Abstract: An assembly is provided for rotational equipment. The assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged around an axis in an annular array. The seal shoes include a first seal shoe. The seal base circumscribes the annular array of seal shoes. The spring elements include a first spring element. The first spring element is radially between and connects the first seal shoe and the seal base. The first seal shoe extends circumferentially about the axis between a first end and a second end. The first seal shoe extends radially between an inner side and an outer side. The first seal shoe is configured with a chamfered corner at an interface between the first end and the inner side.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces and at least one rail extending outwardly from the seal body. The seal body has a seal face that bounds a gas path. At least one rail aperture is defined at least partially through the at least one rail. At least one wear liner has a liner body. The liner body defines a liner aperture and an outer periphery that mates with the at least one rail aperture. A seal support is mountable to an engine case. The seal support has at least one support hook that mates with the liner aperture to mount the seal to the seal support. A method of assembly for a gas turbine engine is also disclosed.

Abstract: A seal according to the present disclosure includes a plate, and a floating shoe supported with respect to the plate in a first direction. The floating shoe has a sealing feature extending in a second direction perpendicular to the first direction. At least one bearing is between the plate and the floating shoe. The bearing is configured to facilitate movement of the floating shoe with respect to the plate in the second direction. A gas turbine engine including the seal and a method of sealing a rotating component with respect to a stationary component are also disclosed.

Abstract: A hydrostatic seal assembly for a gas turbine engine includes a shoe movable radially relative to a longitudinal engine axis. At least one beam supports radial movement of the shoe. A secondary seal is fixed relative to the shoe. A rail is attached to the shoe and in sealing engagement with the secondary seal. A gas turbine engine and a method of creating a seal with a hydrostatic seal are also disclosed.

Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.

Abstract: A seal assembly includes first and second rings. The first ring includes a first outer ring, a first beam connected to the first outer ring, and a first shoe. The first shoe includes free and fixed ends and is configured to move radially. The second seal ring is disposed axially adjacent and is attached to the first seal ring. The second seal ring includes a second outer ring, a second beam connected to the second outer ring, and a second shoe. The second shoe includes free and fixed ends and is configured to move in a generally radial direction. The free end of the second shoe is disposed axially adjacent to the fixed end of the first shoe. The fixed end of the second shoe is disposed axially adjacent to the free end of the first shoe.

Abstract: A seal assembly for use between an inner shaft and an outer shaft rotatable about a common axis within a turbine engine includes a pair of end rings and a plurality of seal elements coupled between the pair of end rings. Each end ring includes a flange extending in an axial direction, and each seal element includes a pair of shoulders extending in opposing axial directions. The seal assembly also includes a pair of retaining rings. Each retaining ring is positioned between one shoulder of the pair of shoulders and a corresponding one end ring flange of the pair of end ring flanges.

Abstract: A turbine housing includes an inner pipe that forms an exhaust air flow path in which a turbine wheel accommodating a turbine shaft is arranged; and an outer pipe that is spaced from the inner pipe at a predetermined distance and covers the inner pipe. At least one reinforcing plate is secured to an inner surface of the outer pipe.

Abstract: In a turbine housing that includes a scroll portion constituting a spiral exhaust gas passage between an exhaust inlet side flange constituting an inlet for exhaust gas and an exhaust outlet side flange constituting an outlet for the exhaust gas, the turbine housing discharging the exhaust gas to an exhaust outlet side through a turbine wheel disposed in a central portion of the scroll portion, a part of a passage face of the exhaust gas passage, in the scroll portion, is formed from a scroll member made of a casting.

Abstract: A non-contact seal assembly is provided. The non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing the annular array of the seal shoes. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes with the seal base, where the plurality of seal shoes each includes a weight reduction pocket formed in a circumferential region of the seal shoe.

