spring arms connecting the inner portion (28) to the outer portion. Each spring arm comprises at least one hollow space.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft configured to rotate during operation of the gas turbine engine, and a squeeze film damper radially outside the shaft. The squeeze film damper includes a cavity including a film of lubricant axially between first and second cavity seals, and further includes a reservoir fluidly coupled to the cavity. A method is also disclosed.

Abstract: A vibration reducing device for a gas turbine engine includes a rotating shaft containing a first mass member, a plurality of bearings rotatably supporting the rotating shaft, and a stationary body supporting the bearings. An annular second mass member having an internal diameter thereof larger than an external diameter of the rotating shaft is rotatably supported in a contact state at a position on the rotating shaft, at which position centrifugal whirling vibration is generated due to imbalance of the first mass member. Therefore, due to the second mass member being eccentric in an opposite phase with respect to the rotating shaft eccentrically undergoing centrifugal whirling, it is possible to counterbalance a centrifugal force acting on the first mass member with an inertial force acting on the second mass member, thus enabling a damping effect to be exhibited and reducing effectively the centrifugal whirling vibration of the rotating shaft.

Abstract: A ball joint (1), for a vehicle chassis, having a joint housing (3) and a joint body (4) having a spherical portion (5). The joint body (4) is held by the joint housing (3) at the spherical portion (5) of the joint body such that the joint body is mounted for articulation movement relative to the joint housing. A sensor assembly comprises a first sensor element (6) associated with the joint housing (4) and a second sensor element (7) associated with the joint body (4). The second sensor element interacts with the first sensor element (6) in order to sense the position of the joint body (4) relative to the joint housing (3). The ball joint is characterized in that the second sensor element (7) is arranged in the region of the spherical portion (5) of the joint body (4).

Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.

Abstract: A fluid damping structure includes first and second annular elements, first and second inner seals, a first outer seal, a damping chamber, a supply plenum, a fill port, and a plurality of fluid passages. The first and second inner seals are disposed radially between and are engaged with the first annular element and the second annular element. The first outer seal forms a sealing interface between the first and second annular elements. The first outer seal is disposed radially outward from the first and second inner seals. The damping chamber is defined by the first and second annular elements and the first and second inner seals. The supply plenum is disposed contiguous with an axial side of the damping chamber and extends from the second inner seal to the first outer seal. The fill port is in fluid communication with the supply plenum and a source of damping fluid.

Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

Abstract: A squeeze film damper bearing has an inner support ring capable of supporting a bearing portion; an outer support ring disposed on an outer periphery of the inner support ring; and a dissipation portion formed on at least one of the outer support ring and the inner support ring to dissipate vibration energy. A damper gap formed between an outer circumferential face of the inner support ring and an inner circumferential face of the outer support ring is filled with a viscous fluid.

Abstract: A positive displacement compressor includes a positive displacement compressor rotor; a shaft operative to support the positive displacement compressor rotor; a bearing operative to support the shaft; a first structure having a first squeeze film compression surface; and a second structure having a second squeeze film compression surface spaced apart radially from the first squeeze film compression surface. The first and second structures are constructed to jointly form a squeeze film damper using the first and second squeeze film compression surfaces. The squeeze film damper is operative to provide squeeze film damping of vibrations. An annular oil discharge groove is disposed adjacent to a first end of the squeeze film damper. A first o-ring gland houses a circumferential-sealing o-ring disposed proximate to the first end of the squeeze film damper. A second o-ring gland houses a second circumferential-sealing o-ring disposed proximate to a second end of the squeeze film damper.

Abstract: An inter-shaft bearing is supported by a support including a solid rigid body which is non-deformable during normal operation, but which can break in the event of an excessive stress, such as a blade failure. A damper included in the support limits the movements between the two shafts and prevents excessive instability.

Abstract: A mount system provides vibration isolation and support through a hybrid hard-soft configuration. The mount system includes a frame and a body connected with the frame. A first coupling element is provided on the body and defines a first opening. A second coupling element is provided on the frame and defines a second opening. A pin extends through the first and second openings to couple the body to the frame. At least one of the first and/or second openings operates as a damping hole with a series of slits disposed about the damping hole, so that the damping hole with the slits is configured to deflect to reduce the transmission of vibrations between the body and the frame.

Abstract: A fluid damping structure is provided that includes an inner and outer annular elements, first and second ring seals, first and second outer annular seals. The inner annular element has an outer radial surface and a plurality of annular grooves disposed in the outer radial surface. The outer annular element has an inner radial surface. A damping chamber is defined by the inner and outer annular elements, and the first and second inner ring seal. A first lateral chamber is disposed on a first axial side of the damping chamber. A second lateral chamber is disposed on a second axial side of the damping chamber. A plurality of fluid passages are disposed in at least one of the inner annular element or the inner ring seals. The fluid damping structure is configurable in an open configuration and a closed configuration.

