Abstract: A screw compressor includes a screw rotor, a casing, and a delivery side shaft sealing unit. The delivery side shaft sealing unit includes an annular groove, a seal ring, and a shaft sealing fluid supply passage. Pressure of the fluid that is supplied to the one side, in the axial direction, of the seal ring via the shaft sealing fluid supply passage is set higher than pressure that acts on a first side surface, in an axial direction with respect to a first side wall surface of the annular groove, of the seal ring.

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 having a first axially extending segment, a second axially extending segment, and a radially extending segment joining the first and second axially extending segments, the shoe cantilevered to the seal housing.

Abstract: A sealing ring for sealing an annular gap between a shaft and a bearing body surrounding the shaft, includes two sealing ring halves having ring segment shapes and a plurality of circumferentially formed sealing tips, arranged axially adjacent on the inner peripheral surface and protruding radially inward. The sealing tips are integrally formed together with the sealing ring halves. A method produces such a sealing ring.

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

Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.

Abstract: A sealing device for suppressing a leakage flow of a fluid via an annular gap between a stationary member and a rotary member of a rotary machine includes: a fixed fin having an annular shape and disposed in the annular gap; and a movable fin having an annular shape and being disposed adjacent to the fixed fin in an axial direction inside the annular gap. The movable fin has a greater thermal expansion coefficient than the fixed fin and is fixed to the fixed fin in a fixing region on a root-end side of the movable fin.

Abstract: An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

Abstract: An apparatus for sealing a circumferential gap between a stationary component and a rotating member is disclosed. The rotating member is configured to rotate about a longitudinal axis and has a radially outer surface disposed at a first non-zero angle with respect to the longitudinal axis. The apparatus includes a stator disposed circumferentially about the longitudinal axis and a shoe configured for translation in a radial direction with respect to the stator. The shoe includes a circumferential surface and a plurality of protrusions extending radially inward from the circumferential surface toward the rotating member, each one of the plurality of protrusions having a length configured to maintain a clearance gap with respect to the rotating member.

Abstract: A 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. A seal base circumscribes the annular array of the seal shoes. The assembly also includes 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. Each of the spring elements comprises a first beam having a first beam thickness and a second beam thickness, where the first and second beam thicknesses are different.

Abstract: A clearance-control-type seal structure including a plurality of arc-shaped grooves (23) formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings (11, 12) having fitting parts (11a, 12a) that are fitted into the grooves so as to leave a prescribed gap, that have extended parts (11b, 12b) that are exposed from the housing in the radial direction toward the inside and expand in the axial direction, and that, during operation, due to back pressure inside the grooves, receive a force that moves in the radial direction toward the inside. One extended part has a protruding part extending even further in the axial direction toward the upstream side, and the other extended part has formed in an outer circumferential surface of a downstream-side end part thereof a recessed part that corresponds to the protruding part.

Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft including a panel and a duct. The fire seal structure includes: a first member provided on the duct at a connection portion between the panel and the duct; and a second member that faces the first member around the opening and is provided on the panel. The panel defines the fire-prevention region. The duct communicates with an opening provided in the panel. The duct defines, together with the panel, the fire-prevention region. The first and the second members each contain refractory material, and the first and the second members form a labyrinth-shaped gap between the duct and the panel.

Abstract: A leaf seal for sealing off a shaft rotating around an axis, particularly in a gas turbine, is disclosed. The leaf seal includes a plurality of leaves arranged spaced apart from one another, where the leaves are produced integrally with a basic element supporting the leaves by a generative production process. A process for producing a leaf seal for sealing off a shaft rotating around an axis is also disclosed.

Abstract: A flow splitter includes a stepped ring and a flow restriction. The stepped ring includes a first inner wall having a first diameter, a second inner wall having a second diameter less than the first diameter, a radial step that transitions from the first to the second inner wall, and a plurality of apertures circumferentially located along the first inner wall and partially through the radial step. The first flow restriction has at least a portion thereof at a position between the first diameter and the second diameter. Further, the first flow restriction directs a flow of at least one of a gas and a fluid towards the first inner wall, and is configured to split the flow into an exit flow and a secondary flow. The exit flow exits the stepped ring via the plurality of apertures and the secondary flow proceeds downstream directed by the second inner walls.

