Abstract: A labyrinth seal, has: rotating and static components rotatable relative to one another relative to a central axis, the rotating component securable to a shaft via a tight fit engagement at an engagement location on the rotating component, the static component securable to a housing; teeth protruding from one of the rotating and static components towards a seal land defined by the other one of the rotating and static components; and clearances between the teeth and the seal land, a first clearance of the clearances greater than a second clearance of the clearances, the first clearance located closer to the engagement location of the rotating component than the second clearance.

Abstract: A labyrinth sealing device for reducing gas intrusion is provided. A sealing bush is provided with a jet hole at the front of a tooth tip gap. The jet hole faces a tip of a corresponding sealing tooth. A gas flow injected by the jet hole suppresses hot gas flowing into the tooth tip gap. The sealing bush is provided with a first intercepting member at the rear of the tooth tip gap, and the sealing tooth is provided with a second intercepting member at the rear of the tooth tip gap. The first intercepting member hinders hot gas flowing against an inner wall of the sealing bush, and the second intercepting member hinders hot gas flowing against the sealing tooth, such that a part of the hot gas flows in a reverse direction and is violently mixed with subsequent hot gas.

Abstract: A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

Abstract: A steam turbine includes a rotary shaft configured to rotate about an axis, a rotor blade including a rotor blade body extending radially outward from the rotary shaft, and a shroud on an end outside in a radial direction, a casing enclosing the rotor blade from outside in the radial direction and including a cavity accommodating the shroud on an inner circumference of the casing, a plurality of seal fins protruding radially inward from an opposing surface that faces the shroud in the cavity such that a clearance is between an outer circumferential surface of the shroud and the plurality of seal fins, and a plurality of swirl breaks upstream of the plurality of seal fins located furthest upstream in a direction of the axis in the cavity, the plurality of swirl breaks being arranged at intervals in a circumferential direction.

Abstract: A seal includes a seal runner, at least one seal ring, and a seal housing. The runner extends in an axial direction to a runner end face that faces a bearing. The ring is fixed to a static structure and has an inner surface engaging the seal runner and a first face that faces the bearing. The seal housing is fixed to the static structure and includes a first portion extending in an axial direction from the first face of the seal ring to a housing face that faces the bearing. The first portion has a first length extending from the first face of the seal ring to the housing face. The seal runner has a first runner portion with a second length that extends from the first face of the seal ring to the runner end face. The second length is at least 35% longer than the first length.

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

Abstract: There are provided a seal fin, a seal structure, a turbo machine, and a method for manufacturing a seal fin. The seal fin suppresses leak of a fluid from a gap between a first and a second structures facing each other in a radius direction, and is formed on the first structure while keeping a clearance with respect to the second structure. The seal fin includes: a fin main body extending in the radius direction; and a protrusion being formed between a front face of the fin main body and a tip face and protruding toward an upstream side. A length of the protrusion is 1.5 times a length of the fin main body or less; an angle of the protrusion is 75 degrees or less; and a tilt angle of the fin main body is set in a range of ?60 degrees or more and 60 degrees or less.

Abstract: A labyrinth seal includes a step portion formed on an outer circumferential portion of a rotary body, a fin extending radially inward from an inner circumferential portion of a stationary body, and an annular groove formed in the outer circumferential portion of the rotary body. The step portion includes a diameter-increasing step portion and a diameter-decreasing step portion. The fin includes a first fin, a second fin, and a third fin. The annular groove is disposed in at least a part of a region that is located close to the low-pressure side compared to the high-pressure-side step portion and close to the high-pressure side compared to the third fin.

Abstract: Disclosed herein is a structure for multi-stage sealing of a turbine, including: an annular multi-stage sealing part disposed on an inner circumferential surface of a fixed body and having different heights of at least two stages; a barrier unit disposed at a central side of the multi-stage sealing part on the inner circumferential surface of the fixed body; and an annular multi-stage tooth part disposed to face the multi-stage sealing part or the barrier unit over an outer circumferential surface of a rotating body and provided with a plurality of teeth, having a relative height corresponding to different heights of the multi-stage sealing part or the barrier unit at an interval between the fixed body and the rotating body.

