Abstract: A turbine engine includes a rotor, a stator, and a seal assembly disposed between the rotor and the stator. The seal assembly includes seal segment. The seal segment includes a seal face that is configured to form a fluid bearing with the rotor. A lift channel extends within the seal segment from an opening on the seal face. The turbine engine further includes a spring assembly disposed within the lift channel. The spring assembly including a biasing element and a piston element coupled to the biasing element. The lift channel includes a lift volume portion extending is between the opening and the piston element. The piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion.

Abstract: A shroud assembly for a turbine engine having a centerline axis. The shroud assembly having a shroud hanger, at least one shroud segment, and at least one biasing element extending between the two. The biasing element configured to radially bias the at least one shroud segment between an outboard position and an inboard position radially outward from the outboard position with respect to the centerline axis.

Abstract: A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.

Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.

Abstract: An illustrative embodiment of a shaft seal assembly generally includes a first stator, a second stator, and a throttle member. In one illustrative embodiment, the second stator may be formed with a main body and an access plate positioned radially interior with respect to a portion of the first stator. The first stator and second stator may engage one another about a semi-spherical interface comprised of a convex surface on the second stator and a concave surface on the first stator. The second stator may include an internal channel in which a throttle member may be positioned, wherein a radially interior surface of the throttle member may be positioned a shaft.

Abstract: A seal assembly for an aircraft engine includes a first seal having an upstream end exposed to a first pressure area, and a downstream end exposed to a second pressure area, the first seal at least partially defining an intermediate pressure area and a chamber being fluidly connected to the second pressure area and to the intermediate pressure area through passages defined in the first seal, the chamber allowing for a mixing of a first portion of a stream of air with air from the second pressure area, and a second seal connected to the first seal, the second seal biasing the first portion of the stream of air toward the passages, and allowing a second portion of the stream of air from flowing therethrough toward the second pressure area. A method of flowing air through an aircraft seal assembly is also described.

Abstract: A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.

Abstract: A system includes an air chamber and an oil capture cavity. The air chamber includes an inlet to receive pressurized air from a gas turbine engine. The oil capture cavity is positioned between the air chamber and an oil sump supplying lubricating oil to the gas turbine engine. The oil capture cavity includes an auxiliary vent formed in a base of the oil capture cavity. A seal may separate the oil capture cavity from fluid communication with the oil sump. A nozzle provides fluid communication between the oil capture cavity and the air chamber. The nozzle is configured and positioned to direct a stream of the pressurized air into the oil capture cavity against an opposite wall of the oil capture cavity to create a quiescent zone at the base of the oil capture cavity. The quiescent zone includes the auxiliary vent.

Abstract: A wheel bearing assembly includes a fixed inner axle with at least one inner race, a rotatable outer hub disposed about the axle and having at least one outer race and rolling elements disposed between the inner and outer races. An annular seal is disposed between the axle and the hub and is located adjacent to the inner and outer races. A shield is spaced axially from the seal such that the seal is disposed between the rolling elements and the shield. The shield includes a rigid annular body having an outer radial end coupled with the outer hub, preferably by a plurality of couplers, and an inner radial end defining a central opening for receiving the axle and located adjacent to the inner axle or a component disposed upon the axle. As such, the annular body substantially obstructs an annular interior space to prevent substances from contacting the seal.

Abstract: A seal assembly for a gas turbine engine defining a central axis extending along an axial direction and including a rotating shaft extending at least partially along the axial direction. The seal assembly includes a first component coupled to a fixed structure or drivingly coupled to the rotating shaft. The seal assembly further includes a rotating component drivingly coupled to the rotating shaft of the gas turbine engine. Additionally, the first component and rotating component define an annular gap therebetween. The seal assembly also includes one or more flanges extending from the stationary component, the rotating component, or both. The flange(s) include a base and an external surface extending into the annular gap from the base to a tip. Additionally, the flange(s) defines an inlet port on the external surface fluidly coupled to an outlet port at the tip. As such, the flange(s) forms a seal within the annular gap.

Abstract: A sealing device for a gas-liquid two-phase fluid medium under variable working conditions includes a rotating shaft and a housing, and a chamber formed by the housing is configured to accommodate the gas-liquid two-phase fluid medium. The sealing device further includes a labyrinth sealing mechanism and a fluid dynamic-pressure mechanical sealing mechanism with double end faces, where the labyrinth sealing mechanism and the fluid dynamic-pressure mechanical sealing mechanism with double end faces conduct mutual synergetic effect. Sealing buffer chambers are arranged between the labyrinth sealing mechanism and the fluid dynamic-pressure mechanical sealing mechanism; the fluid dynamic-pressure mechanical sealing mechanism is provided with stationary rings and movable rings, where the stationary rings and the movable rings oppositely abut against with each other.