Abstract: A labyrinth seal includes a first annular member positioned on a center axis and a second annular member disposed circumferentially around the first annular member. A seal land is disposed on one of the first annular member and the second annular member. The seal land is positioned radially between the first annular member and the second annular member relative the center axis. A seal plate is disposed on the other of the first annular member and the second annular member. The seal plate extends radially toward the seal land and includes a plate body extending between a base and a tip of the seal plate. The plate body extends along a majority of a radial span of the seal plate on a first plane. The tip of the seal plate extends axially and radially away from the plate body on a second plane.

Abstract: 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 during a non-operational state of the engine a reference point of the shoe is substantially centered within a range of radial deflections of the reference point of the shoe over the operating range of the engine.

Abstract: A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.

Abstract: An axial flow compressor is disclosed with a plurality of rotors. Each rotor includes a disk having an outer rim. Each outer rim is coupled to a radially outwardly extending rotor blade. The case is coupled to a plurality of radially inwardly extending stator vanes, i.e. cantilever-type stator vanes. Each stator vane is disposed between two rotor blades and extends towards one of the outer rims and terminates at a tip disposed in close proximity to one of the outer rims. At least one of the outer rims includes a serrated outer surface that faces the tip of a stator vane which results in a vortex flow causing air that would normally leak through the clearance between the stator vane and the outer rim to engage the stator vane to a greater degree thereby increasing the efficiency of the compressor.

Abstract: A non-contact seal assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. A first of the spring elements includes a first mount, a second mount and a spring beam. The spring beam extends a length longitudinally along a centerline from the first mount to the second mount. The spring beam includes opposing first and second surfaces. The first surface is disposed a first distance from the centerline, and the second surface is disposed a second distance from the centerline. The first distance and the second distance change as the spring beam extends longitudinally along the centerline to provide at least a portion of the spring beam with a tapered geometry. The portion of the spring beam has a longitudinal length that is at least about five percent of the length of the spring beam.

Abstract: A system for reducing leakage between static and rotating components within a turbine includes a static structure that is disposed radially outward from a tip of a rotating component. The static structure includes a seal assembly slot formed therein. A seal assembly includes a support block that is disposed within the seal assembly slot. A sealing material is disposed along a bottom portion of the support block and a tip slot is formed within the sealing material. The support block includes a forward portion that is slideably engaged with a forward inner surface of the seal assembly slot and an aft portion that is slideably engaged with an aft inner surface of the seal assembly slot. The system further includes a spring that extends axially between an aft wall of the seal assembly slot and an aft wall of the support block.

Abstract: A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change.

Abstract: Disclosed is a shaft sealing device including: a housing in which an annular recessed portion is formed and which is fixed to a stator; a sealing body, a radially outer portion of which is accommodated by the annular recessed portion; and a high pressure-side sealing plate that is disposed along the sealing body in a high pressure region. An inflow groove is formed in any member of the housing, the high pressure-side sealing plate, and the sealing body such that a fluid flows through the sealing body from a low pressure region during a non-normal operation in which pressure in the high pressure region is higher than pressure in the high pressure region. A communication path is formed in the housing such that the inflow groove and a space in the high pressure region communicate with each other via the communication path.

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: One of the components (15), opposite a labyrinth seal (12), is arranged sliding on a conical interface (18) of its support (7, 19) and constructed from a material with different thermal expansions, so as to reduce the clearance with the component face to face (13, 14), at steady state, at high temperature. The sealing surface (25) may be assured by a circulation of oil.

Abstract: A salt-spray protection structure for fan includes a frame, a hub, at least one protruded portion, and a stator assembly. The frame is internally provided with a base that internally defines a receiving space and has a bearing cup and at least one raised end formed thereon. The hub is mounted on the base, and one side of the hub facing toward the base has at least one open end. The protruded portion is selectively formed on one of the raised end of the base and the open end of the hub. The stator assembly is fitted around the bearing cup. The protruded portion works to scrape off salt grains that are attached to and accumulated on the hub or the base, allowing the fan to have extended service life.

