Abstract: A motor assembly comprises a stator, a rotor configured to be rotated about a shaft by electromagnetically interacting with the stator, an impeller configured to be rotated with the rotor about the shaft by being coupled to the rotor and configured to suction air in response to a rotation, a housing configured to cover between the impeller and the stator by being coupled to the stator, a cover comprising an inlet through which air sucked by the impeller is introduced, and configured to cover the impeller, a guide member configured to guide the air discharged from the impeller and configured to be coupled to the housing, and a plurality of first vanes protruding from one of the cover and the guide member to an axial direction and coupled to the other of the cover and the guide member.

Abstract: A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

Abstract: Blood pump devices having improved rotary seals for sealing a bearing assembly supporting a rotor provided herein. Such rotary seals are particularly suited for use in blood pump devices that include rotors having cantilevered supported through a sealed mechanical bearing disposed outside a blood flow path of the device to avoid thrombus formation caused by blood contact with the bearing. The rotary seal can include a first and second face seal that are preloaded with a deflectable compliance member incorporated into the pump housing or a pair of magnets. Such rotary seals can instead or further utilize tight fitment between components or a bio-absorbable fill material to seal an interface between the rotor shaft and pump housing to seal the bearing assembly from fluid flowing through the pump.

Abstract: Blood pump devices having improved rotary seals for sealing a bearing assembly supporting a rotor provided herein. Such rotary seals are particularly suited for use in blood pump devices that include rotors having cantilevered supported through a sealed mechanical bearing disposed outside a blood flow path of the device to avoid thrombus formation caused by blood contact with the bearing. The rotary seal can include a first and second face seal that are preloaded with a deflectable compliance member incorporated into the pump housing or a pair of magnets. Such rotary seals can instead or further utilize tight fitment between components or a bio-absorbable fill material to seal an interface between the rotor shaft and pump housing to seal the bearing assembly from fluid flowing through the pump.

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.

Abstract: According to an embodiment disclosed herein, an apparatus for cooling a rotating part having cooling channels therein, the rotating part attaching to a disk rotating about an axis, the disk having a conduit for feeding a cooling fluid to the cooling channel is described. The apparatus has a first impeller rotating with the disk and in register with the conduit and an outer periphery of the disk, the impeller directing the cooling flow to the conduit.

Abstract: A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.

Abstract: A seal is provided between first and second relatively movable members. The seal comprises a liner attached to the first relatively movable member which liner is abraded by the second relatively movable member. The abradable liner comprises a metallic, open porous structure formed by fusing a metallic feedstock with an energy beam to build up sequential deposits of the fused feedstock.

Abstract: A brush seal assembly for turbomachinery having a rotor can include a stationary seal component, a floating seal component coupled to the stationary seal component and circumferentially angled bristles arranged in a bristle pack, disposed in the floating seal component and extended axially with respect to the rotor.

Abstract: A centrifugal pump includes at least one impeller (4) and at least one sealing arrangement arranged between the impeller (4) and a housing wall. The sealing arrangement seals a suction side of the impeller (4) with respect to a pressure side of the impeller (4). The sealing arrangement including a seal (12) fastened on the impeller (4) in a rotationally fixed manner.

Abstract: A method and system for improving performance of a compressor section of a gas turbine by diverting leakage air flowing from high pressure downstream of a stator vane assembly to low pressure upstream of the stator vane assembly from disrupting design flow patterns at a leading edge of stator vanes. A cover is provided at a forward face of an inner shroud assembly to prevent the leakage air from impinging on the leading edge. The cover may be provided at an outlet channel of a flow diverter mounted on the forward face of the inner shroud assembly.

Abstract: A ventilation fan includes a rotor holder rotating around a rotation axis, an impeller cup including a plurality of blades provided on an outer circumference thereof, and a base portion arranged to rotatably support the rotor holder through a bearing portion. The base portion includes an outer circumferential wall extending upwards in an axial direction from an outer circumferential edge portion thereof. A gap defining a labyrinth structure is provided between an upper end portion of the outer circumferential wall of the base portion and a lower end portion of an outer circumferential portion of the impeller cup. A lower end portion of a cylindrical portion is located axially lower than the upper end portion of the outer circumferential wall of the base portion.

Abstract: The invention relates to a turbine of a power plant, having a stator, which has a housing and in the housing at least one stator blade carrier comprising stator blades. A rotor is provided which has a rotor shaft having rotor blades. At least one sealing device is provided which axially seals the respective stator blade carrier with respect to the housing and separates two regions having different pressures from one another. Improved sealing action is achieved in that the sealing device includes an axially acting primary sealing ring extending in the circumferential direction, and an axially acting additional sealing ring extending in the circumferential direction. The primary sealing ring facing the region has the lower pressure. The additional sealing ring facing the region has the higher pressure. The primary sealing ring is attached axially rigidly on the stator blade carrier.

