Abstract: A device configured to seal a circumferential gap between a first turbomachine component and a second turbomachine component mutually rotatable about a longitudinal axis. The device is provided with a first sealing element connected to the first turbomachine component and with a second scaling element having an inner part provided with a plurality of projections extending towards the second machine component to define the teeth of a labyrinth seal between the high pressure region and the low pressure region of the turbo machine. The outer part of the second sealing element is connected to the first sealing element through an clastic element. One or more pressure chambers located between the first sealing element and the second sealing element are in fluid communication with the processing fluid of the turbomachine to derive a force acting on the outer part of the second scaling element in the direction of gap closure.

Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

Abstract: In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90°.

Abstract: The present invention relates to a sealing member for a base station antenna and a base station antenna comprising the same as well as a method and device for manufacturing the sealing member. The sealing member (2) is flexible and resilient and is configured to form a seal between an open end (5) of a radome (3) and an end cap (1) of the base station antenna. The sealing member is an elongated sealing strip having two ends, wherein the two ends of the sealing member are lappable with each other, and the sealing member has a groove extending over its entire length, which groove is defined by two side limbs and a bottom limb connecting the two side limbs of the sealing member, wherein the groove is configured to engage with an edge of the open end (5) of the radome, and wherein the sealing member is configured to be received in an annular recess of the end cap (1) and isolate an interior of the radome (3) from the environment.

Abstract: A seal joint assembly is provided that includes a stationary seal carrier, a stationary seal land and a brush seal. The stationary seal land includes a seal land surface. The brush seal is mounted to the stationary seal carrier. The brush seal includes a first set of bristles and a second set of bristles. The first set of bristles includes a first bristle that contacts the seal land surface. The second set of bristles includes a second bristle that contacts the seal land surface. The second bristle crosses the first bristle.

Abstract: A shaft assembly for a gas turbine engine includes a shaft, a bearing, and an annular sump cover. The shaft is arranged along an axis and configured to rotate about the axis. The bearing is coupled to the shaft to facilitate rotation of the shaft about the axis. The annular sump cover is fixed relative to the axis and is configured to allow a lubrication fluid and a buffer air into an air chamber formed between the shaft, the bearing, and the annular sump cover.

Abstract: An assembly is provided for rotational equipment. This assembly includes a plurality of seal shoes, a seal base and a spring system. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the seal shoes. The spring system connects the seal shoes to the seal base. The spring system includes a first spring element and a second spring element. The first spring element extends axially along the centerline in a first axial direction from the seal base to the first seal shoe. The second spring element extends axially along the centerline in a second axial direction from the seal base to the first seal shoe. The second axial direction is opposite the first axial direction.

Abstract: A brush seal includes a first plate and a second plate. A plurality of bristles have a first end and a second end. The plurality of bristles are arranged between the first and second plates such that the first and second ends extend beyond the first and second plates. The first end is arranged at an angle relative to the second end.

Abstract: A component for a gas turbine engine includes a compartment housing that redirects oil from at least one passage in a rotational component onto a backside of a seal land.

Abstract: A sealing device includes a ring part, a first fin group that together with a first outer peripheral surface forms a clearance, and a second fin group of which the front end is positioned farther radially inward than the first outer peripheral surface and which together with a second outer peripheral surface forms a clearance. The ring part has a first gas supply channel capable of supplying a first sealing gas to the first fin group, a second gas supply channel capable of supplying a second sealing gas to the second fin group, and a mixed gas discharge channel capable of discharging a mixed gas of the first sealing gas and the second sealing gas from between the first fin group and the second fin group.

Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components is provided. The seal includes a seal housing. The seal also includes a shoe extending axially from a forward end to an aft end to define an axial length, the shoe cantilevered to the seal housing at one of the forward end and the aft end, the shoe free at the other end.

Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.

Abstract: A gas turbine engine, having: a disk; a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk; a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades; and a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.

Abstract: A bearing isolator seal provides enhanced coupling and stability of the rotor to the shaft, without undue seal enlargement, by including a plurality of drive O-rings in a common retention groove. In embodiments, the isolator seal accommodates axial rotor misalignment up to a maximum permitted axial misalignment, which can be at least 0.025?. Embodiments include a labyrinth passage between the rotor and the stator configured to expel fluid by centrifugal force. Embodiments include a shut off feature that takes advantage of axial misalignment. Some embodiments include a unitization feature that holds the rotor and stator together during assembly. The unitization feature can include chamfers on rotor and stator extensions that facilitate assembly and disassembly when sufficient force is applied.

