Abstract: A circumferential shaft seal segment includes a radial outer face, a radially inner face, a first axial face extending from the radial outer face to the radial inner face and a second axial face axially spaced from the first axial face and extending from the radially outer face to the radially inner face. The seal has a bleed slot in the radially inner face extending from the first axial face toward the second axial face, and there are first and second recesses in the radially inner face in communication with the bleed slot that extend from circumferentially opposite sides of the bleed slot.

Abstract: A non-contacting seal is provided, including a first sealing face formed on an end of a primary ring and a second sealing face formed on an end of a mating ring. Grooves may be formed in at least one of the first and second sealing faces, such that the grooves extend from one edge of the respective sealing face to an intermediate radius of the respective sealing face. At least one groove may include an entrance edge along the one edge of the respective sealing face and a dam wall opposite the entrance edge. The at least one groove may also include two symmetric side walls extending from the entrance edge to the dam wall. The two symmetric side walls may include a first convex curve extending from the entrance edge to a transition point and a second concave curve extending from the transition point to the dam wall.

Abstract: A fluid resistance reducing method and a resistance reducing propulsion device are disclosed, wherein vane-shaped devices are inserted in the fluid at a certain interval along a vertical direction to a moving velocity direction of the fluid, and thus the fluid is divided into several limited zones to limit the fluid and solidify moving state; resultantly the fluid is prevented from directly crashing with fixed wall of a surface of an object to be resistance-reduced and thus a moving velocity direction of the vane-shaped device accords with a predetermined direction of a tangent line of the fixed wall and reaction force on the fluid provides a centripetal force for the fluid to turn, so as to force the fluid to gradually change the velocity direction along the fixed wall and manually intervene with parts of the object to force the fluid near a boundary face to moves stratifiedly and orderly.

Abstract: A continuous flow centrifuge system is provided. The system includes a rotor, a stator, a stator housing, upper and lower bearing plates, upper and lower bearings, first and second snap rings, and lip seal. The upper bearing rotatably secures a shaft of the rotor in the upper bearing plate. The first snap ring secures the upper bearing to the rotor shaft. The lip seal is over the upper bearing and forms a rotatable seal with the upper bearing plate. The second snap ring secures the lip seal to an inner diameter of the upper bearing plate. The upper and lower bearing plates are secured to the stator housing so that the rotor is operatively aligned with the stator.

Abstract: The power-assisted supercharger (10) includes: a turbocharger (12) in which a turbine (12a) is rotationally driven by exhaust gas (7) from an engine (40), a compressor (12b) rotationally driven by the turbine compresses intake air (5) and supplies the intake air to the engine; an electric motor (14) connected to a rotary shaft (12c) connecting the turbine and the compressor, the electric motor to add rotational force to the turbocharger; and a motor controller (20) to control a drive current (I) to the electric motor required for an assist operation for the turbocharger, by open loop, based on an accelerator opening degree (A) of the engine and a rotational speed (NE) of the engine. In this power-assisted supercharger, a turbo lag can be reduced by itself, power consumption can be small even in a range in which the rotational speed is high, malfunctions or unnecessary power consumption can be prevented, a control system can be simplified, and the installation space and the weight thereof can be small.

Abstract: A hydrodynamic face seal ring for use in a rotary machine includes a support ring having at least two support ring segments and a radially-extending, first face. The support ring is configured to releasably couple to an inner surface of an outer casing of the rotary machine. The face seal ring also includes a sealing ring substantially concentric with the support ring. The sealing ring includes at least two sealing ring segments and a radially-extending, second face. The sealing ring is releasably coupled to the support ring such that the first face is mated against the second face.

Abstract: In sealing rings for a labyrinth seal that are arranged on a rotationally symmetrical component and in frictional contact with a stationary run-in layer, a part of the sealing ring (8) that contacts the run-in layer is in the form of a wear protection ring segment (15) that is built up on a truncated sealing ring (14) and which includes a metal matrix (16) with wear protection particles (13) embedded therein. The manufacture of the wear protection ring segment is carried out by laser build-up welding, wherein the proportion of wear protection particles contained in the metal powder flow supplied to the laser beam can be controlled and increased in an edge or tip region of the sealing ring.

Abstract: An annular seal positionable in a gap is disclosed herein. The annular seal includes a plurality of leaves positioned about a center axis. Each leaf extends to a distal end that is elastically deflectable relative to the center axis to accommodate changes in a size of the gap. The annular seal also includes a ring encircling the center axis and at least partially interconnecting the plurality of leaves together for concurrent installation and removal. The annular seal also includes a plurality of tabs projecting from the ring along the center axis. Each of the tabs is directly connected to at least one of the plurality of leaves such that elastic deformation of one of the plurality of leaves induces bending in the corresponding tab before inducing bending in the ring.

