Abstract: In a main bearing replacement method for a wind turbine power generation facility including a nacelle, a rotor head rotatably supported by the nacelle, a drive shaft to which rotation of the rotor head is transmitted, a main bearing disposed between the rotor head and the nacelle, and a coupling connecting the rotor head and the drive shaft on a radially inner side of the main bearing, the wind turbine power generation facility includes a main bearing sleeve fitted and fixed to an inner ring of the main bearing and mounted with the rotor head, and the main bearing is replaced at least while the main bearing sleeve is fitted and fixed to the inner ring of the main bearing.

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

Abstract: A bearing housing is configured as an end-side cover for a nacelle of a fluid-flow power plant and includes a cylindrical section having an interior and a bearing unit in the interior. The bearing unit includes at least one rolling-element bearing having an inner ring and an outer ring rotatably disposed with respect to each other about a bearing rotational axis and a plurality of rolling elements between the rings. A pressure line of the bearing intersects the bearing rotational axis at a first angle. An angled section of the housing extends from the cylindrical section of the housing at a second angle that is related to, and preferably substantially equal to, the first angle.

Abstract: Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

Abstract: A magnetic levitation centrifugal pump, comprises: one hollow body provided with at least one inlet connector and with at least one outlet connector for blood; one rotor element, housed inside the hollow body and comprising at least one magnetic portion, where the rotor element can be commanded in rotation about an axis of rotation, without contact, by a stator element associable with the hollow body, the rotor element comprising at least one revolving body, which defines an upper surface supporting a plurality of blades which are adapted to convey blood towards the outlet connector; where the upper surface has a substantially concave shape and where the revolving body comprises at least one through hole which is positioned along the axis of rotation.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: A shaft sealing arrangement includes a first seal and a second seal, wherein the first seal is designed in the form of a lip seal and the second seal is designed in the form of a mechanical seal. When the shaft is at a standstill, the lip seal performs the sealing action and, when the shaft is rotating, the mechanical seal performs the sealing action.

Abstract: An apparatus includes a shared cooling device for cooling one or more systems or components, and a plurality of primary cooling pathways. Each of the primary cooling pathways includes a fan, and each fan is in fluid communication with the shared cooling device.

Abstract: A rotary machine includes: a stationary body having a stationary-side peripheral surface; a rotating body having a rotating-side peripheral surface facing the stationary side-peripheral surface. One surface which is one of the stationary-side peripheral surface and the rotating-side peripheral surface has an upstream-side peripheral surface, a downstream-side peripheral surface, and a rearward step surface. The other surface has an upstream-side seal fin forming a minute gap between the upstream-side seal fin and the upstream-side peripheral surface; a downstream-side seal fin forming a minute gap between the downstream-side seal fin and the downstream-side peripheral surface. The rearward step surface has a guide surface extending downstream Da2 while directed toward the other surface and connected to the upstream-side peripheral surface.

Abstract: A motor includes a connector detachably connected with an external cable and a resin sealing member which covers the connector. The connector includes a frame part into which a cable side connector is to be inserted and a step part on an outer peripheral face of the frame part. A shape of the step part when viewed in the inserting direction is a ring shape. The resin sealing member covers the connector from the front side and exposes an end face of the step part of the frame part and a portion of the frame part on the rear side to the step part end face to the outside, and an outer peripheral face of the resin sealing member is provided with an outer peripheral face portion which surrounds the frame part and is continuously connected with the step part end face without a step.

Abstract: A motor includes a rotor, a stator having coils, a connector for supplying electrical power to the coils, and a resin sealing member. The resin sealing member comprises an opposite-to-output side sealing part and a connector sealing part covering the connector. The connector comprises a frame part into which the cable side connector is to be inserted, and the opposite-to-output side sealing part comprises a first protruded part and a second protruded part. A tip end face of the first protruded part and a tip end face of the second protruded part are located on one imaginary face intersecting the rotation center line, a tip end on the opposite-to-output side of the frame part is located on the output side with respect to the imaginary face, and the second protruded part is provided at a position closer to the frame part between the first protruded part and the frame part.