Abstract: A compressor stator blade 10 includes a seal mechanism 12 configured to hermetically seal a part between a radial inner end on the upstream side and an outer surface of a rotary body, and a remainder part on the downstream side of the seal mechanism includes a hub clearance 14 between the outer surface of the rotary body and itself. Additionally, a compressor rotor blade 20 includes a seal mechanism 22 configured to hermetically seal a part between a radial outer end on the upstream side and an inner surface of a stationary body, and a remainder part on the downstream side of the seal mechanism includes a tip clearance 24 between the inner surface of the stationary body and itself.

Abstract: A turbine blade sealing system for reducing a gap between a tip of a turbine blade and a stationary shroud of a turbine engine. The sealing system includes a plurality of flexible seal strips extending from a pressure side of a turbine blade generally orthogonal to the turbine blade. During operation of the turbine engine, the flexible seal strips flex radially outward extending towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the turbine blades and increasing the efficiency of the turbine engine.

Abstract: A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the blades on an annular casing area and/or an annular drum area.

Abstract: A sealing arrangement for sealing between segments of a component assembly. The sealing arrangement includes a sealing member having a mating surface for mating with the surface of the segment. The sealing arrangement further includes a location member removably attached to the sealing member along a transition region therebetween, and also a free end distal to the sealing member. The location member is configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature. The location member is configured to be detached from the sealing member along the transition region and be removed from the segment after the sealing member has been bonded to the segment.

Abstract: A runner assembly for a circumferential seal assembly includes a runner having an inwardly extending runner mounting flange, a flexible mounting structure and a retainer assembly therefore.

Abstract: A hollow shaft of a turbomachine including a cylindrical wall with an inner surface portion and at one end a member for attachment to a rotor disk of the turbomachine is disclosed. The shaft also includes a damping device wherein at least one vibration-damping laminate is attached to the inner surface portion. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and a counterlayer of rigid material.

Abstract: A multi-stage submersible pump uses impellers having only one shroud to provide stages with shorter stack lengths to allow more stages per housing and more head pressure per housing. The impellers are biased with wave springs to keep the rotating impeller vanes close to the mating diffusers. The entire stack of impellers is assembled in contact with each other using the wave springs and are always under axial load. The wave springs also take up any tolerance variations in the stack to keep the impellers in proper running position. To keep the impellers in their proper locations, thrust washers formed from hard materials are used between adjacent impellers to avoid erosion thereof.

Abstract: The invention relates to a device for sealing the space between first and second components, wherein a sealing element is placed between the sealing surface of the first component and the sealing surface of the second component, means are used for displacing the sealing element towards the first component and the sealing surface of the second component is used in the form of a guiding surface for the sealing element when it is displaced towards the first component. The means comprise a movable pressure element which is embodied in such a way that the displacement thereof generates the displacement of the sealing element.

Abstract: The hybrid seal assembly includes a seal for use with rotating surfaces which may suffer significant deflections such as for sealing between flanges and mating surfaces typical of annular seal face surface of a diffuser section of a tip turbine engine.

Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a structure operable to rotate about an axis and having a first surface facing radially outward. The circumferential sealing arrangement also includes a static housing circumscribing the rotatable structure. The circumferential sealing arrangement also includes at least one seal element connected to the static housing and having a second surface facing radially inward. The circumferential sealing arrangement also includes a seal runner rotatable with the structure and having a third surface facing radially outward. The third surface cooperates with the second surface to form a circumferential seal between the static housing and the rotatable structure. A radial gap is defined between the first surface of the rotatable structure and a fourth surface of the seal runner facing radially inward and opposing the first surface.

Abstract: A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface. The seal assembly provides minimal leakage of core airflow to increase the tip turbine engine operating efficiency.

Abstract: An axial seal arrangement is provided between a rotor and a stator. The rotor is provided with a first disk having a substantially flat sealing face surface. The stator is provided with a second annular disk surrounding the rotor, supporting proximate ends of a plurality of axially extending, flexible, compliant seal elements arranged in an annular array of plural, circumferentially-overlapping radial layers to thereby provide a tortuous path for radially outward leakage flow.

Abstract: An impeller assembly includes a molded impeller and an insert within the impeller. The insert includes an unthreaded sleeve and a shoulder adjacent the sleeve for locating the impeller and the insert during manufacturing and installation. Methods of manufacturing and installing are also disclosed.

Abstract: A blade for a rotor assembly including a root portion, a platform with an overhang, an airfoil portion and a sealing plate. The sealing plate protrudes from the blade along a circumferential direction.