Abstract: A bearing isolator seal having a shut off O-ring is tolerant of axial rotor-stator misalignment and provides an enhanced static seal while minimizing rotational wear. A tapered section of the stator is overlapped by the shut off O-ring. When the rotor is static there is no axial misalignment, and the shut off O-ring is pressed against the tapered section, forming an enhanced seal. During rotor rotation, increased axial misalignment moves the O-ring away from the tapered section, reducing rotational wear. The stator can extend horizontally beyond the tapered section and below the O-ring, so that if the rotor moves beyond a maximum misalignment, there is a “line on line” fit between the stator and rotor. The bearing isolator seal can include labyrinth technology, and the tapered section can include a contour that allows the shutoff O-ring to drag along the surface of the tapered section with no hang-ups or binding.

Abstract: A seal for a rotary machine includes a flexible element extending circumferentially about a rotor and extending generally radially from a first end to a free second end. The flexible element is coupled proximate the first end for rotation with the rotor. The flexible element extends at substantially a first angle between at least an intermediate portion of the flexible element and the free second end when the rotor is operating at less than a critical speed, such that a clearance gap is defined between the free second end and a stationary portion. The seal also includes a retaining plate having a stop that orients the flexible element at a second angle proximate the free second end when the rotor is operating at equal to or greater than the critical speed, such that the flexible element forms a dynamic seal between the rotor and the stationary portion.

Abstract: A brush seal land is disclosed. The brush seal land may comprise a first portion configured to be coupled to a turbine disc of an aircraft engine and a second portion having a contact surface. The brush seal land may comprise a concave annular structure. The second portion may deflect through a clearance area in response to contact with a brush. The second portion may not deflect in response to contact with a brush after the second portion has deflected through a clearance area in response to contact with the brush. The contact surface comprises tungsten carbide. The brush seal land may comprise INCONEL. The brush seal land may be configured to be coupled to an annular member extending from the turbine disc. The brush seal land may reduce abrasion to an annular member extending from the turbine disc by a brush.

Abstract: Described is a brush seal for sealing between a first component and a second component which relatively rotate during normal use, comprising: an annular housing which is attached to a first component in use; a plurality of bristles each having a fixed end attached to the housing and a free end, wherein the free ends of at least some of the plurality of bristles contact the second component during normal use to provide a sealing surface, wherein the sealing surface includes a plurality of discontinuities around the circumference of the brush seal for providing hydrodynamic lifting force in use.

Abstract: A fluid delivery assembly for delivering fluid to a component in a gas turbine engine includes a rotating shaft having a central bore and at least one fluid exhaust in communication with the central bore for centrifugally expelling fluid, and a delivery scoop disposed around the rotating shaft and spaced apart from the rotating shaft by an annular gap. The delivery scoop includes an annular body having at least one impingement surface facing the at least one fluid exhaust and configured to scoop the fluid expelled by the at least one fluid exhaust. The impingement surface has at least one outlet for delivering the scooped fluid to the component. A method of delivering pressurised fluid in a fluid system is also presented.

Abstract: A steam turbine is provided. The steam turbine includes a housing and a steam inlet configured to discharge a primary steam flow within the housing. A stator is coupled to the housing and a rotor is coupled to the housing and located within the stator. The rotor and the stator are configured to define a primary flow path there between and in flow communication with the primary steam flow. The steam turbine includes a seal assembly coupled to the housing. The seal assembly includes a packing head and a plurality of seals. The packing head is configured to define a cooling flow path in flow communication with the rotor and configured to discharge a cooling steam flow toward the rotor. An anti-swirl device is coupled to the seal assembly and located between the rotor and the packing head.

Abstract: A rotary shaft and a seal mechanism are provided. The rotary shaft extends into outside air outside a case via a shaft hole provided in the case of a drive system. The seal mechanism prevents entry of foreign matter from the outside air into the shaft hole. The case includes a canopy portion and a recessed portion. The recessed portion is recessed coaxially with the canopy portion from an end face of the canopy portion in the direction of the axis. The seal mechanism includes a deflector and a seal member. The deflector is fixed to the rotary shaft in a liquid-tight manner, and extends into the recessed portion. The seal member is an elastic body. The seal member is fixed in the shaft hole in a liquid-tight manner, and is in sliding contact in a liquid-tight manner with the rotary shaft and the deflector.