Abstract: A non-contact labyrinth seal assembly, bearing assembly therewith, and method of construction thereof, has an outer rigid carrier and an inner sleeve. The carrier has an outer cylindrical flange and a radially inwardly extending leg and the sleeve has a cylindrical wall and a radially outwardly extending flange. A body is attached to at least one of the leg and the flange, wherein the body provides, at least in part, a purely non-contact labyrinth passage extending between the carrier and the sleeve.

Abstract: The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.

Abstract: A self-adjusting non-contact seal for sealing the circumferential gap between a first machine component and a second machine component includes structure which undergoes wear in the event of inadvertent contact with one of the machine components in such a way as to allow a reset of its radial distance from such machine component, compared to initial installation tolerances, while minimizing leakage.

Abstract: A knife edge seal assembly includes at least one knife edge and at least one honeycomb ring seal. The at least one knife edge has material removed to a first knife edge radial height and the least one honeycomb ring seal has material removed to a finished radial thickness for sealable engagement with the at least one knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.

Abstract: A non-contacting seal is provided, including a first sealing face formed on an end of a primary ring and a second sealing face formed on an end of a mating ring. Grooves may be formed in at least one of the first and second sealing faces, such that the grooves extend from one edge of the respective sealing face to an intermediate radius of the respective sealing face. At least one groove may include an entrance edge along the one edge of the respective sealing face and a dam wall opposite the entrance edge. The at least one groove may also include two symmetric side walls extending from the entrance edge to the dam wall. The two symmetric side walls may include a first convex curve extending from the entrance edge to a transition point and a second concave curve extending from the transition point to the dam wall.

Abstract: A rotating device includes a rotator on which a magnetic recording disk is to be mounted, and a stationary body that supports the rotator in a freely rotatable manner through a fluid dynamic bearing. A lubricant is continuously applied to a lubricant applied portion in a gap between the rotator and the stationary body and from a second capillary seal to a first capillary seal through a dynamic pressure generating portion of the fluid dynamic bearing. This rotating device is structured so as to reduce an amount of the lubricant spilled and eventually dissipated when shock of substantially 1200 G is applied to be less than 5% of the total amount of the lubricant.

Abstract: A sealing arrangement for a bearing assembly. The sealing arrangement can include a static seal carrier coupled to a static component of the bearing assembly and including a first plurality of rings, a rotating seal carrier coupled to a rotating component of the bearing assembly and including a second plurality of rings, the first plurality of rings and the second plurality of rings disposed in an interdigitated arrangement so as to define a tortuous passageway therebetween, the tortuous passageway having one end in communication with a high pressure area of the bearing assembly and a second end in communication with a low pressure area of the bearing assembly, and a scraper seal coupled to the rotating seal carrier and disposed over the second end of the tortuous passageway.

Abstract: A hydrodynamic mating ring includes a base and an insert coupled to the base. In embodiments, an insert has a coefficient of thermal expansion greater than the coefficient of thermal expansion of the base. A hydrodynamic seal assembly including a corresponding stator is also disclosed.

Abstract: A labyrinth sealing device is disclosed for use between a rotating shaft and a bearing housing. In some embodiments, an internal stator engages the housing and a rotor engages the shaft. A labyrinth pathway is defined between the rotor and stator to prevent the migration of lubricants and/or contaminants in either direction. The rotor acts as a running surface for the sealing element, but may also with a ground surface of the rotor to provide a pump that continuously draws lubricant away from the sealing lip toward a sump. In another embodiment, the stator and sealing element are combined as a single element formed from a sealing material. A recess in the sealing lip creates a pressure differential at the sealing surface and minimizes wear.

Abstract: The present invention provides a seal device comprising a sealing passage which allows communication between a first space and a second space, and evacuation lines individually connected to the first space and the sealing passage. A gas feed line for feeding dry gas is connected to the sealing passage.

Abstract: Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

Abstract: A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates.

Abstract: A seal assembly including first and second components; a seal arranged between the first and second components to seal a secondary flow region from a primary flow region; and a second recess portion provided on a surface of the second component between the seal and the primary flow region, the second recess portion further being arranged to receive a first portion of a flow from the secondary flow region and being configured to promote a second flow feature within the second recess portion, wherein the second recess portion is set back from the surface of the second component such that a second portion of the flow from the secondary flow region bypasses the second recess portion.