Abstract: The invention relates to a device and a method for mounting a bearing 200 on a roll neck and for removing the bearing from the roll neck of a roll. Known devices of this type have a first and a second piston/cylinder unit. They also have a stop ring 130, fixed in the axial direction A at the end of the roll neck 320 remote from the body, which acts as a stop for the inner piston 110 of the first piston/cylinder unit. In addition, the known devices have a nut 150 which can be screwed onto an external thread of the inner piston to secure the bearing 200 in the axial direction, in particular during a rolling operation. As an alternative to the known prior art, the present invention provides that an annular cylinder 120 serves both as a cylinder for the first piston/cylinder unit and as a cylinder for the second piston/cylinder unit.

Abstract: A multi-film oil damper suited for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall and radially extending side walls; an inner damper ring; an outer damper ring disposed between the inner damper ring and the radially outward wall of the annular damper cavity; wherein the annular damper cavity has an oil inlet in communication with a source of pressurized oil; and wherein a radial thickness of the inner damper ring exceeds a radial thickness of the outer damper ring.

Abstract: A method and an apparatus includes a static engine structure, at least one shaft that rotates relative to the static engine structure, and a bearing assembly that supports the shaft. The bearing assembly includes at least one first bearing hard mounted directly between the shaft and the static engine structure and at least one second bearing mounted between the shaft and the static engine structure. The at least one second bearing includes a damper. Also included is at least one third bearing that is mounted between the shaft and the static engine structure, wherein the at least one third bearing includes a resilient member.

Abstract: A stabilizing arrangement for a rotating shaft including a shaft being arranged substantially vertically in a machine so as to rotate during machine operation, first pressure delivery system for delivering a fluid pressure, in particular of a fluid circulating inside the machine, at a first location of the machine. First location is close to the shaft and part of first pressure delivery system is arranged at first location so as to exert a lateral pulling or pushing action on the shaft.

Abstract: A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal.

Abstract: A seal assembly for a turbine engine having a shaft with a rotary axis and a housing surrounding the shaft; the seal assembly being disposed between the shaft and the housing, the seal assembly comprising: an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins; an inner labyrinth seal, disposed radially inwardly concentric to and axially overlapping the outer labyrinth seal and the outer seal runner, the inner labyrinth seal having multiple inner fins in opposing sealing engagement with a concentric inner seal runner, one of: the inner labyrinth seal fins; and the inner seal runner, engaging the housing, and the shaft engaging an opposing one of: the inner seal runner; and the inner labyrinth seal fins; and an intermediate plenum, defined between the outer fins,

Abstract: In a bearing device, a squeeze film damper includes an annular mass member disposed in a floating state between an outer periphery of an outer race and an inner periphery of a bearing retaining member, a first squeeze film damper part formed between the outer periphery of the outer race and an inner periphery of the annular mass member, and a second squeeze film damper part formed between an outer periphery of the annular mass member and the inner periphery of the bearing retaining member. Therefore, due to the floatingly supported annular mass member being eccentric with the opposite phase to a rotating shaft, which is eccentric and undergoes centrifugal whirling, an inertial force acting on the annular mass member counteracts the centrifugal force acting on the rotating shaft, thus enabling a damping effect to be exhibited.

Abstract: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage.

Abstract: A turbocharger, including a turbine with a turbine rotor, a compressor with a compressor rotor coupled to the turbine rotor via a shaft. At least one bearing, via which the shaft is mounted in the bearing housing, wherein the respective bearing comprises a bearing bush mounted in the bearing housing in a rotationally fixed manner, wherein between the bearing bush and the bearing housing a radially outer lubricating gap and between the bearing bush and the shaft a radially inner lubricating gap is formed. The radially inner lubricating gap is suppliable with lubricating oil via at least one line introduced into the bearing bush, wherein the or each line introduced into the bearing bush, which serves for the oil supply of the radially inner lubricating gap, leads into a lubricating oil pocket of the bearing bush each, which based on the axial length of the bearing bush is placed off-center.

Abstract: A damping device for connecting a bearing housing to a bearing outer race is provided. The damping device may permit an allowable range of radial movement of the bearing. The damping device has an elastomeric body connected to one of the bearing outer race and the bearing housing and a cover portion connected to the other one of the bearing outer race and the bearing housing. It also has two or more deformable fluid chambers fluidly connected to one another via at least one orifice and in which fluid is encapsulated. The damping device may dissipate at least partially vibrations travelling between the bearing housing and the bearing outer race by compressing its elastomeric body and by discharging fluid from one fluid chamber to another. There may be a plurality of such damping devices disposed circumferentially about the bearing outer race.

Abstract: Rotating coalescer crankcase ventilation (CV) systems are described. The described CV systems utilize a contact seal to seal a gap between a static side of a housing and a rotating coalescer inlet. The rotating coalescer may be driven mechanically, electrically, hydraulically, or the like. The contact seal can be formed via a soft solid or a liquid film created by oil. Accordingly, the contact seal is a hydrodynamic soft seal. The contact seal prevents the blowby gases from bypassing the filter element of the rotating coalescer. At the same time, the contact seal may be broken during positive blowby gas recirculation circumstances because the contact seal is a hydrodynamic soft seal.