Abstract: A sealing arrangement for an electric machine, which is between a first part attached to a rotatable shaft and a second part immobile with respect to a stator of the electric machine includes a plurality of zig-zag sections of a channel of a labyrinth seal in a radial direction of the electric machine. The channel of the labyrinth seal includes a second seal which is fixedly attached to the first part and which has an elastic material part, the second seal is pressed in the radial direction against a surface of the second part, a normal of which has a component parallel to the radial direction, at rotational speeds a centrifugal force of which to the second seal is weaker than a spring force of the second seal, and the second seal opening a gap between the second seal and said surface at rotational speeds the centrifugal force of which to the second seal is greater than the spring force of the second seal.

Abstract: A labyrinth sealing joint for a turbomachine, for example of an aircraft, includes a rotor element extending about an axis (A), and a stator element extending around the rotor element, the rotor element having two annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. A plurality of gas passage cavities are arranged circumferentially next to one another between the two lips which are interconnected by connecting partitions, wherein at least one of the lips has at least one axial gas passage opening that leads into at least some of the cavities, wherein the partitions extend substantially axially between the lips and define sectors of gas passage spaces between them, the sectors of spaces being divided by separation walls for forming the cavities.

Abstract: A traction transmission for purposes of transmitting the rotation of an input drive shaft to a rail wheel which is connected in a rotationally fixed manner to an output drive shaft, has at least two transmission stages, in each case having at least one small gear or pinion, and at least one large gear, and has a transmission housing with bearings for the input drive shaft and the output drive shaft, and has transmission oil arranged in the transmission housing, wherein in the position of use the input drive shaft is arranged below the output drive shaft. The transmission housing has an attachment element for purposes of a pivotable arrangement about an axis parallel to the axis of rotation of the input drive shaft and output drive shaft.

Abstract: In a piston including a plurality of piston rings, a state where a difference in differential pressure between the piston rings is eased is maintained even after passage of time, and the life of the piston rings is extended. A piston includes a piston body in which a plurality of ring grooves is formed, and a plurality of piston rings respectively arranged in the ring grooves. In the piston, a leakage groove is formed on a low-pressure side surface of the ring groove, and in a state where the piston ring is abutted with the low-pressure side surface while being abutted with a cylinder, the leakage groove ensures communication between a high-pressure side space and a low-pressure side space with respect to the piston ring.

Abstract: A magnetic liquid sealing device is provided. The magnetic liquid sealing device includes a housing, a rotating shaft, a pole shoe, a permanent magnet, and a first sealing ring. The rotating shaft is provided with an annular first stop portion, the pole shoe has a first end face and a second end face opposite to each other in an axial direction of the rotating shaft, and the permanent magnet is fitted over the rotating shaft. The first sealing ring is fitted over the rotating shaft, and includes a first part and a second part. The first part is sealedly fitted with at least one of the first end face and an inner peripheral surface of the housing, and an inner end of the second part is a first free end movably arranged along the axial direction of the rotating shaft.

Abstract: A robot drive unit is provided with: a housing; a shaft body that is relatively rotated with respect to the housing; rotating-body sealing members that is provided in the housing; a contact-surface member that is provided on the shaft body and that contact with the rotating-body sealing members; and a sealing member that seals a gap between the shaft body and the contact-surface member.

Abstract: A system includes an air chamber and an oil capture cavity. The air chamber includes an inlet to receive pressurized air from a gas turbine engine. The oil capture cavity is positioned between the air chamber and an oil sump supplying lubricating oil to the gas turbine engine. The oil capture cavity includes an auxiliary vent formed in a base of the oil capture cavity. A seal may separate the oil capture cavity from fluid communication with the oil sump. A nozzle provides fluid communication between the oil capture cavity and the air chamber. The nozzle is configured and positioned to direct a stream of the pressurized air into the oil capture cavity against an opposite wall of the oil capture cavity to create a quiescent zone at the base of the oil capture cavity. The quiescent zone includes the auxiliary vent.

Abstract: An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.

Abstract: A wrist structure of a robot capable of protecting an oil seal of a wrist structure from a high-pressure jet for cleaning or from external foreign matter or the like. A wrist structure of a robot includes a wrist body, a holder attached to the wrist body, a wrist flange rotatably supported by the holder, an oil storage provided between the wrist body and the holder, an oil seal disposed between the holder and the wrist flange and configured to prevent oil from leaking from the oil storage, and a cover that is formed integrally with the holder and that covers the oil seal from the outside between the holder and the wrist flange.