Abstract: A brush seal is provided having a brush housing having a back plate and a front plate, a first layer of bristles disposed adjacent to the back plate, where at least one of the first layer of bristles has a first diameter. A second layer of bristles are disposed adjacent to the first layer of bristles, and at least one of the second layer of bristles has a second diameter. A third layer of bristles are disposed adjacent to the second layer of bristles, and at least one of the third layer of bristles has a third diameter. The first diameter and the third diameter are larger than the second diameter.

Abstract: Sealing apparatus and engine are provided. A sealing apparatus includes a first cover plate, a second cover plate spaced apart from the first cover plate, and a sealing element disposed between the first cover plate and the second cover plate and including at least two diaphragm members, wherein a first diaphragm member has a first stiffness and a second diaphragm member has a second stiffness that is different than the first stiffness. The sealing apparatus may be disposed in an engine.

Abstract: A compliant plate seal assembly for a turbo machine includes a rotor and a stationary component. A plurality of compliant plates are coupled circumferentially to the stationary component. A natural frequency of each compliant plate varies from a natural frequency of adjacent compliant plates and/or gaps between adjacent plates to produce a zero-oscillation state between adjacent compliant plates in flow.

Abstract: A brush ring seal device for installation within a packing case of a turbine includes: a brush seal carrier having a substantially ring-shaped body portion having a front face, a rear face, an inner circumferential groove, and an outer circumferential groove; a brush seal mounted within the inner circumferential groove of the brush seal carrier; and a ring-shaped spring mounted within the outer circumferential groove of the brush seal carrier. The rear face of the brush seal carrier is coated with an anti-friction coating, thereby allowing movement of the brush ring seal device within the packing case.

Abstract: A partial seal platform for mounting a seal and securing seal to a rotor or a casing including a first arcuate securing segment with a first securing notch for receiving a first securing ridge of rotor or casing; a second arcuate securing segment with a second securing notch for receiving a second securing ridge of rotor or casing; an arcuate coupling segment with a first flat ridge forming a first and second lateral notch on each side of the first flat ridge for receiving the first arcuate securing segment and the second arcuate securing segment; and an arcuate mounting segment including a second flat ridge forming a lateral notch on each side of second flat ridge for receiving first arcuate securing segment and second arcuate securing segment.

Abstract: The system and method for preventing air leakage from the process side to the bearing side of a mill. The system includes a labyrinth seal ring comprising a series of knives defining first and second labyrinth paths from an air inlet to the process side and the bearing side of the system, respectively. The differences in the two paths such as provided by the number of knives used in each path creates a differential pressure drop which biases air from the air inlet to the process side. The labyrinth seal thus provides a reliable and superior method for reducing the potential for particulate in the process side of the mill from damaging the bearing system.

Abstract: An adjustable seal and method for varying a radial distance between the adjustable seal and a rotor of a turbomachine are provided. The adjustable seal may include a first annular member defining a plurality of radial channels, and a second annular member defining a plurality of slots at least partially extending therethrough. The second annular member may be concentric with the first annular member and configured to rotate relative to the first annular member. The adjustable seal may also include a plurality of seal segments interposed between the first annular member and the second annular member. Each seal segment of the plurality of seal segments may be slidably disposed in a respective radial channel of the plurality of radial channels and may have an axial projection slidably disposed in a respective slot of the plurality of slots.

Abstract: An inter-stage seal for a turbomachine includes a sealing member extending from a first end to a second end through an intermediate portion having a sealing surface, a first mounting member extending from a first end portion coupled to the sealing member adjacent the first end to a second, cantilevered end portion having a first rotor mounting element, and a second mounting member extending from a first end portion coupled to the sealing member adjacent the second end to a second, cantilevered end portion having a second rotor mounting element.

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: Embodiments of the present disclosure are directed towards a seal assembly including a first seal and a second seal, wherein the first seal and the second seal axially abut one another within a retaining bore of a compressor, and cooperatively form an outer radial contour of the seal assembly that is retained by the retaining bore.

Abstract: A sealing system for process gas leakage from a turbomachine casing is provided. The sealing system may include a seal assembly housing coupled to or integral with the turbomachine casing. The seal assembly housing defines a bore configured to receive a rotary shaft and a sealing assembly. The sealing assembly includes a plurality of carbon rings mounted circumferentially about the rotary shaft. The plurality of carbon rings may include an inboard carbon ring configured to prevent flow of a separation gas inboard of the barrier seal, an outboard carbon ring configured to prevent flow of contaminates into the seal assembly housing, and an intermediate carbon ring interposed between the inboard carbon ring and outboard carbon ring. A pressure differential is maintained across the inboard carbon ring, such that the separation gas is prevented from flowing inboard across the inboard carbon ring by a residual portion of a seal gas.