Abstract: A shaft seal includes first and second rings, each formed from first and second discrete arc segments, mounted on a shaft. The first ring includes a central opening and a flange projecting axially away from a first axial surface of the first ring around the central opening, and the flange has a radially outer surface. The second ring has a radial inner face defining a central opening that includes a first portion extending from a first axial face of the second ring and a second portion extending from a second axial face of the second ring, and the second ring is mounted to the first ring with the second portion in contact with the radially outer surface of the flange. A plurality of fasteners extend from the second ring into an axial surface of the first ring or from the first ring into an axial face of the second ring.

Abstract: A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46).

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

Abstract: The disclosed finger seals are designed to be operational under rotational velocity or a stationary condition. The contact surface of the finger seals is inclined in an axial direction. The rotational velocity of the bore does not affect the hydrodynamic lift and the finger seals can operate at any rotational speed, unlike prior finger seal where the hydrodynamic lift is generated by rotational velocity. Each finger seal is pressure balanced. The pressure chambers on the two sides of each finger seal are connected through the finger cutouts. The finger seal design is such that the fingers lift and move away from the bore surface in radial direction. In one form, each finger seal is designed with the specific required length to allow sufficient surface area for the hydrodynamic force such that the finger seals would be lifted from the bore surface at the design pressure.

Abstract: A labyrinth seal design, an actuation control clearance strategy, and a method of operating a turbomachine. The labyrinth seal design including a plurality of features configured to open and close radial clearances in response to relative axial movement between a stationary component and a rotating component. The actuation control clearance strategy and method of operating a turbomachine effective to achieve relative motion between a rotating component and a stationary component of the turbomachine using active elements. Axial displacement of the rotating component relative to the stationary component provides an adjustment in a radial clearance at one or more sealing locations between the rotating component and the stationary component to suit a given operating condition of the turbomachine.

Abstract: A method and system for adjusting the clearance between a stator member and the tip of a rotor member in a rotor apparatus. The system comprises a position adjustment mechanism for adjusting the radial position of the stator member to any one of at least two and preferably three different radial positions. The system further comprises a variable pressure chamber having a first pressure state and a second pressure state. The system is arranged for applying a force for maintaining the stator member in either one of said at least two radial positions when said chamber is in said first pressure state and for allowing the position adjustment mechanism to adjust the radial position of the stator member between said at least two positions when the chamber is in said second pressure state.

Abstract: Bearing isolator seal for installation within an assembly including a housing having a bore, and a shaft rotatable in the bore. The seal includes an interlockable stator and rotor, and a diffuser ring disposed between the stator and the rotor.

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: A sealing assembly provides a seal between a first element and a second element, the first element being movable with respect to the second element, wherein the sealing assembly comprises: a sealing member adjacent to the first and second elements; a first seal portion for providing a first seal between the sealing member and the first element, the first seal portion being arranged in a first direction; and a second seal portion for providing a second seal between the sealing member and the second element, the second seal portion being arranged in a second direction, wherein the first direction is arranged at an angle with respect to the second direction and the sealing member is disposed such that the sealing member is movable relative to the second element in the second direction.

Abstract: The present invention relates to a centrifugal pump, a shaft sleeve and a stationary seal member for a static seal used in connection with a dynamic sealing of a centrifugal pump. The invention relates to a static seal the clearance of which may be adjusted while the pump is running. Especially the invention discusses the novel structure of such a static seal.

Abstract: A steam turbine comprises a steam turbine casing, a rotor, and at least one compliant plate seal assembly situated between the casing and the rotor. The compliant plate seal assembly comprises a supporting member being stationary with respect to the casing, a plurality of plate members movably mounted to the supporting member and extending towards the rotor, each plate member being inclined with respect to a rotation direction of the rotor, and an actuator for selectively exerting a pressure to retract the plate members in a direction away from the rotor.

Abstract: Disclosed is a variable clearance packing ring including a plurality of arcuate packing ring segments positional seriatim, a plurality of biasing member interfaces defined by the plurality of arcuate packing ring segments, and a biasing member interactive with one of the plurality of interfaces on one of the plurality of arcuate segments and one of the plurality of interfaces on an adjacent one of the plurality of arcuate segments.