Abstract: A labyrinth seal suppresses leakage of fluid through a gap between a circumferential outer surface of a rotating body, having an axis of rotation, and a circumferential inner surface of a stationary body provided on an outer side of the rotating body, by increasing fluid energy loss caused by vortices. Said leakage occurs in an axial direction from a high pressure to a low pressure side. A step is formed on the outer surface such that the diameter of the low pressure side is smaller than that of the high pressure side. A fin extending radially inward from the inner surface is formed on at least the low pressure side of the step. An annular groove is formed to extend in a circumferential direction in the outer surface, in at least one portion of the area axially between the step and the fin.

Abstract: A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees.

Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.

Abstract: A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter.

Abstract: A rotary machine includes a casing that is disposed on the outer circumference side of a rotating shaft and rotates about the axis relative to the rotating shaft, and a hole pattern seal that is fixed to the casing, divides a space between the rotating shaft and the casing into a high pressure side and a low pressure side, and has a first hole line on which a plurality of first hole portions are formed at intervals in a circumferential direction so as to face an outer circumferential surface of the rotating shaft. The hole pattern seal has fin portions that extend toward the rotating shaft at the high-pressure side of the first hole line and in the circumferential direction. The rotating shaft includes a convex portion that protrude from the outer circumferential surface of the rotating shaft toward the first hole portions to extend in the circumferential direction, and face the first hole portions at the low pressure side of the fin portion. The convex portion has a wall surface facing the fin portions.

Abstract: A steam turbine through which a fluid flows along an axis is equipped with: a tip shroud for turbine blades that are provided on a shaft that extends with the axis as a center; an outer partition plate ring that is provided on a casing so as to face the tip shroud in a radial direction and be capable of rotating relative to the tip shroud around the axis; seal fins that extend radially inward from the outer partition plate ring and that, with the tip shroud, form minute gaps therebetween; and steam introduction surfaces that are formed on downstream sides of the seal fins and are provided so as to face the seal fins within cavities where a main vortex, generated from a leakage flow passing through a minute gap, is generated, and that guide the flow, generated from the main vortex, toward the minute gaps.

Abstract: A plurality of stepped parts which have step surfaces facing an upstream side in a rotating axial direction of a structural member are provided in a tip portion of a blade, and seal fins which extend toward a circumference surface of each of the stepped parts and form small clearances between the seal fin and the circumference surface corresponding to the each of the stepped parts is provided in the structural member. Also, lengths from the small clearance to the step surface on the upstream side along the rotating axial direction of the structural member are set such that one of the stepped parts on the downstream side is smaller than the other one of the stepped parts on the upstream side.

Abstract: The disclosure includes a sealing assembly for a turbine system. In one embodiment, the sealing assembly is for a turbine having a rotor blade and a stator nozzle. The sealing assembly includes a pair of oppositely facing seal teeth including concave surfaces. The pair of oppositely facing seal teeth are positioned on one of the rotor blade and the stator nozzle, and are for sealingly engaging the other of the rotor blade and the stator nozzle during operation of the turbine.

Abstract: A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow.

Abstract: A seal assembly includes a first component and a second component of a gas turbine engine. The first component has a threaded portion. The second component interfaces with the threaded portion and together the threaded portion and the second component form a seal that restricts fluid flow between a first cavity and a second cavity of the gas turbine engine.

Abstract: A seal assembly for sealing a stationary component and a rotating component including a seal tooth mating surface for mating with a seal tooth, the seal tooth mating surface including a plateau portion for sealingly receiving the seal tooth during a steady-state operation of the seal assembly and a first concave portion adjacent to the plateau portion for receiving the seal tooth with a clearance during a first non-steady-state operation of the seal assembly, wherein the seal tooth is coupled to one of the stationary component and the rotating component and the seal tooth mating surface is coupled to the other of the stationary component and the rotating component.

Abstract: The disclosure describes a windback device for a circumferential seal within a turbine engine. The windback device includes an annular collar at one end of an annular fluid seal housing, at least one inclined thread, and a plurality of inclined baffles separately disposed along an outer circumferential surface of a rotatable runner. The housing is adapted at another end for an annular seal. The collar has an opening therethrough sized to receive the runner without contact. The annular seal surrounds and sealingly engages the runner. The threads extend from an inner face of the collar toward the runner. The baffles are separately recessed in or raised above the outer circumferential surface of the runner. The baffles are interposed between the runner and threads. Each baffle is separated from the threads via a radial clearance. Threads and baffles direct lubricant away from the annular seal.