Abstract: A leaf seal assembly (20) for providing a seal between a first member and a second member (10), the leaf seal assembly comprising a plurality of leaf elements (22) and a first substantially planar cover plate (24a), the leaf elements being arranged in a pack, with a first edge of each leaf element being adjacent to the first cover plate, wherein each leaf element comprises a first shoulder (30a) in the first edge, the first shoulder being arranged so as to form a first gap (28a) between the first edge of each leaf element and the first cover plate over a portion of the first edge.

Abstract: A dry seal apparatus (30) for a machine (10) includes a seal having a stationary portion (40) and a rotating portion (38); a space (44) disposed between the stationary and rotating portions; a biasing member (42) disposed proximate the stationary portion (40) and in contact therewith for applying a force to the stationary portion; and a labyrinth (37) proximate the rotating portion (38) and constructed and arranged for receiving a liquid for being vaporized before entering the space between the stationary and rotating portions of the seal. A related method is also provided.

Abstract: A centrifugal turbomachine comprising a casing, a rotor assembly comprising at least one centrifugal impeller for a fluid flowing from an inlet side to an outlet side of the impeller, and an eye seal extending between an impeller eye of the centrifugal impeller and the casing for preventing the fluid from leaking between the casing and the centrifugal impeller, wherein the eye seal comprises at least a first portion toward the inlet side and a last portion toward the outlet side of the impeller, the last portion being smaller in diameter than the first portion.

Abstract: According to one embodiment of the invention, a gerotor apparatus includes a first gerotor, a second gerotor, and a synchronizing system operable to synchronize a rotation of the first gerotor with a rotation of the second gerotor. The synchronizing system includes a earn plate coupled to the first gerotor, wherein the cam plate includes a plurality of cams, and an alignment plate coupled to the second gerotor. The alignment plate includes at least one alignment member, wherein the plurality of cams and the at least one alignment member interact to synchronize a rotation of the first gerotor with a rotation of the second gerotor.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward-shoe section and an aft-shoe section having one or more labyrinth teeth therebetween facing the rotor. The sealing device includes a stator interface element having a groove or slot for allowing disposal of a spline seal for preventing segment leakages. The sealing device segment also includes multiple bellow springs or flexures connected to the shoe plate and to the stator interface element. Further, the sealing device segments include a secondary seal integrated with the stator interface element at one end and positioned about the multiple bellow springs or flexures and the shoe plate at the other end.

Abstract: A seal (48) between a compressor rotor blade (26) and compressor casing (28) comprises an abradable structure (59) on the compressor casing (28). The abradable structure (59) comprises a metallic foam (60) having pores (66, 68). The metallic foam (60) has a first a region (62) and a second region (64). The first region (62) of the metallic foam (60) is arranged adjacent to the compressor casing (28) and the second region (64) of the metallic foam (60) is spaced from the compressor casing (28) by the first region (62) of the metallic foam (60). The pores (68) of the second region (64) of the metallic foam (60) contain an abradable material (70) and the pores (66) of the first region (62) of the metallic foam (60) do not contain an abradable material.

Abstract: An aerodynamic seal assembly for a rotary machine is provided. The assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward-shoe section and an aft-shoe section having multiple labyrinth teeth therebetween facing the rotor. The shoe plate is configured to allow a high pressure fluid to a front portion of the plurality of the labyrinth teeth and a low pressure fluid behind the plurality of the labyrinth teeth and further configured to generate an aerodynamic force between the shoe plate and the rotor. The sealing device segment also includes multiple bellow springs or flexures connected to the shoe plate and to a top interface element, wherein the multiple bellow springs or flexures are configured to allow the high pressure fluid to occupy a forward cavity and the low pressure fluid to occupy an aft cavity.

Abstract: A screw fluid machine has a first non-contact seal, a second non-contact seal and a lip seal disposed between a rotor chamber and a bearing for a rotor shaft located on the high pressure side, and in this order from the rotor chamber side. It includes a pressurized communicating channel for introducing high-pressure target gas into a pressurized space formed between the first and second non-contact seals, a pressurized pressure detecting device for detecting the pressure of the pressurized space, and an alarm device for generating an alarm when a value detected by the pressurized pressure detecting device falls out of a predefined range of pressurized pressures. The screw fluid machine is capable of detecting or predicting a condition of the shaft sealing device and accurately and reliably reporting the detected condition to an operator.

