Abstract: A sealing arrangement for a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine engine efficiency. The stator shroud segment includes an outer shroud having a leading edge groove and a trailing edge groove, and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook. The leading and trailing hooks of each of the inner shrouds are respectively engaged with the leading and trailing edge grooves of the outer shroud so as to connect the inner shrouds to the outer shroud. A resilient shaped seal is located on a leading edge hook of the inner shroud so as to be between the leading hook and a retaining ring that contributes to holding the inner shroud in place.

Abstract: An engine fan containment shroud including a containment structure composed of a composite material including a reinforcing fiber having an elongation to break of at least about 3.6%. The preferred fiber is a quartz fiber having an elongation to break of at least about 5%. Additionally or alternatively, the reinforcing fiber, in particular quartz fiber, has a hardness of at least about 4 on the Mohs scale, as measured on bulk material, which resists cutting by an impacting object. The composite material and specifically an epoxy/quartz fiber composite provides for weight reduction while providing fan blade containment without loss of structural integrity and with improved resistance to impact and puncture.

Abstract: A method for controlling fluid leakage between a first pressure region and a second pressure region within a gas turbine engine using a first sealing member and a second sealing member. The first sealing member is movably coupled to a portion of the gas turbine engine, and a space defined generally between a portion of the first sealing member and a portion of the second sealing member fluidly couples the first pressure region to the second pressure region. The method includes moving the first sealing member towards the second sealing member using fluid pressure within a portion of the engine, and, using the first and second sealing members, substantially controlling fluid leakage between the first pressure area and the second pressure area through the space generally without contacting the first sealing member with the second sealing member.

Abstract: A turbine engine that includes a housing having a circular cavity of an inlet and an outlet that provide fluid communication to and from the circular cavity. A rotor having a circular body and least one sealing fin extending from the circular body to the cavity wall of the circular cavity. A gas delivered into to the circular cavity causes the fin to move as it expands in the circular cavity. A sealing flap may also be incorporated into the system in order to ensure that gasses are directed against the fin. A valving system for use with the turbine is also disclosed.

Abstract: A sealing mechanism for a fluid pump comprises first and second seal members which are coaxially and radially oriented relative to each other, and are positioned between the rotating and non-rotating elements of the fluid pump to maintain a competent seal which is simple to assembly, maintain and repair or replace, and which also improves pump operation when compared to known sealing mechanisms for fluid pumps.

Abstract: A turbine engine has a rotor shaft rotatably carried within a non-rotating support structure. A seal is carried by the support structure circumscribing the shaft and having a flexible sealing element for sealing with the shaft. A chamber is located between the seal and support structure. A fluid is carried within the chamber and damps radial excursion of a seal axis from a support structure axis. The seal may be a full annulus or may be segmented. The fluid may be contained within one or more elastomeric bladders.

Abstract: A seal apparatus provides the seal between inner and outer elements. The seal apparatus has a flexible sealing element for forming a seal with a first of the inner and outer elements. At least one support element is secured to the sealing element. The seal further includes means for magnetically interacting with the first element to bias the seal relative to the first element.

Abstract: A turbine engine has a rotor shaft rotatably carried within a support structure. A seal is carried by the support structure circumscribing the shaft and having a brushpack for sealing with the shaft. A first plate on a first side of the brushpack has a first radial clearance from the rotor shaft. A rubplate has a radial clearance from the rotor shaft that is less than the first radial clearance when the seal and rotor are coaxial.

Abstract: A structure for attaching together or sealing a space between a first component and a second component that have different rates or amounts of dimensional change upon being exposed to temperatures other than ambient temperature. The structure comprises a first attachment structure associated with the first component that slidably engages a second attachment structure associated with the second component, thereby allowing for an independent floating movement of the second component relative to the first component. The structure can comprise split rings, laminar rings, or multiple split rings.

Abstract: A water pump includes a first enclosure having a center portion that is moveable from a normal condition to a deflected condition and a second enclosure adjacent to the first to form an internal cavity. An impeller is disposed within the internal cavity. A tubular shaft portion extends from the impeller through a bore in the second enclosure. The tubular shaft portion is press fit to a motor shaft which rotates the impeller within the internal cavity. As the motor shaft is inserted into the tubular portion of the impeller, a tool is used to press on and axially deflect the center portion of the first enclosure. Thus, the center portion of the first enclosure contacts the impeller and provides an opposing force on the impeller while the motor shaft is inserted into the tubular portion of the impeller. When the motor shaft is press-fit sufficiently into the tubular portion, the tool is removed.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a seal assembly including a brush seal and a plurality of seal bristles to a first rotatable shaft, and positioning the seal assembly such that the seal bristles contact a second rotatable shaft to facilitate sealing between the first and second rotatable shafts during gas turbine engine operation.