Abstract: A leakage management assembly for an orifice configured to limit a flow of at least one of a leakage fluid and a cooling fluid past an instrument positioned within the orifice are provided. The leakage management assembly includes a labyrinth ferrule including an annular ferrule body having a central bore extending therethrough. The labyrinth ferrule further includes an annular assembly cone formed at a first end of the labyrinth ferrule. The annular assembly cone includes an annular convergent lip and is configured to facilitate directing the instrument into the central bore. The labyrinth ferrule also includes a plurality of labyrinthine annular restrictions extending from a radially inner surface of the annular body toward the central bore. A combustor and a gas turbine engine including such a seal assembly are also provided.

Abstract: A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.

Abstract: An apparatus for sealing an internal environment of a turbomachine includes a first chamber connectable in fluid communication with a high pressure environment of a turbomachine so that a working fluid can flow from the high pressure environment to the first chamber; and a second chamber in fluid communication with a lubrication circuit so that a lubricant can flow from the lubrication circuit to the second chamber. The first and second chambers are arranged in fluid communication with each other so that the working fluid can flow from the first to the second chamber. A return line for the working fluid is in fluid communication with the first chamber and connectable in fluid communication with a low pressure environment of the turbomachine so that the working fluid can flow from the first chamber to the low pressure environment. A pressure regulating device is included along the return line and is configured to provide a predetermined pressure drop.

Abstract: An axial flow rotating machinery includes: a rotor; a casing; a rotating-blade stage including rotating blades and a radially-outer side rotating blade ring continuing to radially outer ends of the rotating blades; and a rotating-blade side seal device configured to seal a gap between the radially-outer side rotating blade ring and the casing. The rotating-blade side seal device includes: a seal fin having an annular shape and extending toward an outer peripheral surface of the radially-outer side rotating blade ring from the casing; and a swirl brake fixed to the casing in a cavity formed at an upstream side of the seal fin. The swirl brake includes: a first plate-shaped member having a surface along a radial direction of the rotor; and a second plate-shaped member or a third plate-shaped member having a surface oblique to the radial direction of the rotor.

Abstract: A high speed labeling machine especially designed for use in food or pharmaceutical processing environments. It can be periodically washed down in accordance with applicable governmental standards without entry of washing fluid into an interior of an enclosure assembly containing servo motors and the electronics for driving shafts that penetrate through a wall of the enclosure assembly and on which a label web supply reel and a web take-up reel are removably mounted. A plurality of idler rollers and a pinch roller are used to route the label carrying web from the supply reel, over an edge of a peel plate, where the labels are separated from the web, and back to the web take-up reel. The idler rollers and the pinch rollers are journaled on shafts in a way precluding entry of wash fluids into their interior. The enclosure assembly is cantilever-mounted on a jack stand for vertical adjustment relative to items to be labeled.

Abstract: A gearbox includes a main housing carrying input and output shafts, a carrier mounted to the housing having a bore, an isolator plate mounted to the carrier having a bore aligned with the carrier bore, and an isolator mounted to the isolator plate having a bore aligned with the isolator plate and carrier bores. The carrier includes an oil collection well, spaced from the bore, and an oil return channel in fluid communication with the oil collection well that extends through the carrier to the main housing. The isolator plate includes an interior surface and an oil passage formed therein that extends from the interior surface to the oil collection well, such that the interior surface is in fluid communication with the main housing via the oil passage, the oil collection well and the oil return channel, and fluid at the interior surface is drawn into the main housing via the oil passage, the oil collection well and the oil return channel.

Abstract: A seal structure is for sealing leakage fluid flowing through a gap between a rotation member rotating about a rotation axis and a stationary member facing the rotation member. The seal structure includes seal fins projecting from a base that is one of the rotation and stationary members toward the other one, the seal fins being spaced apart from each other at a certain interval in an axial direction of the rotation axis; and a step section provided to the other one, the step section including step surfaces facing the seal fins and a riser surface between the adjacent step surfaces, the step surfaces and the riser surface defining a step portion. The seal fins are inclined upstream in a flow direction of the leakage fluid relative to a radial direction perpendicular to the rotation axis. Each seal fin and the base define a corner portion having a curved surface.

Abstract: Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element The rotor element includes a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. Each lip includes an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation. At least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.