Abstract: A water-lubrication type screw fluid machine has a first non-contact seal, a second non-contact seal and a lip seal disposed between a rotor chamber and a bearing for a rotor shaft. The bearing is located on the high pressure side and in this order from the rotor chamber side. the bearing includes a low pressure communicating channel for allowing an outflow space formed on the rotor chamber side with respect to the first non-contact seal to communicate with a low pressure channel for the target gas communicating with a low pressure space inside the rotor chamber or the rotor chamber, a pressurized communicating channel for introducing high-pressure target gas into a pressurized space formed between the first and second non-contact seals, and an open communicating channel through which an open space formed between the second non-contact seal and the lip seal opens to the outside of the casing.

Abstract: A non-contacting shaft seal apparatus according to which an alternating array of axially-spaced, porous and non-porous annular segments extend radially-inward from the inside surface of an annular seal body and to a radial clearance defined between the segments and a rotating shaft.

Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.

Abstract: A housing of a Roots pump is configured by joining a lower housing member and an upper housing member that are separable from each other. With the upper and lower housing members joined together, an upper accommodating portion and a lower accommodating portion form a front bearing accommodating portion and a rear bearing accommodating portion, which accommodate whole bearings, respectively. The Roots pump further includes bearing holders attached to the bearings and fixed to the lower housing member so that the bearings are received in the lower accommodating portion in a positioned state.

Abstract: A labyrinth seal for a bypass discharge-type motor-fan unit includes a motor unit from which extends a rotating shaft that passes through an aperture in an end plate to drive a fan unit. Disposed within the aperture is a labyrinth seal configured to prevent liquid entrained in a working airflow from entering the motor unit. The rotating shaft also includes a vacuum bore, such that the negative pressure generated by the operation of the fan unit draws any liquid out of an evacuation zone maintained between the motor unit and the end plate. As such, the components of the motor unit are protected from being exposed to the liquid, thereby extending the operating life motor-fan unit.

Abstract: An actuator comprising a first part and a second part, the first part being configured to move relative to the second part, wherein a labyrinth seal is provided between the first part and the second part, the labyrinth seal being configured to restrict the flow of gas from a first side of the labyrinth seal to a second side of the labyrinth seal, wherein one or more inlets and one or more outlets are provided within the labyrinth seal, the one or more inlets being configured to provide gas to a location within the labyrinth seal and the one or more outlets being configured to remove at least part of the gas from a location within the labyrinth seal.

Abstract: A method for assembling a rotary machine is provided. The method includes providing at least one seal assembly that includes at least one annular seal housing defined by a top wall, a front wall, and a rear wall, that are connected together such that a cavity is defined within the housing, coupling a plurality of flexible plates within the cavity such that the plates are axially-spaced from the front wall and the rear wall within the cavity, coupling at least one side plate to the at least one annular seal housing such that the at least one side plate is moveable with respect the front wall and the rear wall, and coupling the at least one sealing assembly within a rotary machine to facilitate sealing between a rotary component and a stator component.

Abstract: A seal assembly includes a first component, a second component that defines an outer surface and is located radially inward from the first component, a groove defined in the second component and arranged to face the first component, and a seal ring positioned between the first and second components and extending at least partially into the groove. The seal ring defines an outer diameter surface and a first lateral surface adjoining the outer diameter surface. The seal ring is split to define a first free end and a second free end, and the first and second free ends are configured to overlap along a split surface that extends from the first lateral surface to the outer diameter surface.

Abstract: Disclosed is a seal for a turbomachine including at least one fixed component located proximate to a rotating component of the turbomachine defining a clearance therebetween. At least one magnet is located at the at least one fixed component. The at least one magnet is, when activated, capable of moving the at least one fixed component thereby adjusting the clearance between the fixed component and the rotating component. Further disclosed is a turbomachine utilizing the seal and a method for adjusting a position of at least one fixed component of a turbomachine.

Abstract: A seal assembly for a turbomachine includes a plurality of compliant plate members attached to an interior surface of a stationary housing. The compliant plate members define a sealing ring between the stationary housing and a rotor. Each of the compliant plate members comprises at least one slot therein. The seal assembly further includes at least one arcuate static ring attached to the interior surface of the stationary housing and extending radially into the at least one slot in the compliant plate members. Each of the at least one static ring extends circumferentially through and between a plurality of the compliant plate members. Finally, the seal assembly includes a vibration damper disposed adjacent to or provided on the plurality of compliant plate members. The vibration damper is configured to dampen vibration of the plurality of compliant plate members.