Abstract: A sealing arrangement for sealing around a turbine or compressor blade includes casing segments having sealing faces for abutting with opposing sealing faces of circumferentially adjacent casing segments along joints between the segments. The sealing faces on adjacent segments are forced into contact with each other by rotation of each casing segment about a mounting pin. To reduce radial leakage, a sealing plate is provided.

Abstract: An antifriction bearing unit comprises a rotating shaft, an outer ring, and rolling members. The rotating shaft comprises a large-diameter shaft portion serving as an inner ring and a small-diameter shaft portion, which is hollow and has a fitting portion of increased diameter at one end thereof. The large-diameter shaft portion has an end portion fitted and fixed in the fitting portion of the small-diameter shaft portion. The fitting portion has an outward flange integral with an end thereof. The outer ring is fixedly provided with a seal member having lips slidable in contact with the flange and the outer peripheral surface of the large-diameter shaft portion, respectively.

Abstract: A method and apparatus for sealing between an inner casing and an outer casing is provided. The method includes positioning a first sealing member in a leakage path defined between an inner casing and an outer casing such that leakage flow in a first direction activates the first sealing member, and positioning a second sealing member in the leakage path such that leakage flow in the first direction bypasses the second sealing member, and such that leakage flow in an opposite second direction activates the second sealing member. The apparatus includes a pair of circumferential grooves in a channel, a divider positioned in the channel that defines a leakage path, a first sealing member positioned to seal against a flow in the leakage path in a first direction, and a second sealing member positioned to seal against a flow in the leakage path in a second direction.

Abstract: A membrane seal includes a pair of confronting annular sealing grooves. A first annular sealing member is received in one of the oppositely facing sealing grooves and a second annular sealing member is received in the other of the oppositely facing sealing grooves. The first and second sealing members are sealably connected together by an annular membrane. A pressure difference across the membrane forces the first and second sealing members into contact with a side wall of each of the oppositely facing sealing grooves to effect a seal. Known sealing members have a circular cross-section but in the present invention at least one of them has an oval cross-section. The oval cross-section gives the first and/or second sealing member(s) a larger zone of contact with the oppositely facing sealing groove(s). This reduces the amount of wear on the first and/or second sealing member(s) and produces a better seal.

Abstract: A steam turbine includes a rotor supporting a plurality of turbine buckets. The rotor has shaped grooves for receiving a complementary-shaped bucket hook formed on an end of each of the turbine buckets. A rope seal is disposed in each interface between the bucket hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the bucket hooks between the buckets and respective rotor grooves.

Abstract: A seal assembly and method for a turbomachine having a rotary member and a stationary member circumscribing the rotary member. The seal assembly comprises an annular-shaped platform on the rotary member so as to be disposed at an outer circumferential region thereof. The platform is supported radially outward from the rotary member so as to project beyond axially-adjacent regions of the rotary member. The platform has a contact region radially separated from the rotary member by a cavity. A sealing member is disposed at a radially inward region of the stationary member, with a portion of the sealing member in rubbing contact with the contact region.

Abstract: A high-pressure ratio turbocharger of this invention has a two-stage compressor section comprising a first-stage compressor impeller rotatably disposed in a first compressor housing, and a second-stage compressor impeller rotatably disposed in a second-stage compressor housing. The first and second stage compressor impellers are attached to a common shaft, and are positioned within respective compressor housing in a direction facing away from one another. A portion of the second-stage compressor housing is formed from a compressor backplate attached to a turbocharger center housing. A scroll seal is disposed between the first and second-stage compressor housings, and is interposed between the impellers to separate outlet air flow between each respective first and second-stage compressor chamber.

Abstract: A seal assembly and method for a turbomachine having a rotary member and a stationary member circumscribing the rotary member. The seal assembly comprises an annular-shaped platform on the rotary member so as to be disposed at an outer circumferential region thereof. The platform is supported radially outward from the rotary member so as to project beyond axially-adjacent regions of the rotary member. The platform has a contact region radially separated from the rotary member by a cavity. A sealing member is disposed at a radially inward region of the stationary member, with a portion of the sealing member in rubbing contact with the contact region.