Abstract: A tool is disclosed for adjusting a seal. The tool includes an engagement block. The engagement block defines a slot configured to capture a portion of the seal. The tool further includes an impact surface connected to the engagement block, and a hammer head movable along a strike axis with respect to the engagement block and configured for striking the impact surface. Striking of the impact surface with the hammer head can cause movement of the seal.

Abstract: A seal for a turbomachine is disclosed. The seal assembly includes a rotatable shaft having a stepped outer circumferential surface that defines one or more annular protrusions axially-spaced thereon. A seal is radially-offset dially-offset from the rotatable shaft and has one or more annular recesses that extend radially-outward from the inner circumferential surface of the seal. A plurality of holes are defined in both the inner circumferential surface and the one or more annular recesses of the seal, the one or more annular recesses being axially-spaced from each other and configured to receive the one or more annular protrusions in an interlocking fit.

Abstract: An assembly for a gas turbine engine includes a component and a finger seal. The component has a first surface and a second surface. The first surface has an elevation that differs from an elevation of the second surface. The finger seal is connected to the first surface and extends above the second surface. The disposition of the second surface relative to the finger seal creates a cavity below a curved portion of the finger seal.

Abstract: A fluid control device for use in a high pressure fluid system, the device including a device body with a cavity and a high pressure circuit, a plunger positioned for reciprocal movement in the cavity, and a leakage reduction cap mounted to the plunger for reducing fluid leakage flow. In one implementation, the leakage reduction cap includes a flexible portion positioned between the device body and the plunger, and defining an annular clearance gap between the leakage reduction cap and the device body. The flexible portion of the leakage reduction cap resiliently flexes radially outwardly in response to fluid pressure forces to reduce the annular clearance gap so as to minimize fluid leakage flow through the annular clearance gap.

Abstract: There is disclosed a rotary air-riding seal between a first structure and an adjacent second structure, including: first and second seal members defining respective seal surfaces facing to one another. The first seal member is provided on the first structure and the second seal member is mounted to the second structure towards the first seal member. At least one of said seal members is configured to generate a riding film of air between said seal surfaces. One of said seal members is supported for axial oscillation relative to the other seal member by a secondary support arrangement configured to bias said seal member towards the other seal member. The said secondary support arrangement accommodates relatively high frequency axial movements between the seal members.

Abstract: A seal device is provided for sealing intermediate spaces formed between bodies arranged to be relatively movable, wherein the seal device has a resilient, gas-tight main body which is extendable in a peripheral direction and through which a portion of the first of the two bodies is guided, and a first end portion, which fastenable to the second body, and a second end portion, which is settable against the first movable body, wherein the second end portion is movable with respect to the first end portion in a first transverse direction which extends at an angle different from 0° with respect to a longitudinal direction. A sliding seal device, which is applicable to the first movable body so that a relative rotation is made possible between the first body and the second body by a pre-set angle, is arranged on the second end portion of the seal device.

Abstract: A system includes an electrodynamically suspended seal. The electrodynamically suspended seal includes a first element that includes an electrically conducting material and a second element that includes a magnetic material. At least one of the first and second elements is configured to rotate about an axial axis. The first and second elements are disposed adjacent one another. The rotational movement of at least one of the first and second elements creates a levitation force such that the first and second elements are repelled away from one another. The electrodynamically suspended seal also includes a third element configured to create a counteracting force.

Abstract: A controlled gap seal device is adapted to surround a shaft with an annular seal element. A ring is positioned on an outer surface of the seal element, the ring adapted to modify a diametrical dimension of the seal element by thermally expanding/contracting as a function of temperature variations. A housing assembly has an interior enclosing the seal element and the ring, with the seal configured to be generally stationary in the interior. The housing assembly has an air inlet and air outlet in fluid communication with a surrounding environment for directing a flow of gas from the surrounding environment onto the ring to controllably cool and shrink the ring. A method for modifying a diameter of a controlled gap seal relative to the shaft is also provided.

Abstract: An adverse pressure gradient seal mechanism for use with variable speed components. The adverse pressure gradient seal mechanism may include a number of labyrinth teeth positioned on a component and an adverse pressure gradient seal positioned between a pair of the labyrinth teeth. The adverse pressure gradient seal may include a number of strips with each of the strips having an angled end.

Abstract: A self-adjusting non-contact seal for sealing the circumferential gap between a first machine component and a second machine component includes structure which undergoes wear in the event of inadvertent contact with one of the machine components in such a way as to allow a reset of its radial distance from such machine component, compared to initial installation tolerances, while minimizing leakage.

Abstract: The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (1-3) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.