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: According to one embodiment of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

Abstract: A seal for use in a machine, such as a machine with rotating members, includes a labyrinth seal with multiple fins. The seal is slotted and is designed to limit fluid flow to the desired amount from the high pressure side of the seal to the low pressure side of the seal inside partially or exclusively radially extending cavities between two rotating members. The rotating members may operate at different speeds with a common axis of rotation. The seal remains effective when the rotating members move axially in relation to one another despite the fins having a component parallel to the axis of rotation.

Abstract: A non-contact labyrinth seal assembly includes a carrier having cylindrical outer flange with an annular leg extending inwardly therefrom. An elastomeric body is attached to the leg. The body has a first pair of seal lips extending radially inwardly in diverging relation from one another and a second pair of seal lips spaced radially outwardly from the first pair of seal lips. The second pair of seal lips includes radially outermost and a radially innermost seal lips. The radially outermost seal lip has a cylindrical inner surface and an inner surface of the radially innermost seal lip has a first portion extending substantially parallel to the cylindrical inner surface to form an annular channel and a second portion extending radially outwardly to an innermost lip free end that is radially aligned with the cylindrical inner surface to form an annular opening having a width less than a width of the channel.

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: An illustrative embodiment of porous media shaft seal assembly may include a stator and a rotor. The rotor may be configured to rotate with a shaft, and the stator may be engaged with a housing. Porous media may be applied and/or engaged with a portion of the stator, and a seal fluid may be communicated to the porous media. A biasing member may be employed to urge a portion of the rotor toward a portion of the stator, and seal fluid exiting the porous media may counteract the force of the biasing member.

Abstract: According to an aspect of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

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 seal device including: three ring-shaped first vertical wall portions (21) which extend toward a rotational body (12) from a stationary body (11) and are arranged at predetermined intervals in an axial center direction (A) of the rotational body (12); a ring-shaped second vertical wall portion (22) which extends toward the rotational body (12) from the stationary body (11) and is adjacent to the first vertical wall portions (21), the thickness of which is thicker than the first vertical wall portions (21); a ring-shaped protrusion portion (23) which faces the second vertical wall portion (22) and protrudes toward the stationary body (11) from the rotational body (12); and a plurality of swirl breaker chambers (24) which are arranged in the stationary body (11) at predetermined intervals in a circumferential direction of the rotational body (12) to face the protrusion portion (23).

Abstract: In a system for contactlessly sealing a rotably mounted shaft from a housing, and a gear unit, oil is provided in the interior of the housing, the rotating shaft in particular projecting from the interior to the outer area, wherein a centrifugal disk is provided, which is connected to the shaft in torsionally fixed manner and has at least partially radially extending bores, which connect oil from a centrifugal chamber to a catch basin surrounding the centrifugal disk.

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: 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: A shaft seal structure capable of preventing a seal body of the shaft seal structure of a rotation body from being held in an inclined posture even when the seal body is inclined is provided. It includes, an accommodation body (9), a seal body (12) including thin plate seal pieces (20), and a plate body (17) covering one end in the axial direction (20d) of the seal body (12). A recessed portion (31) recessing in the axis direction, and a protruding portion projecting to the other side from the recessed portion (31) are formed on one of the plate surface (17c) of the plate body (17) and the inner wall surface (9e) of the accommodation body (9). When the protruding portion abuts the other side and a pocket (X), the recessed portion (31) communicates with the pocket (X) and the fluid low pressure region.

Abstract: An arrangement (30, 80) for sealing a shaft (40, 60, 90, 110) in a casing (31, 81) by a hydraulic seal (50, 70, 100, 120) includes at least one essentially annular, radially inwardly open cavity (51, 71, 101, 121) and at least one essentially annular, radially outwardly directed sealing element (54, 74, 102, 122) which projects into the cavity (51, 71, 101, 121). To provide a hydraulic shaft seal, in which swirl and friction losses in the sealing medium are low and no leakage occurs, the hydraulic seal (50, 70, 100, 120) is arranged on the inner side (42, 62, 92) or on the outer side (111) of the shaft (40, 60, 90, 110) and the cavity (51, 71, 101, 121) or the sealing element (54, 74, 102, 122) of the hydraulic seal (50, 70, 100, 120) is connected to a wall (32, 82) of the casing (31, 81).