Abstract: A non-contact seal assembly is provided. This assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. An aperture may extend partially axially into the first seal shoe from the first shoe end and laterally within the first seal shoe. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Abstract: A non-contact seal assembly is provided. This assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. An aperture may extend partially axially into the first seal shoe from the first shoe end and laterally within the first seal shoe. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Abstract: A support assembly for a gas turbine engine includes an outer support that extends about a circumferential axis and includes at least one engagement member. An inner support forms a cavity. A control ring is located within the cavity and includes at least one tab for engaging at least one engagement member on the outer support.

Abstract: An intershaft seal assembly for use between an inner shaft and an outer shaft rotatable within a turbine engine is presented. The seal assembly includes a sealing ring, an inner ring, and a pair of end rings. The sealing ring further includes a plurality of asymmetric ring segments whereby each asymmetric ring segment further includes a vertical flange and a pair of horizontal flanges extending from the vertical flange in a non-symmetric arrangement. The non-symmetric seal geometry provides an axial force balance thereby reducing wear and increasing seal life. The sealing ring is disposed about the inner ring. The inner ring includes a plurality of ridges that engage the asymmetric ring segments so as to prevent rotation of the asymmetric ring segments with respect to the inner shaft. The end rings are disposed about the sealing ring and the inner ring.

Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection configured to engage the inner surface, the actuator further comprising a plurality of locating protrusions extending from the projection, the locating protrusions configured to fit within locating channels defined in the first end piece and the second end piece.

Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.

Abstract: A sealing band located in opposing seal band receiving slots of adjacent turbine disks to seal an annular gap therebetween. An anti-rotation body including a base portion is located between edges of the sealing band within the annular gap, and a pin portion extends axially from the base portion for engagement with a cut-out portion of at least one of the disks. A pair of spaced projections extend from the base portion and into through openings in the sealing band at a location within the annular gap. The projections define an attachment structure attaching the anti-rotation body to the sealing band.

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: A segment of a seal assembly for sealing against a rotating member is disclosed. The segment includes a radial external surface, a radial internal surface for sealing against said rotating member, a face groove, and a secondary sealing surface. In embodiments, the segment may include a radial feed groove, and the face groove has an axial depth from the surface of the secondary sealing surface that is greater than the axial depth of the radial feed groove. Additionally, in embodiments, the face groove may include a relief groove, the face groove has a radial length at the axial position of the secondary sealing surface, the relief groove is axially offset from the secondary sealing surface, and the relief groove includes a portion with a radial length greater than the radial length of the face groove at the axial position of the secondary sealing surface.

Abstract: Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap.

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 circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing.

Abstract: A seal assembly for a turbomachine is provided. The turbomachine includes a stationary housing and a rotor rotatable about an axis. The seal assembly includes a plurality of arcuate packing ring segments disposed intermediate to the rotor and the stationary housing, and a plurality of inter-segment gaps disposed between the plurality of arcuate packing ring segments. The plurality of inter-segment gaps are inclined at a first angle from a radial axis of the rotor and inclined in a direction of motion of the plurality of arcuate packing ring segments. The seal assembly also includes a biasing member disposed intermediate to the stationary housing and the plurality of arcuate packing ring segments and coupled to both.

Abstract: An inter stage seal housing for a turbine engine having upper and lower half inter stage seal housings in which a contact sealing surface of the seal housing is restored after an interval of engine operation. The contact sealing surface is restored by fitting a replaceable wear strip on the downstream sealing surface of the seal housing. In order to fit the replaceable wear strip, a circumferential groove is machined along an outer peripheral edge of the seal housing. The groove is machined to include axial location and radial retention such that the wear strips can be slid into the upper half and lower half inter stage seal housing circumferentially from the horizontal joint. The groove includes through holes and the wear strips include corresponding threaded holes such that the wear strips can be fastened in the groove by fasteners and fastener retention hardware.

Abstract: A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combustion chamber, has a combustion chamber wall edge which freely terminates in the axial flow direction of the hot gases. The combustion chamber wall edge is formed with a profile which blocks or at least inhibits a diffuser effect when a cooling air flow, which is guided axially through the flow passages into the annular spatial area, flows over the combustion chamber wall edge.