Abstract: The present invention relates to a windback device and method of use to prevent lubricant from leaking from a lubricant sump. More specifically, the present invention is comprised of a windback device within a lubricant sump formed from the coupling of an annular sump housing, an annular fluid seal assembly, and a bearing. The annular housing substantially surrounds the runner to form a chamber. The seal assembly is coupled to a sump housing both of which are adapted to receive a rotatable runner such that a sealed chamber is formed around the runner. A plurality of inclined threads extend along an inner face of the windback device and are angled such that lubricant or fluid splashed from the rotating shaft is redirected away from a shaft seal element of the annular fluid seal and through leak off slots leading to the sump housing chamber.

Abstract: In accordance with embodiments of this invention, a pressure actuated leaf seal assembly is provided that includes film riding, hydrodynamic/hydrostatic runners under seal member leaf ends. Leaf seal assemblies according to embodiments of this invention maintain the runner away from a rotating body until adequate rotating speed is present to generate lift required to allow the runner to float on a thin film of operating fluid on the rotating body, so that the runner does not rub the rotating body. In addition, runners are attached, or added, to leaf seal members such that the runners move in a radial direction, while remaining parallel to the rotating body. In one embodiment, a runner can comprise a separate structure coupled to a leaf seal member, and in another embodiment, a runner can comprise a wear-resistant pad on a distal end of a leaf seal member.

Abstract: The present relates to a seal for an energy recovery wheel. The seal comprises a main body defining an inner surface, and a pair of lateral walls extending from each lateral side of the main body. Each lateral wall respectively comprises a free edge defining a lip. The inner surface and lateral walls define a space therebetween. The seal provides for air travelling from one section of the energy recovery wheel to another to turbulate within the space. The inner surface is generally flat and the space may comprise a cavity. The lateral walls may be flexible or rigid. The present also relates to a combination of the seal with the energy recovery wheel.

Abstract: The present application thus provides a retractable seal system for use between a high pressure side and a low pressure side of a turbine engine. The retractable seal system may include a seal positioned in a slot of a stationary component, a pressure balance pocket positioned about the seal, and a conduit in communication with the pressure balance pocket and the high pressure side.

Abstract: A hydrodynamic sealing system for use in an oxidizing environment includes a rotor and a sealing stator. The stator includes a solid lubricant or a surface treatment and the rotor is hardened or the stator is hardened and the rotor includes the solid lubricant or the surface treatment. The stator is located proximate to the rotor to provide a seal. The stator and the rotor are robust at extreme temperatures above 700 degrees Fahrenheit (F) such that at least one of the stator and the rotor have a wear rate and a surface roughness sufficient to maintain an operating gap between the stator and rotor.

Abstract: A shaft seal that is constituted by annularly arranging a plurality of seal segments in the circumferential direction of a rotating shaft, in which each seal segment has a plurality of thin plates that are provided in a predetermined arrangement in the circumferential direction of the rotating shaft, side plates that sandwich the plurality of thin plates from both sides thereof in the axial direction, and retention rings that retain the base ends of the plurality of thin plates and the base ends of the side plates; the distal ends of the thin plates protrude farther toward the rotating shaft than the distal ends of the side plates, and the protrusion length of the distal ends of the thin plates in the vicinity of the end portions in the circumferential direction where adjacent seal segments are connected is set to be less than the protrusion length of the distal ends of the thin plates that are located at the middle of the seal segment in the circumferential direction.

Abstract: A sealing arrangement, for example for providing an intershaft seal between shafts of a gas turbine engine, includes an air-riding sealing ring disposed between runners. A buffer fluid, such as air, is conveyed to a buffer cavity through a passage in the sealing ring. The buffer air provides a positive pressure drop along fluid-riding gaps, preventing leakage across the sealing arrangement. The sealing ring may be a split carbon ring, and measures may be provided to minimise leakage of buffer air at the split.

Abstract: The present invention relates to circumferential seal ring segments positioned around a rotating shaft so as to prevent fluids from leaking from a lubricant sump during both low and high pressure conditions. The circumferential seal is comprised of a plurality of adjoining annular ring segments facing the rotating shaft. Each sealing ring segment includes a dead end circumferential groove on a shaft-side face of each sealing ring such that, when the segments are joined, the circumferential dead end groove of each segment extends arcuately in the direction of shaft rotation. At least one additional groove is contained on the shaft-side face of each sealing ring segment. Each additional groove is an axial bore groove extending perpendicularly to a longitudinal axis of the seal ring segment in fluid communication with the dead end circumferential groove so as to direct fluid flow generated from a rotating shaft into the dead end circumferential groove.