Abstract: A method and systems for a purged seal for an annular space are provided. The purged seal includes a first baffle element that extends from an inner surface of the annular space into the annular space at an oblique angle and a second baffle element that extends from an outer surface of the annular space above the first baffle element in a direction opposite gravity flow into the annular space wherein the second baffle element extends at an oblique angle. The system also includes a third baffle element that extends from the inner surface above the first baffle element in a direction of gravity flow into the annular space wherein the third baffle element extends into the annular space at an oblique angle with respect to the inner surface and wherein a distal end of the third baffle element is positioned proximate a distal end of the second baffle element.

Abstract: An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.

Abstract: A seal ring for a rotatable shaft in a turbo machine includes a seal body configured for disposing around the shaft wherein a radial gap is defined between an inner surface of the seal body and the shaft. An upstream surface defined by the seal body extends from the inner surface, and an annular obstruction extends from the upstream surface of the seal body, wherein the obstruction is spaced away from the inner surface.

Abstract: A labyrinth sealing ring for a labyrinth seal of a turbine disk 1 of a gas turbine includes a metallic annular element 3 with at least one annular sealing lip 4. The sealing lip 4 is provided with at least one groove 5 on its circumference which is essentially arranged in the radial direction.

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: In one embodiment, a packing seal has a plurality of lands that align with annular teeth. Each land has opposite axial sides relative to a rotational axis of a rotary component. Each land also has a recess in at least one of the opposite sides.

Abstract: A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.

Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.

Abstract: An improved staggered seal assembly uses a static element and a rotating element to create a seal. The static element surrounds the rotating element and has at least one fin. The rotating element has at least one long fin and a set of shorter fins. A third component has a staggered fin. The fins create a leakage flow path which throttles the leakage across the seal from a high pressure zone into a low pressure zone.

Abstract: According to one embodiment of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

Abstract: A main spindle device includes: a housing having an air supply passage; a spindle that is inserted into the housing and supported by a bearing so as to be able to rotate relative to the housing; and an air sealing member that is positioned between an outer circumferential surface of the spindle and the housing on a front side with respect to the bearing along a rotation axis of the spindle, has a substantially annular shape, and is detachably fixed to the housing with an inner circumferential surface of the air sealing member facing the outer circumferential surface of the spindle, wherein air supplied from the air supply source through the air supply passage is discharged into a gap between the outer circumferential surface of the spindle and the housing, thereby effecting non-contact air sealing at least between the inner circumferential surface of the air sealing member and the outer circumferential surface of the spindle.

Abstract: A seal assembly for a turbomachine may include at least one arcuate plate coupled to an interior surface of a stationary housing; a circumferentially-segmented packing ring disposed intermediate to a rotor and the plate; a plurality of arcuate teeth disposed intermediate to the ring and the rotor, wherein a clearance of each tooth decreases progressively going from an upstream side of the turbomachinery to a downstream side; wherein the progressive decrease in the clearances of the teeth creates a passive feedback, such that as a tip clearance decreases, outward radial forces cause the packing ring to move away from the rotor and as the tip clearance increases, inward radial forces cause the packing ring to move toward the rotor; and a biasing member disposed intermediate to the arcuate plate and the ring and coupled to both.

Abstract: A stepped labyrinth seal having a plurality of teeth forming gaps between a stationary honeycomb member, where the cavities formed between adjacent teeth include a plurality of vortex flow generating strips on the wall of the cavity that redirect the leakage flow from a gap back toward the gap and in a direction toward the gap in order to limit the leakage flow through the gap. The vortex generating strips extend along the cavity floor and up the sides of the teeth forming the cavity. The strips slope downward from the downstream tooth toward the upstream tooth in the direction of rotation, and with a curvature in the direction of rotation. The stepped labyrinth seal is intended for use in a gas turbine engine having a plurality of stages in the turbine, with the labyrinth seal being used to seal the gap between rotating blades and the honeycomb surface on the stationary casing.

Abstract: A seal in a turbine engine for preventing axial leakage through a radial gap between a stationary structure and a rotating structure, wherein the radial gap is defined by an inner radial surface that opposes an outer radial surface across the radial gap, the seal including: a first groove disposed on one of the inner radial surface and the outer radial surface; and a first tooth that projects radially from the other of the inner radial surface and the outer radial surface; wherein the first groove, at an upstream end, comprises a gradual slope that slopes away from the surface on which the first tooth is located and, at a downstream end, comprises a steep slope; and wherein the first tooth comprises an axial position that is approximately just upstream of the axial position of the upstream end of the groove.