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 sealing ring for turbo engines is provided. The sealing ring includes individual sealing segments, between which springs are mounted. Locking elements are provided on the parting joint of the turbo engine to retain the sealing segments. In order to ensure that the sealing elements can be securely closed on the parting joint, the sealing segments are positively interconnected on the parting joint.

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 may contain a pocket. 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: 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. Additional grooves are contained on the shaft-side face of each sealing ring segment. The additional grooves direct and create pressurized air within the dead end circumferential groove, either directly or indirectly maintaining a seal between the ring segments and the shaft.

Abstract: A turbomachinery includes a labyrinth seal (2) to prevent unstable vibration of a rotor formed by dividing the seal into segments (7) in a circumferential direction and combining the segments (7) whose comb teeth (5) differ in height. The labyrinth seal (2) preferably includes two kinds of segments (7) whose comb teeth (5) differ in height for each kind of segment, and the segments (7a) of the greater comb tooth height are arranged in a certain reference direction on a cross section right-angled to a rotational axis, and in a direction opposite to the reference direction, and the segments (7b) of the smaller comb tooth height are arranged in a direction right-angled to the reference direction, and in a direction opposite to that right-angled to the reference direction.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed intermediate to a stationary housing and a rotor. Each of the segments includes at least one plate and a sealing element. The seal assembly also includes multiple inter-segment gaps formed between the multiple sealing device segments. Further, for each pair of adjacent sealing device segments, at least one pair of adjacent plates includes one plate overlapping another plate at an inter-segment gap.

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 seal apparatus including at least first and second adjacent seal segments, each including an elongate body with ends defined at opposing elongate body ends, to be arranged such that an end of the first seal segment joins with a complementary end of the second seal segment, the end of the first seal segment including a first male component protruding from a plane of a first seal surface to define a first female mating section about the first male component, the end of the second seal segment including a second male component protruding from a plane of a second seal surface to define a second female mating section about the second male component, the first and second male components being receivable in the second and first female mating sections, respectively, to form first and second male component overlaps in at least two dimensions.

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 yoke air seal assembly for sealing a vertical pulverizer yoke includes a yoke seal housing ring having a plurality of circumferential segments mounted together end to end in a ring. A seal ring is mounted radially inside the housing ring. The seal ring has a radially inner face having a plurality of grooves defined therein for forming a labyrinthine air seal against a pulverizer yoke. The seal ring can be segmented into a plurality of circumferential seal ring segments. The segmented ring configuration facilitates installation and replacement of yoke seal components, increases operational lifetime thereof, and reduces down time for such installation and replacement.

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: A seal assembly for a turbomachine is provided. The turbomachine includes a stationary housing and a rotor rotatable about an axis. The seal assembly includes a plurality of arcuate packing ring segments disposed intermediate to the rotor and the stationary housing, and a plurality of inter-segment gaps disposed between the plurality of arcuate packing ring segments. The plurality of inter-segment gaps are inclined at a first angle from a radial axis of the rotor and inclined in a direction of motion of the plurality of arcuate packing ring segments. The seal assembly also includes a biasing member disposed intermediate to the stationary housing and the plurality of arcuate packing ring segments and coupled to both.

Abstract: A split mechanical composite seal assembly for providing a seal between a rotating shaft and a static surface. The split mechanical composite seal assembly includes first and second axially adjacent annular seal elements. The first and second seal elements each include a sealing edge contacting the shaft to provide a respective seal between the first and second seal element and the shaft. A static housing receives the first and second seal elements and engages the static surface to provide a static stationary seal, while concomitantly providing a flex region that engages the seal elements to form a dynamic seal therewith. A holder assembly receives one seal element and may include a double-angled lead-in to facilitate installation of the seal element. The holder assembly may include a detent groove for receiving and retaining an O-ring disposed about the seal element. The static housing may comprise two mating segments having overlapping surfaces.