Abstract: A method of monitoring a blade pitch bearing of a rotor blade of a wind turbine is provided, the method including: pitching the rotor blade; measuring an amount of a vibration of the blade pitch bearing during the pitching; estimating a condition of the blade pitch bearing based on the measured amount of vibration. Also disclosed is an arrangement for monitoring a blade pitch bearing, a rotor blade bearing and a wind turbine.

Abstract: A squeeze film damper bearing assembly includes a bearing and a spring cage that receives and surrounds the bearing. The spring cage has an inner diameter and an outer diameter. The outer diameter has an outer surface that defines a first circumferential channel recessed within the outer surface that is axially spaced apart from a second circumferential channel recessed within the outer surface and at least one axial anti-rotation chamber that interconnects the first and second channels. The assembly includes a first piston ring received in the first channel and a second piston ring received in the second channel. The assembly includes at least one anti-rotation member received within the at least one axial anti-rotation chamber that cooperates with the first piston ring and the second piston ring to inhibit a rotation of the first piston ring and the second piston ring relative to the outer surface.

Abstract: A method for performing uptower maintenance of a wind turbine in order to replace the main bearing on the turbine shaft is disclosed. Embodiments of this method to perform maintenance may include installing a rotor lock to resist rotation of the main shaft during maintenance, providing a lifting device in order to elevate the main shaft, removing the main bearing from its main bearing housing, and installing a replacement split main bearing. A crane may also be installed uptower to assist in the maintenance.

Abstract: A wind turbine rotor blade with a rotor blade tip, a rotor blade root, and a rotor blade connection in the region of the rotor blade root with a rotationally symmetrical flange coupling is provided which has a first and a second end. The first end of the flange coupling has multiple bores for receiving fastening means for fastening to a hub of a wind turbine. The second end is fastened in or on material of the rotor blade root. The second end extends in the direction of an axis of rotation of the flange coupling.

Abstract: A double-row self-aligning roller bearing has rollers interposed, in two rows aligned in a bearing width direction, between an inner ring and an outer ring. The outer ring has a spherical raceway surface. Each of the rollers has an outer circumferential surface having a cross-sectional shape that matches the raceway surface of the outer ring. The rollers have lengths equal to each other and maximum diameters equal to each other, and have different distances from centers of the roller lengths to positions at which the maximum diameters are obtained.

Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.

Abstract: A seal carrier for a turbomachine, in particular a gas turbine, including a carrier base and at least one seal member, the at least one seal member being connected to the carrier base, and the at least one seal member being formed by a plurality of cavities arranged adjacent one another, in particular in a regular fashion, in the circumferential direction and the axial direction, the cavities extending from the carrier base in the radial direction, is provided. At least one stiffening element on the carrier base, the stiffening element extending along the circumferential direction and at least partially covering the at least one seal member at one of its axial end regions is provided.

Abstract: A fan motor according to the present invention comprises a rotor 10 which rotates together with a shaft 30; a stator 20 which is installed to be oriented towards the rotor 10; a top-covering bracket 60 which is coupled to an upper insulator 21 and a core 22 constituting the stator 20; a motor bracket 80 which is mounted on a fixed-installation bracket 70 and coupled to the core 22, upper insulator 21 and lower insulator 23 of the stator 20 and a printed circuit board 50; and a sealing element 100 which is filled in a space portion S formed between a lower surface of the printed circuit board 50 coupled to the bottom of the lower insulator 23 and an inner lower surface of the motor bracket 80.