Abstract: A system and method for achieving clearance control for a high-pressure turbine by means of casing mechanical deflection. An active clearance control system is provided to act on a blade that rotates near a shroud. The shroud is attached to a case at a shroud supporting location, or shroud hanger. A clearance is required between a tip of the blade and the shroud. The blade tip and shroud are surrounded with an elastic case. This case can deflect radially in response not only to thermal expansion, but also to a difference in pressures acting on the inner and outer diameters of the case.

Abstract: In the diaphragm packing area of a turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a pair of raised rims having flanges with teeth projecting axially toward one another and defining slots therebetween. The platform segments each include underlying flanges with axially oppositely directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: In the diaphragm packing area of a steam turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a raised rim having flanges with axially oppositely projecting teeth circumferentially spaced one from the other by slots. The platform segments each include a channel section having flanges with axially inwardly directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: In a steam turbine high pressure end seal region, brush seals are provided between first and second pressure regions having a pressure drop in excess of the sealing capacity of an individual brush seal. To use brush seals between the first and second regions, one or more intermediate pressure regions are maintained at a substantially fixed predetermined pressure between the first and second pressure regions. Brush seals are interposed between adjacent pressure regions whereby the pressure drop between adjacent pressure regions is within the sealing capacity of the individual brush seal disposed between the adjacent pressure regions.

Abstract: To accurately axially position and/or seal between axially facing turbine parts, a groove having a cylindrical cross-section is formed in one surface with a centerline offset toward the one surface, the groove opening through the one surface. Rod segments having corresponding cylindrical cross-sections are inserted in the groove. The rod segments have flat surfaces coextensive therewith projecting a predetermined measured distance from the one surface, thereby accurately axially locating the turbine parts relative to one another and forming a seal therebetween. The rod segments have ends abutting one another to seal the segments one to the other.

Abstract: A method of assembling a steam turbine includes positioning a sealing member in a leakage path defined between a first stage nozzle diaphragm and a packing casing, wherein the first stage nozzle diaphragm has a first coefficient of thermal expansion, and the packing casing has a second coefficient of thermal expansion, and coupling the first stage nozzle diaphragm and the packing casing such that the sealing member is fixedly secured between the first stage nozzle diaphragm and the packing casing.

Abstract: A turbine engine has a rotor shaft rotatably carried within a support structure. A seal is carried by the support structure circumscribing the shaft and having a brushpack for sealing with the shaft. A first plate on a first side of the brushpack has a first radial clearance from the rotor shaft. A rubplate has a radial clearance from the rotor shaft that is less than the first radial clearance when the seal and rotor are coaxial.

Abstract: A seal apparatus provides the seal between inner and outer elements. The seal apparatus has a flexible sealing element for forming a seal with a first of the inner and outer elements. At least one support element is secured to the sealing element. The seal further includes means for magnetically interacting with the first element to bias the seal relative to the first element.

Abstract: A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the nozzle hooks between the nozzles and respective stator grooves.

Abstract: In a steam turbine high pressure end seal region, brush seals are provided between first and second pressure regions having a pressure drop in excess of the sealing capacity of an individual brush seal. To use brush seals between the first and second regions, one or more intermediate pressure regions are maintained at a substantially fixed predetermined pressure between the first and second pressure regions. Brush seals are interposed between adjacent pressure regions whereby the pressure drop between adjacent pressure regions is within the sealing capacity of the individual brush seal disposed between the adjacent pressure regions.

Abstract: The present invention reduces the amount of gas which leaks and flows from a high pressure side to a low pressure side of the axis and maintains good sealing performance even at high differential pressures. The invention discloses an axis sealing mechanism comprising casings which are supported inside of the stable portion, a plurality of planar plates, which are mutually spaced around the axis, each of which is fixed to the casings, positioned so that an inner end of each planar plate makes an acute angle with a peripheral surface of the axis and contacts the peripheral surface of the axis over a predetermined length in an axial direction, a high pressure side plate which is arranged at a high pressure side and a low pressure side plate which is arranged at a low pressure side so as to hold the planar plates therebetween and a flexible plate which is arranged between the planar plates and the high pressure side plate, and is flexible in an axial direction.

Abstract: A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion. The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith. The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring. The resilient members maintain contact between the shroud support segments and the ceramic shroud ring.