Abstract: A seal structure is for sealing leakage fluid flowing through a gap between a rotation member rotating about a rotation axis and a stationary member facing the rotation member. The seal structure includes seal fins projecting from a base that is one of the rotation and stationary members toward the other one, the seal fins being spaced apart from each other at a certain interval in an axial direction of the rotation axis; and a step section provided to the other one, the step section including step surfaces facing the seal fins and a riser surface between the adjacent step surfaces, the step surfaces and the riser surface defining a step portion. The seal fins are inclined upstream in a flow direction of the leakage fluid relative to a radial direction perpendicular to the rotation axis. Each seal fin and the base define a corner portion having a curved surface.

Abstract: A dry vacuum pump, comprising a pump housing, which forms a plurality of suction chambers, wherein rotor elements are arranged in the suction chambers, in order to convey a pump medium from a high-vacuum-side inlet to an outlet. At least one rotor element is arranged in each suction chamber. The rotor elements are connected to a rotor shaft. The rotor shaft is supported by bearings, wherein a high-vacuum-side bearing is arranged in a cut-out. A sealing device is arranged between the high-vacuum-side bearing and at least one suction chamber adjacent to the high-vacuum-side bearing. The cut-out is connected, by means of a first channel, to a region of the dry vacuum pump in which there is a higher pressure than in at least one suction chamber adjacent to the high-vacuum-side bearing.

Abstract: The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.

Abstract: An assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes to the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to the first seal shoe. The second mount is connected to the seal base and disposed a circumferential distance away from the first mount. The spring beam extends longitudinally along a non-straight centerline between and connected to the first mount and the second mount.

Abstract: An electric motor assembly for pumping a fluid through a fluid cavity includes a stator assembly including a plurality of conduction coils configured to transmit heat energy to the fluid within the fluid cavity. The electric motor assembly also includes a rotor assembly positioned adjacent the stator assembly to define an axial gap therebetween. The electric motor assembly also includes an impeller directly coupled to the rotor assembly opposite the stator assembly such that the rotor assembly and the impeller are configured to rotate about an axis. The rotor assembly and the impeller are configured to be submerged in the fluid within the fluid cavity.

Abstract: A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor. Each of the thin plates has a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate.

Abstract: An electric motor assembly includes a bearing assembly including a rotating component and at least one stationary component. The electric motor assembly also includes an impeller coupled to the rotating component. The impeller includes an inlet and an outlet and is configured to direct a fluid between the inlet and the outlet. The electric motor assembly also includes a rotor assembly directly coupled to the impeller. A fluid flow channel is defined between the rotating component and the at least one stationary component. The flow channel includes a first end proximate the impeller outlet and a second end proximate the impeller inlet.

Abstract: A housing for an air cycle machine includes a housing with a first end and a second end opposite the first end, a first duct adjacent the first end of the housing with an air inlet and an air outlet, a second duct adjacent the second end of the housing with an air inlet and an air outlet, and a collar in the housing extending into the second duct. The collar includes a first annular surface facing radially inward and configured to engage a journal bearing and a second annular surface facing radially inward and configured to engage a rotating shaft, wherein the second surface is monolithic with the housing.

Abstract: A sealing device includes: a sealing body that seals a gap between a rotor and the sealing body; a fastening bolt that fixes the sealing body to a stator; and a bolt sealing part that seals a gap around the fastening bolt. The sealing body includes: a facing surface that faces a fixing surface of the stator facing in an axial direction; and a body through-hole that penetrates the sealing body and opens on the facing surface. The bolt sealing part is disposed in a gap between a head portion and the inner peripheral surface of the body through-hole, or between the fixing surface and the facing surface.

Abstract: A sealing apparatus includes a sealing apparatus body attached to an outer ring of a hub bearing, and a slinger attached to a hub, and the sealing apparatus body includes a reinforcement ring and an elastic body portion. The elastic body portion includes seal lips contacting the slinger, and a labyrinth lip forming a gap from the slinger. The slinger includes a slinger cylinder portion, a slinger flange portion, a slinger bent portion, and a slinger extended portion, and the slinger bent portion and the slinger extended portion form a labyrinth seal L1, having gaps between the elastic body portion and the outer ring.

Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

Abstract: A sealing system for at least one floatingly mounted ring in a support for a rotary shaft rotatable about an axis directed along a longitudinal direction provides dynamic sealing between the shaft and the support. The system includes a coupling part interposed between the ring and the support, whereby the ring is secured to the support. A first cylindrical type joint directed with respect to a first transverse direction provides a joint between the support and the coupling part. A second cylindrical type joint directed with respect to a second transverse direction perpendicular to the first transverse direction provides a joint between the ring and the coupling part. A turbopump includes such rotary shafts and sealing systems.