Abstract: A compressor bladed disk comprises a disk including an axial groove and a disk protrusion, a compressor blade including an attachment engaged with the axial groove of the disk, and a first locking plate disposed on the disk and the attachment, wherein the attachment includes an upstream surface and an upstream fillet connected to the upstream surface, wherein the upstream surface of the attachment and a protrusion front surface of the disk protrusion are aligned with each other, wherein a back surface of the first locking plate is disposed on the upstream surface of the attachment and the protrusion front surface of the disk protrusion, and wherein the first locking plate is disposed on the upstream fillet. The compressor bladed disk further comprises a second locking plate disposed on a downstream surface of the attachment.

Abstract: An object is to is to reduce a leakage flow by reducing a clearance between an end surface of a nozzle vane, forming a variable nozzle mechanism of a variable geometry turbocharger, and a wall surface facing the end surface, and prevent the nozzle vane from being stuck due to contact of the end surface.

Abstract: A fan-motor assembly includes a fan which includes a hub and blades and generates a wind by using a rotational force, and an outer rotor fan motor which includes a stator and a rotor rotating at the periphery of the stator and is coupled to the fan by a shaft to provide the rotational force to the fan. In the fan-motor assembly, the rotor includes a magnet generating magnetic flux for rotating the rotor, and a rotor frame which surrounds the magnet to be coupled to the outer circumferential surface of the magnet and is spaced apart from the hub by the shaft so as not to be directly contacted with the hub.

Abstract: A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom. Each blade has a suction side and a pressure side and includes a shank, a platform and a main portion, the main portion being radially outward of the shank and separated therefrom by the platform. At least one cavity is defined, each radially inward of the platforms and between a suction side of the shank of one blade and a pressure side of the shank of an adjacent blade. The rotor includes at least one damper, the damper including a main body in contact with at least one blade and a deflector nose. The deflector nose extends from the main body into the cavity.

Abstract: A turbine rotor includes: a rotor shaft part; a plurality of blades secured to an outer periphery of the rotor shaft part; and a seal plate configured to be fitted into a groove and configured to seal off a flow of gas in an axial direction, the groove being defined in a platform of one of the blades so as to be recessed toward an outer side in a radial direction and to extend in a peripheral direction. A blind tool hole into which a removing tool can be inserted is defined in an outside surface of the seal plate opposite an inside surface that faces a blade root of the one of the blades.

Abstract: A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades.

Abstract: A sealing ring configured to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring including a plurality of anti-rotation pegs which prevent it from rotating in relation to the rotor disc, each peg protruding axially from a ring body and including two opposite circumferential-end surfaces, respectively configured to be located facing two directly consecutive blades carried on the rotor disc. An axially opening slot passes radially through at least one of the anti-rotation pegs.

Abstract: A system for isolating electrical current in an aircraft structure includes a first structure a bearing having an outer race and an inner race and a liner disposed therebetween, the outer race having a second structure coupled thereto. A dielectric seal is secured to the outer race and engages the inner race. A conditionally non-conductive gas occupies a sealed chamber that defines a gap between the inner race and the outer race. The gap has a predetermined magnitude sufficient to prevent electrical arcing or current leakage between the inner race and the outer race at a first voltage less than that voltage resulting from a lightning strike; and/or to conduct an electrical current between the inner race and the outer race at a second voltage greater than or equal to the voltage resulting from the lightning strike.

Abstract: A method of installing a diffuser in an air cycle machine includes placing a first housing on a shaft, placing a seal plate on the shaft, and placing a diffuser on the shaft. Next, the diffuser and the seal plate are aligned with an alignment tool. The alignment tool has a first annular surface to align with a radially outer surface of the seal plate and a second annular surface to align with an annular flange on the diffuser. Finally, the diffuser is fastened to the seal plate and the alignment tool is removed from the diffuser and the seal plate.

Abstract: A drive unit for a door includes an electronically commutated multipole motor having: a stator part configured to be arrangable at a stationary structural component part; and a rotor part configured to be gearlessly connectable to a rotationally drivable element. The stator part and the rotor part include sheet metal elements stacked in a package-like manner. The sheet metal elements of the stator part and the sheet metal elements of the rotor part extend parallel to one another.