Abstract: A circumferential seal system for sealing a high pressure region from a low pressure region separated by a runner with an outer circumferential surface and a seal ring disposed about the outer circumferential surface is described. The seal system includes a plurality of groove sets separately disposed along the outer circumferential surface. Each groove set further includes at least two grooves. At least one groove within each groove set exerts a lifting force via a fluid from the high pressure region onto the seal ring as the runner translates with respect to the seal ring along an axis substantially perpendicular to the rotation of the runner. The continuous feed of fluid onto the seal ring ensures a thin film between the seal ring and the runner regardless of their relative arrangement during axial excursions of the runner resulting from conditions within a turbine engine.

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: 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 circumferential seal system for sealing a high pressure region from a low pressure region separated by a runner with an outer circumferential surface and a seal ring disposed about the outer circumferential surface is described. The seal system includes a plurality of groove sets separately disposed along the outer circumferential surface. Each groove set further includes at least two grooves. At least one groove within each groove set exerts a lifting force via a fluid from the high pressure region onto the seal ring as the runner translates with respect to the seal ring along an axis substantially perpendicular to the rotation of the runner. The continuous feed of fluid onto the seal ring ensures a thin film between the seal ring and the runner regardless of their relative arrangement during axial excursions of the runner resulting from conditions within a turbine engine.

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: A method for facilitating the installation of labyrinth packing comprises the step of using pressurized air to extend the packing segments of a portion of a disassembled rotor casing to the close clearance position.

Abstract: a system for facilitating turbine labyrinth packing comprises: a packing holder 30, packing 20, packing teeth 21, pressurized air supply 50, hose 40, hose stabilizer 41, hose sleeve 42, pneumatic regulator 51, pressure gage 52, male quick disconnect 43, and female quick disconnect 44.

Abstract: A segment of a seal assembly for sealing a higher pressure area from a lower pressure area is disclosed. The segment comprises a radial external surface, a radial internal surface for sealing against a rotating member, a transverse groove for maintaining a pressure around portions of the segment, and one or more pads including a scooping groove. The scooping groove is positioned at or in proximity to an edge of the transverse groove and provides for a transition flow between the one or more pads and the transverse groove.

Abstract: A sealing ring for turbo engines is provided. The sealing ring includes individual sealing segments, between which springs are mounted. Locking elements are provided on the parting joint of the turbo engine to retain the sealing segments. In order to ensure that the sealing elements can be securely closed on the parting joint, the sealing segments are positively interconnected on the parting joint.

Abstract: Assembly of segmented seals can be problematic in areas of limited space for an introductory tapered mandrel and where there are the problems with damage to the seal surfaces 23, 24. By the present method and arrangement, a seal formed from segments 22 is expanded to an expanded state and then retained at that state by the use of a sacrificial material 26 in the gaps 25 between the segments 22 opened by expansion. The sacrificial material 26 is typically a low melting temperature wax and so is removed when the seal arrangement reaches its operating temperature.

Abstract: A non-contacting seal for sealing in high temperature applications includes at least one segment having an inner pad with a hydrodynamic/hydrostatic lift-off geometry enabling the seal to run in a non-contact mode, and at least one finger spring supported on the pad that aids in making the seal radially compliant while also being axially stiff, compared to the radial direction. In one embodiment, multiple segments are supported on a support member spaced from the pad to form a gap (g) therebetween. The pad preferably includes a wear resistant layer on its inner diameter (ID) which prevents excessive wear of the pad. In one embodiment, the hydrodynamic/hydrostatic lift-off geometry is in the form of a groove formed on the inner pad. A cover may also be provided between inner pads at the ID and the support ring at the outer diameter OD in order to prevent leakage through the gap.

Abstract: A dynamic seal assembly for a rotating member comprising a first split housing carrying a first split seal, a second split housing carrying at least one second split seal, each split seal being resiliently closed so that sealing contact is maintained when the rotating member wobbles. The free ends of the second split seal overlap with one another in either a side-by-side relationship or an over-under relationship, or both.