Abstract: Angel wing seals for turbines are described. In one aspect, an angel wing seal between a rotor blade and nozzle in a turbine inhibits ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces. The seal includes, in an example embodiment, a seal body extending from a shank of the blade and generally toward the nozzle. The seal body has at least one concave surface.

Abstract: A floating ring seal arrangement for rotodynamic pumps comprises a flexible ring that is structured to fit within a circular channel formed by generally concentric grooves in the rotating and non-rotating elements of the pump, the ring further being sized to rest against the inner diameter of the groove of the rotating element when static, and capable of radially expansion under centrifugal forces to cause the flexible ring to float in the circular channel during operation of the pump, or deformation under centrifugal or pressure forces such that gaps between the flexible ring and groove in the non-rotating element are minimized or eliminated.

Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: A radial seal is provided for installation within a centrifugal pump of the type having an impeller, a pump casing having a suction inlet, a sealing ring groove formed in the pump casing, and means for supplying flushing water to the sealing ring groove. The radial seal comprises a seal body, including a sealing end, a water inlet end, and opposed sides. The sealing end has an outwardly extending lip portion. The seal is adapted for installation within the sealing ring groove, with openings formed through the seal body for the passage of water.

Abstract: A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section, and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section. The annular heat shield member includes a plurality of slots formed on a surface of the heat shield member in a radial direction of the annular heat shield member.

Abstract: A seal assembly including a rotatable seal head subassembly also includes a fan that rotates with the seal head assembly, with the fan drawing air through a pump housing for purposes of cooling.

Abstract: A device for application in a fan configuration is configured, in particular, to be directly driven by an electric motor. In the fan configuration, a centrifugal fan wheel is mounted to rotate in unison with a drive shaft. The centrifugal fan wheel, for producing a directed airflow, is surrounded by a fan housing. A seal is disposed in an admission orifice, for largely filling in an air gap between the centrifugal fan wheel and the inner surface of the fan housing. Such a configuration improves the housing and sealing thereof for an application in a vacuum cleaner by having the sealing device be embodied as a sealing ring linked to a buffer part out of the fan housing, which part tightly surrounds the admission orifice.

Abstract: An improved motor-driven pump is provided for delivering a flow of water in a swimming pool or spa environment or the like. The improved pump includes a motor mounted within a motor housing having a seal plate mounted at one end thereof. The seal plate carries a shaft bearing for rotatably supporting a drive shaft having an outboard end connected to an impeller disposed within a pump chamber defined cooperatively by the seal plate and a volute housing mounted thereon. A primary seal assembly includes an axially spring-loaded dynamic seal ring carried on the drive shaft for rotation therewith and for running engagement with a stationary bushing carried by the seal plate. A secondary seal assembly is positioned axially between the primary seal assembly and motor bearing, and includes at least one slinger disk for radially outwardly slinging any water leaking past the primary seal assembly through a vent chamber.

Abstract: A method for controlling fluid leakage between a first pressure region and a second pressure region within a gas turbine engine using a first sealing member and a second sealing member. The first sealing member is movably coupled to a portion of the gas turbine engine, and a space defined generally between a portion of the first sealing member and a portion of the second sealing member fluidly couples the first pressure region to the second pressure region. The method includes moving the first sealing member towards the second sealing member using fluid pressure within a portion of the engine, and, using the first and second sealing members, substantially controlling fluid leakage between the first pressure area and the second pressure area through the space generally without contacting the first sealing member with the second sealing member.

Abstract: A seal arrangement for an impeller assembly, the impeller assembly including an impeller housing (34) adapted to receive a drive shaft. An impeller (10) is located within the impeller housing (34) and is adapted for connection to the drive shaft for rotation by the drive shaft about an axis. The seal arrangement includes an annular seal (24) located axially between the impeller housing (34) and the impeller (10) to provide a substantially fluid tight seal between the impeller housing (34) and the impeller (10).

Abstract: A high-pressure ratio turbocharger of this invention has a two-stage compressor section comprising a first-stage compressor impeller rotatably disposed in a first compressor housing, and a second-stage compressor impeller rotatably disposed in a second-stage compressor housing. The first and second stage compressor impellers are attached to a common shaft, and are positioned within respective compressor housing in a direction facing away from one another. A portion of the second-stage compressor housing is formed from a compressor backplate attached to a turbocharger center housing. A scroll seal is disposed between the first and second-stage compressor housings, and is interposed between the impellers to separate outlet air flow between each respective first and second-stage compressor chamber.