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 flow-based power generating plant with a turbine, which can be acted on by a fluid flow and having a plurality of blades that extend from a blade base to a blade tip and are fastened by the blade base to a rotating rotor. The action of the fluid flow can cause the blades to twist elastically around an axis which extends through the blade base, in such a way that the pitch of the blades can be increased.

Abstract: A platform seal strip, in particular for use in a gas turbine blade assembly, is provided. The platform seal strip includes an upper side, a lower side, a first portion and a second portion. The width of the first portion is smaller than the width of the second portion. The first portion and the second portion are at least partially bent downwards such that the upper side includes a convex surface portion and the lower side includes a concave surface portion.

Abstract: A frame assembly of a ring-type fan with a pressure-releasing function includes a fan wheel, a pressuring-releasing portion, and a frame body. The fan wheel is received in an accommodating space of the frame body. The fan wheel has a hub and a plurality of blades. The pressure-releasing portion is formed on free ends of the blades and has a stopping wall and a flange extending from one end of the stopping wall. A pressure-releasing channel is formed between the stopping wall and an inner wall of the frame body. With the pressure-releasing portion being formed on the free ends of the blades, the present invention is capable of delaying the deceleration, improving the fan performance, and reducing its noise.

Abstract: A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

Abstract: A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing. Frictional forces between contacting parts limit torsional windup and increase torsional resistance with increasing load. The damper bearing assembly includes a damper housing configured substantially within a U-shaped spring finger housing and a spanner nut with a radial hook portion coupled to the spring finger housing. The damper housing is coupled to the spring finger housing such that it is substantially confined within the U-shaped void. The spanner nut is coupled to the spring finger housing such that the radial hook portion is configured to limit the deflection of the spring finger housing and damper housing during a fan blade out event.

Abstract: A bearing arrangement, comprising a rolling bearing, which includes an inner ring, an outer ring, rolling elements interposed therebetween, and a cage for holding and separating the rolling elements, wherein the inner ring presents an inner circumferential surface. A shaft is also present, wherein the rolling bearing is mounted on the shaft via the inner circumferential surface of the inner ring. The shaft during operation is meant to oscillate in its axial direction, or is positioned in an angle ? being (90?y) degrees, wherein y is between 0 and 89, or the rolling elements during operation are exposed of an axial force F, and the cage presents means for axially guiding the rolling elements against at least one of the inner ring, the outer ring or a separate element located outside the rolling bearing. The bearing can be integrated into a wind turbine main shaft arrangement.

Abstract: An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.

Abstract: The invention is directed to a rotor blade assembly for a wind turbine designed to mitigate pitch bearing loads. The rotor blade assembly includes a rotor blade, a pitch bearing, and at least one shim plate. The rotor blade includes a body extending between a blade root and a blade tip. The pitch bearing includes an outer race, an inner race, and a plurality of roller elements between the outer race and the inner race. As such, the inner race is rotatable relative to the outer race. The at least one shim plate may be configured between the inner race and the blade root or between the outer race and a hub of the wind turbine so as to mitigate loads experienced by the pitch bearing.

Abstract: A mounting system for mounting a blade to a rotor body includes a pitch control mechanism including an anchor and a pitch change rod extending radially outwardly from the anchor to join to a base of the blade. The anchor and the rod are rotatable about the longitudinal axis of the rod to vary the blade pitch. The pitch control mechanism further includes a torque-transmitting formation between the blade and the anchor such that pitch-varying torque can be transmitted to the blade through the torque-transmitting formation while allowing relative radial movement between the blade and the anchor. The system includes a primary bearing formation, which transmits blade centrifugal loads to the rotor body while accommodating variation of the blade pitch, and secondary bearing formation, which transmits pitch change mechanism centrifugal loads to the rotor body while accommodating rotation of the anchor and the rod during variation of the blade pitch.