Abstract: A non-contact labyrinth seal assembly, bearing assembly therewith, and method of construction thereof, has an outer rigid carrier and an inner sleeve. The carrier has an outer cylindrical flange and a radially inwardly extending leg and the sleeve has a cylindrical wall and a radially outwardly extending flange. A body is attached to at least one of the leg and the flange, wherein the body provides, at least in part, a purely non-contact labyrinth passage extending between the carrier and the sleeve.

Abstract: The present invention relates to circumferential seal ring segments positioned around a rotating shaft so as to prevent fluids from leaking from a lubricant sump during both low and high pressure conditions. The circumferential seal is comprised of a plurality of adjoining annular ring segments facing the rotating shaft. Each sealing ring segment includes a dead end circumferential groove on a shaft-side face of each sealing ring such that, when the segments are joined, the circumferential dead end groove of each segment extends arcuately in the direction of shaft rotation. At least one additional groove is contained on the shaft-side face of each sealing ring segment. The additional groove(s) directs and creates pressurized air within the dead end circumferential groove, either directly or indirectly maintaining a seal between the ring segments and the shaft. A bleed hole may also be provided to create a seal between each sealing segment.

Abstract: A seal assembly for a turbo machine is provided. The turbo machine includes a rotary component and a stationary component. The seal assembly is disposed between the rotary component and the stationary component. The seal assembly is configured to provide a sealing between a high pressure area and a low pressure area of the turbo machine. The seal assembly includes a plurality of compliant plates coupled circumferentially along the stationary component. Each of the compliant plate includes a tip disposed facing the rotary component. A tip slot is provided on the tip of the compliant plates, wherein the tip slots is provided at the portion of the tip proximate the high pressure area. The compliant plates further include a plate slot extending from the stationary component towards the tip. An annular resistance member coupled to the stationary component is disposed in the plate slot in the compliant plates.

Abstract: A hydrodynamic non-contacting seal wherein the sealing surface of a rotatable sealing member is grooved in a spiral pattern such that the depth of the grooves decreases in a direction opposite to the direction of rotation of the rotatable sealing member.

Abstract: There is provided a shaft seal device comprising a seal piece-laminated body (12) where a plurality of thin seal pieces (20) are laminated in the circumferential direction along a rotating shaft, outer ends of the plurality of thin seal pieces in the radial direction are connected to each other, inner ends (20b) of the thin seal pieces in the radial direction are formed as free ends, a small gap (s) is formed at every two thin seal pieces adjacent to each other, and a small gap (s) is formed between the rotating shaft and the seal piece-laminated body (12). A wear-resistant treatment layer (25) is formed on the surface of a portion of the thin seal piece close to the inner end.

Abstract: The present application provides an aerodynamic seal assembly for use with a turbo-machine. The aerodynamic seal assembly may include a number of springs, a shoe connected to the springs, and a secondary seal positioned about the springs and the shoe.

Abstract: A sealing ring for sealing a rolling chamber of a rolling bearing, which has a supporting part that is fixed to a first bearing part and retains an elastic part. The sealing ring seals the roiling chamber by a radial or axial sealing lip on the elastic part. The sealing ring lies between the first bearing part and a second bearing part that is rotatable relative to the first bearing part or lies between the first bearing part and another component fixed to the second bearing part and moveable relative to the first bearing part. A ring of lubricant is applied, formed and retained by an annular groove in a sealing lip and by the second bearing part or by the component. The ring of lubricant can also be shaped so that the ring of lubricant closes a gap between the sealing lip and the second bearing part or the components.

Abstract: The invention relates to a seal with non-contact adjacent deflector rings, arranged concentrically to each other, about a common rotation axis, whereby, on a first deflector ring of the deflector rings, at least two axially-adjacent radial lips are embodied an said radial lips are embodied such as not to come into contact with a second deflector ring of the deflector rings and an annular hollow cavity is embodied between two axially-adjacent radial lips and the second deflector ring.

Abstract: A leaf seal device having a connection holding section of a sealing plate which is bent at a first bending section. A plurality of laminated sealing plates are engaged sequentially at the first bending section. An inclined face at an inner circumferential side of the connection holding section, a pitch and a space of a sealing section are changed.

Abstract: A seal comprises the combination of a primary seal and a secondary seal each of which acts on at least one shoe that is installed with clearance relative to one of a rotor and a stator in a position to create a non-contact seal therewith. The at least one shoe is provided with a surface geometry and labyrinth-type teeth that influence the inertia of fluid flowing across the seal, and, hence, the velocity of the fluid and the pressure distribution across the seal, ultimately affecting the balance of forces applied to the seal.