Abstract: The present invention relates to replaceable brush seal assemblies for use with turbines such as industrial gas turbines. In accordance with the present invention, a brush seal assembly comprises a flange, a brush seal mounted to the flange, and retainers preventing rotation of the brush seal relative to the flange. A method of repairing a brush seal having a back plate, side plate, and bristles is also disclosed. The method comprises the steps of removing the side plate and the bristles from the back plate, and securing a second brush seal to the back plate.

Abstract: A method of assembling a turbomachine that includes a rotor and a stationary component is provided. The method includes coupling a housing to the stationary component using at least one biasing member, wherein the housing extending circumferentially about the rotor. The method also includes coupling at least one annular ring to the housing, and coupling a plurality of plate members to the housing such that the at least one annular ring extends from the housing towards the rotor and partially through the plurality of plate members.

Abstract: A spring assembly for a retractable turbine rotor seal supported in an arcuate segment may include in one embodiment a first radially inner restraining plate having a lower surface adapted to engage a surface of a turbine stator, and a flat upper surface provide with an upstanding hub; a second radially outer restraining plate having a flat lower surface and an upper surface adapted to engage a surface of the arcuate segment, the radially outer restraining plate formed with an opening receiving the upstanding hub; and at least one spring telescoped over the upstanding hub and exerting a radially outward biasing force on the second radially outer restraining plate, and adapted to exert a radially outward retracting force on the arcuate segment.

Abstract: The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and a packing ring. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring and the rotor. The plurality of arcuate teeth includes at least one subset of arcuate teeth. The clearance of at least one of the arcuate teeth is different from the clearances of the rest of the arcuate teeth. The clearances of the arcuate teeth of the at least one subset do not progressively increase going from an upstream to a downstream side of the turbomachinery.

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 invention relates to a device for sealing the space between first and second components, wherein a sealing element is placed between the sealing surface of the first component and the sealing surface of the second component, means are used for displacing the sealing element towards the first component and the sealing surface of the second component is used in the form of a guiding surface for the sealing element when it is displaced towards the first component. The means comprise a movable pressure element which is embodied in such a way that the displacement thereof generates the displacement of the sealing element.

Abstract: The hybrid seal assembly includes a seal for use with rotating surfaces which may suffer significant deflections such as for sealing between flanges and mating surfaces typical of annular seal face surface of a diffuser section of a tip turbine engine.

Abstract: A compressor of a gas turbine engine comprises blades 2, 4 provided on blade platforms 8, 12 of a rotor. Stator vanes 20 lie between the blades 2, 4 and are connected to a vane support structure 22. Sealing rings 38 are secured to the vane support structure 22 to restrict air flow into stator wells 36 on each side of the vane support structure 22. The sealing rings 38 are made from a flexible material so that they deflect on installation of the vane support structure 22 in a direction radially inwards between the adjacent blade platforms 8, 12.

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 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 seal structure that is capable of actively controlling the actuation of a movable seal ring, enhancing sealing performance, and enhancing reliability, is provided.

Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a structure operable to rotate about an axis and having a first surface facing radially outward. The circumferential sealing arrangement also includes a static housing circumscribing the rotatable structure. The circumferential sealing arrangement also includes at least one seal element connected to the static housing and having a second surface facing radially inward. The circumferential sealing arrangement also includes a seal runner rotatable with the structure and having a third surface facing radially outward. The third surface cooperates with the second surface to form a circumferential seal between the static housing and the rotatable structure. A radial gap is defined between the first surface of the rotatable structure and a fourth surface of the seal runner facing radially inward and opposing the first surface.

Abstract: The invention relates to a dry-running piston rod sealing arrangement (1) for sealing a piston rod (2) mounted in a longitudinally displaceable manner. The sealing arrangement comprises at least one sealing ring (5) having a sealing surface (5a), an actuator (7), a sensor (8), and a chamber ring (3) containing the sealing ring (5). The actuator (7) comprises an active connection in relation to the sealing ring (5), such that the sealing surface (5a) can be radially displaced in relation to the piston rod (2). The actuator (7) can be controlled according to a measuring value detected by the sensor (8).