Abstract: A turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed. During operation, the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade. The plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.

Abstract: A bearing assembly for a gas turbine engine includes a bearing, an outer assembly disposed about an axis and having an angled perimeter, and an inner assembly supporting the bearing and having a surface angled to slide against and attach to the angled perimeter as the bearing is aligned with the axis.

Abstract: A rotor structure of a fan includes a bushing, a hub, a shaft and a plurality of blades. The hub has a top portion and a sidewall, and the top portion of the hub covers the bushing. The hub and the bushing are made by the same material. One end of the shaft is connected to the bushing, and the shaft is disposed inside the top portion. The blades are disposed on the outer side of the sidewall of the hub. A manufacturing method of the rotor structure is also disclosed.

Abstract: A turbomachine bucket may include an airfoil, a shank coupled to the airfoil, and an angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent. Various methods for modifying an angel wing to accommodate different sized discouragers are also disclosed.

Abstract: A fluid pump 1, particularly a water pump 1, wherein an impeller 11 comprising a plain bearing bush 12 is rotatably supported on a bearing pin 13. The impeller 11 and the plain bearing bush 12 are thereby made of an identical base material in one or more pieces. A further material is mixed into the base material of the plain bearing bush 12, improving the sliding properties of the plain bearing bush 12 on the bearing pin 13.

Abstract: A prestressing device extending about an axis between a first plane that is substantially perpendicular to the axis and a second plane that is substantially parallel to the first plane and axially offset relative to the latter. The device includes a first annular body extending in the first plane, and a first series of at least three tabs, each of which is connected to the first body and extending in an essentially radial direction, each of the tabs of the first series including a planar surface extending in the second plane. This arrangement ensures surface contact between the parts of the elements to be subjected to prestressing. The device can be used for example for a rotor, and for example for a rotor of an unducted propeller for a turbine engine.

Abstract: A roller bearing comprises an outer ring, an inner ring, a plurality of rollers arranged between the outer ring and the inner ring, and a plurality of retainer segments having a plurality of column parts extending in a direction along a shaft so as to form a pocket for holding the roller, and connection parts and extending in a circumferential direction to connect the plurality of column parts, and continuously lined with each other in the circumferential direction between the outer ring and the inner ring. The column part is positioned at an circumferential end of the retainer segment. Here, a circumferential outer side end face of the column part positioned at the end is flat, and a circumferential inner side end face of the column part positioned at said end is provided with a recess recessed in the circumferential direction to reduce the thickness of the column part.

Abstract: A shaft cap to connect between a shaft and a tie rod on a rotative assembly includes a circular portion with a central opening for connecting to the tie rod; a conical portion extending out from the circular portion at a slope; and a pilot around the outer edge of the conical portion. The pilot includes an outer lip to connect to an end of the shaft, an inner portion to connect to the inner circumference of the shaft and an undercut portion between the outer lip and the inner portion.

Abstract: The present invention relates to a bearing assembly for supporting a shaft having a toroidal roller bearing arrangement. The bearing assembly includes a first set of rolling elements formed of toroidal roller elements arranged in a first row and interposed between an inner ring providing a first inner raceway and an first outer ring providing a first outer raceway, and a thrust bearing arrangement having a second set of rolling elements arranged in a second row. The rolling elements are in contact with and arranged to cooperate with a second inner raceway and a second outer raceway for supporting axial loads and for restricting axial movement of the shaft in relation to the first outer ring. The present invention also relates to a method for manufacturing a bearing assembly for supporting a shaft.

Abstract: A low density abradable coating for use as a seal material is formed by depositing a metal bond coat followed by depositing a low density, porous, abradable metal seal layer on the bond coat. The seal layer is formed by co-depositing metallic sponge particles and metal precursor particles. The metal precursor particles decompose during heat treatment leaving fine pores distributed throughout the microstructure.