Abstract: A squeeze film damper bearing device includes an inner race that is fitted around an outer periphery of a rotating shaft, an outer race that is supported on an inner periphery of a bearing retaining member, a plurality of rolling bodies that are disposed between the inner race and the outer race, and an annular space that is defined between the bearing retaining member and the outer race by a pair of seal rings and forms a squeeze film. The annular space includes a first space facing an outer peripheral face of the outer race and a second space facing an end face in an axial direction of the outer race.

Abstract: A counter-rotating shaft assembly of a gas turbine engine includes an outer shaft rotatable in a first direction about a virtual rotational axis, an inner shaft counter-rotatable about the virtual rotational axis in a second direction that is opposite to the first direction, a differential bearing rotatably connecting the two shafts, a centering spring connecting the inner shaft to the differential bearing, and a squeeze film damper between the differential bearing and the inner shaft.

Abstract: A bearing spring support/damping apparatus has: a first end portion; a second end portion; and a flexible portion between the first end portion and the second end portion, and further comprising: a single outer diameter groove in the second end portion.

Abstract: The presently disclosed embodiments utilize a rear bearing sleeve interposed between an inner surface of an exhaust housing of a gas turbine auxiliary power unit and the rear roller bearing supporting a turbine within the exhaust housing. In some embodiments, the rear bearing sleeve includes a lubricant supply channel formed in an outer surface thereof for receipt of a supply of lubricant, and at least one lubricant supply opening between the outer surface and an inner surface thereof, the inner surface of the bearing sleeve forming an outer race of the rear roller bearing. The at least one lubricant supply opening supplies the lubricant to a gap between the rear roller bearing and the rear bearing sleeve for formation of a squeeze film viscous damper therebetween.

Abstract: A component 2 for a bearing, the component 2 comprising a bearing surface 4, wherein the bearing surface 4 is formed so as to be tapered at rest, thereby offsetting deformation of the bearing during an operational condition which generates an induced angle in the bearing surface 4 or an opposing surface of the bearing. A method of manufacturing a bearing is also provided. The method comprises: determining an induced angle of a component 2 of the bearing caused by deformation of the bearing during an operational condition: and providing a surface 4 of the component 2 or an opposing component with a taper at rest so as to offset the induced angle generated during the operational condition.

Abstract: A centralizing assembly for an engine having a plurality or rotatable vanes is provided including an engine casing and at least one unison ring disposed concentrically there about. A spacing gap is formed between the unison ring and the engine casing and is variable between a maximum spacing gap and a minimum spacing gap in response to thermal expansion of the engine casing. A centralizer element includes a plunger element movably mounted to unison ring and spanning the spacing gap. At least one conical spring washer is mounted to the plunger element and exerts a centralizing force through the plunger element onto the engine casing. The at least one conical spring washer maintains the centralizing force between the maximum spacing gap and the minimum spacing gap.

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 squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. A pressurized oil reservoir is formed in the gap between the static member and the whirling member. A first low pressure oil reservoir is formed in a first cavity in the whirling member, wherein the first low pressure oil reservoir is positioned on a first end of the pressurized oil reservoir. A second low pressure oil reservoir is formed in a second cavity in the whirling member, wherein the second low pressure oil reservoir is positioned on a second end of the pressurized oil reservoir. A first primary seal is positioned between the first end of the pressurized oil reservoir and the first low pressure oil reservoir, and a second primary seal is positioned between the second end of the pressurized oil reservoir and the second low pressure oil reservoir.

Abstract: A film damper for a gas turbine engine includes an annular inner member and an annular outer member located radially outboard of the annular inner member, the annular outer member and the annular inner member defining a damper annulus therebetween. A fluid supply passage delivers a flow of fluid into the damper annulus from the annular outer member, and a backflow prevention device is located at the fluid supply passage to prevent backflow of the flow of fluid from the damper annulus into the fluid supply passage.

Abstract: A bearing load sharing system comprising: first and second rotors extending in an axial direction; a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor; a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor; and an inter-rotor bearing having an inner race and an outer race, the inner race connected to one of the first and second rotor and the outer race connected to the other of the first and second rotor; wherein the outer race of the first bearing and/or the outer race of the second bearing is movable to vary the axial spacing between the outer races.

Abstract: The present disclosure relates to a tubless washing machine, and more particularly, to a tubless washing machine including only a drum without a tub containing wash water.

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: Self-adjusting bushing bearing with a shaft seal for engaging a shaft. The self-adjusting bushing bearing has a plurality of bearing segments configured to receive a shaft therein. A springy element engages an outer surface of the plurality of bearing segments and biases the plurality of bearing segments towards the shaft. A shaft seal coupled to the springy element is configured to contact the shaft when the shaft is received in the plurality of bearing segments so as to create an operable seal between the shaft and the housing.

Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.