Abstract: A turbine includes a rotor shaft having a plurality of rotating blades mounted on the rotor shaft, a bearing assembly rotatably supporting the rotor shaft, a casing forming a passage of a fluid and to include a space in which the rotating blades are disposed so that thermal energy of the fluid is converted into mechanical energy by rotation, a foundation fixedly supporting the bearing assembly, and a packing device installed in the rotor shaft for sealing between the casing and the rotor shaft and supported by the foundation. The casing comprises a connection unit extended toward the packing device and fixed to the casing so that a location of the connection unit is relatively changed with respect to the packing device. Accordingly, there is an advantage in that the leakage of a fluid is reduced because a clearance between the packing device and the rotor shaft is reduced.

Abstract: A seal structure (2) for sealing a gap between a first structure body (10) and a second structure body (51). The seal structure includes: a peripheral surface formed on one of the first structure body and the second structure body; a plurality of seal fins (5) provided at intervals in the axial direction so as to form clearances (m) together with the peripheral surface and protrusions that form re-adhesion edges between pairs of axially adjacent seal fins; the re-adhesion edges being locations at which leak currents (SL) re-adhere that have passed through a clearance (mA) of an upstream seal fin; and the protrusions forming first cavities in which eddies (B1) are created that flow along the upstream seal fin toward the second structure body, and second cavities in which currents (B2) are created that cause a contraction current effect on a clearance (mB) of a downstream seal fin.

Abstract: A device and method for reducing swirl in a gas compressor is provided. The device can include a tubular or annular seal body having an abradable interior surface for use in forming a seal. The tubular body can further have a plurality of swirl teeth arranged on a high pressure side of the seal body. The swirl teeth are disposed so as to form swirl slots between the adjacent swirl teeth. The swirl teeth can have a brake chord and a brake pitch describing the length and separation of each adjacent swirl tooth. The ratio of the brake pitch to the brake chord can be optimized in order to maximize creation of free vortices between the swirl teeth as the compressor rotates for swirl reduction.

Abstract: A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount.

Abstract: A bearing isolator apparatus is for use in a piece of equipment which includes a rotatable shaft and a housing through which the shaft extends. The apparatus includes a static component for securing to the housing and a rotational component for securing to the shaft. A tortuous fluid path extends between the static component and the rotational component and a plurality of electrically conductive filaments extends between the static component and the rotational component, such that an electrical current can pass between the components. One or more conductive members electrically connect the rotor to the shaft.

Abstract: A plunger includes a sleeve having a passage therethrough and a valve member in the passage. When the plunger falls in a production string of a hydrocarbon well, the valve member is open and allows gas flow through the plunger. When the plunger contacts a liquid slug in the production string, the valve closes so that pressure from below reverses movement of the plunger so it pushes liquid above the plunger toward the earth's surface and ultimately to a well head where liquid and gas are separated.

Abstract: A bladed rotor and a hub rotor for a gas turbine are provided. A bladed rotor may comprise a rotor interface comprising a radially inward surface, wherein the rotor interface comprises a constant diameter zone; and a reduced stress zone located adjacent to and aft of the constant diameter zone. A hub rotor may comprise a hub interface comprising a radially outward surface, wherein the hub interface comprises, a constant diameter zone, and a reduced stress zone located adjacent to and aft of the constant diameter zone.

Abstract: An assembly includes a monolithic carrier structure and a seal assembly. The monolithic carrier structure includes a carrier base and a support ring. The carrier base extends axially along the centerline. The support ring projects radially inward from the carrier base. The seal assembly is nested radially within the carrier base and axially next to the support ring. The seal assembly includes a seal base, a plurality of spring elements and a plurality of seal shoes arranged about the centerline in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Abstract: The invention relates to a sealing segment for sealing between a stationary component and a rotating component. The sealing segment having a passage that extends so as to enable pressure balancing between radial ends of the sealing segment so by providing a seal that can ensure a minimum seal distance is maintained without the need for the complexities of actuators or other mechanical devices.

Abstract: A device includes a torque-proof first structural component and a second structural component rotatably connected to the first component. Hydraulic fluid is guided to lubrication points via the components. A sealing device seals an interface between the components. The interface includes a transition area limited by areas of the components that overlap in the radial direction and which carries hydraulic fluid, and which is connected to supply areas for hydraulic fluid of the first component and transmission areas for hydraulic fluid of the second component. The hydraulic fluid forms a floating hydrodynamic bearing between the components. The sealing device includes at least one thread area in the area of a surface of the second component or of the first component that is facing towards the surface of the first component or the second component.