Abstract: A turbomachinery seal (20) attached to annular member (30) which surrounds and rotatably engages a shaft (34). The seal is capable of sealing pressure differentials between a high pressure region (24) and a low pressure region (26) well in excess of 300 psi at relatively low leakage rates. One embodiment (120) of the seal includes a plurality of confronting plates (128) arranged so as to form an annular structure. Another embodiment (220) includes a plurality of bristle packs (252), each positioned between annular plates (256) having an axial taper (278) adjacent radially inner ends (274). In another embodiment (320) bristles 334′ and 334″ extend in axial positive and negative directions so as to create an interleaved bristle structure. In yet another embodiment (720), a plurality of elongate members (450) are embedded within bristles (434). A turbomachine (550) includes seals 520′ and 520″ of the invention.

Abstract: A compressor in which an electric motor and a compressing mechanism are accommodated in a case, a main shaft and an auxiliary shaft of a rotating shaft of the motor are supported by a radial plain bearing and a rolling bearing with a predetermined clearance given to the rotating shaft in an axial direction, a flange portion that contacts with a main-shaft receiving member of the radial plain bearing to align the rotating shaft with the compressing mechanism is provided on the main shaft, and preload toward the side of the rolling bearing is given to the rotating shaft. In this constitution, a prevention member for preventing contact and/or collision of the rotating shaft with the main-shaft receiving member is provided between opposing faces of the flange portion and the main-shaft receiving member.

Abstract: A seal for use in a centrifugal pump of the type used for pumping an abrasive slurry, and having a sealing ring groove formed in the pump casing and an arrangement for supplying flushing water, comprising a radial seal having a sealing end, a water receiving end, and opposed sides and adapted for installation within the sealing ring groove, the radial seal having multiple openings formed therethrough for the passage of flushing water. The openings are dimensioned and located so that when flushing water is supplied to the water receiving end of the radial seal, the water flows through the openings, causing the radial seal to automatically moves to a self-compensating balanced position between the pump casing and a rotating pump impeller. This will reduce leakage between the pump casing and pump impeller and reduce wear of the pump surfaces.

Abstract: An integrated boot, seal and impeller system is adapted for being driven by a pump shaft. The system includes an impeller unit having a plurality of radially extending blades, a hub portion, a recess in the hub portion and a tubular portion extending from the hub portion. The tubular portion is engaged to the shaft and has an outer diameter with at least one flat in the outer diameter. A seal head is slidingly engaged to the tubular portion. The seal head also has an inner diameter with at least one flat on the inner diameter to engage the outer diameter of the tubular portion. A flexible boot extends from the elastomeric blades. The boot has a distal portion adjacent to the seal head. Additionally, a biasing member is disposed in the recess and urges the seal head into engagement with the seal washer.

Abstract: A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.

Abstract: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.

Abstract: A double-seal/oil-reservoir system for motor/pump assembly includes first seal (S1) and a second seal (S2) of a carbon/ceramic ring type that are axially spaced from one another along a drive shaft (24). A containment volume “V” is defined between the first and second seals (S1 and S2) in which an oil or oil-like fluid is contained to prevent seepage or weepage of the fluid circulated by the pump.

Abstract: A water pump with a plurality of elastomeric blades on a rigid impeller is disclosed. The impeller has a tubular extension with a pair of flats on the outer diameter of the extension. The seal seat has a corresponding pair of flats on its inner diameter to engage the flats on the tubular extension for positive rotation. The impeller also has a retaining lip formed on its inner diameter and a sealing shoulder to form a retaining cavity along the tubular extension. The retaining lip receives the seal seat in the cavity by stretching the lip radially into a gap to accommodate the outer diameter of the seal seat. This stretch to fit feature eliminates the need to control the outer diameter of the seal ring to precise dimensions. The lip forms a static seal with the outer diameter of the seal seat. The elastomeric shoulder provides a static seal against the seal seat.

Abstract: A floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a land region, a second non-rotary component having an end extending over and around at least a portion of the land region with the floating brush seal being positioned between the first and the second component to substantially reduce the flow of air between the first and second component. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is disclosed.

Abstract: In a centrifugal pump, a barrier ring in the form of a dynamic seal member is interposed between relatively rotating, generally circular wall portions which undergo relative axial movement to vary the width of a gap between the wall portions, the seal member having an outer jacket of flexible material and an annular spring member of frustoconical configuration inserted into offset grooves in the jacket, and when the seal member is mounted under compression between the confronting surfaces will follow the relative axial movement between the wall portions to maintain liquid-tight sealing engagement with the wall portions. In a modified form of invention, the seal member includes a pair of helical spring members inserted into grooves in an outer flexible jacket and, when the seal is mounted under compression between confronting surfaces of the wall portions as described will maintain liquid-tight sealing engagement notwithstanding variations in the width of the gap between members.