Abstract: In the diaphragm packing area of a steam turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a raised rim having flanges with axially oppositely projecting teeth circumferentially spaced one from the other by slots. The platform segments each include a channel section having flanges with axially inwardly directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: In the diaphragm packing area of a turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a pair of raised rims having flanges with teeth projecting axially toward one another and defining slots therebetween. The platform segments each include underlying flanges with axially oppositely directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: Spline seals are disposed in circumferentially registering slots of adjacent arcuate sealing segments disposed in grooves of the casing of a steam turbine about a rotor. The spline seals extend in the gap between the endfaces of the segments and minimize or preclude steam leakage past the endfaces. The spline seals may be oriented axially or inclined radially to minimize leakage paths in the radial inclined and axial directions, respectively. The spline seals are disposed in the slots which may be formed as part of original equipment manufacture or may be machined in segments with the spline seals provided as retrofits.

Abstract: A simplified support device (110) for nozzles (112) of a gas turbine stage, of the type in which the support device (110) is interposed in a rotor of the gas turbine, between an upstream blading disc (122) and a downstream blading disc (124) of the nozzles (112), and is provided with honeycomb-type alveolar seals (120); the nozzles (112) of the gas turbine stage comprise an annular body which is divided into nozzle segments (112) and the honeycomb-type alveolar seals (120) are anchored directly to these nozzle segments (112).

Abstract: An insert assembly is provided for a rotary machine wherein the rotary machine comprises a rotor and a casing. The rotor comprises a generally longitudinally-extending axis. The casing is generally coaxially aligned with the axis. The casing circumferentially surrounds and is radially spaced apart from the rotor. The insert assembly comprises a channel circumferentially disposed on the rotor and an insert circumferentially disposed in such channel such that the insert assembly is configured to thermally isolate frictional heat from the rotor to the insert.

Abstract: A seal is provided for controlling flow of a fluid in a fluid path in a rotary machine. The seal comprises a brush seal carrier having a front plate and a back plate disposed therein. A brush seal is disposed between the front plate and the back plate. In addition, a flexible member is disposed between the brush seal and the back plate for reducing stress in the brush seal.

Abstract: A seal is provided for controlling flow of a fluid in a fluid path in a rotary machine. The seal comprises a brush seal carrier having a front plate and a back plate disposed therein. A brush seal is disposed between the front plate and the back plate. In addition, a flexible member is disposed between the brush seal and the back plate for reducing stress in the brush seal.

Abstract: One or more stator seal assemblies are mounted in the housing of a rotating machine such as, for example, an air turbine starter for a gas turbine engine, and surround a rotating shaft. The seal assemblies each include a seal case and a seal. The seal has a face that engages an axial face of a face seal rotor to form a seal. One or more anti-rotation tabs in the seal case engage anti-rotation notches formed in the peripheral surface of the seal. The anti-rotation notches each include substantially arcuate sections formed in notch end surfaces. The arcuate sections increase the amount of wear in the notches that can be tolerated before a potential seal lock-up, thus increasing seal assembly lifetime.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a radially outwardly projecting platform between axially adjacent wheels on the rotor. The brush seal is located upstream of the labyrinth seal teeth. The platform has at least one and preferably a pair of flanges or fins projecting in opposite axial directions adjacent radial outer ends of the platform. Non-uniform heat distribution resulting from the frictional contact between the bristles of the brush seal and a sealing surface on the platform along the rotor surface affecting rotor dynamics is thereby eliminated or minimized.

Abstract: A joint sealing key assembly includes a sealing key having a sealing face and one or more posts projecting in a direction away from the sealing face. The sealing key is disposed in a key slot of a first part with the post extending into an opening through the bottom of the key slot. The post includes a laterally opening elongated hole for receiving a lateral pin to retain the sealing key in the slot during assembly. Upon formation of the joint by bringing the seal faces of the first and second parts together, the sealing key is displaced against the bias of a leaf spring thereby retaining the sealing face of the sealing key in sealing engagement with the seal face of the second part.

Abstract: In a gas turbine including a nozzle retaining ring having a first annular axially facing sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-shaped marginal portions is received in a cavity formed in the second surface. At operating conditions, the marginal portions seal against the base of the cavity and the first surface of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body is first compressed and maintained in a compressed state by applying one or more wraps about the seal body and an epoxy is used to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions against opposite sealing surfaces of the shroud segments and retaining ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner band of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth supported by a bracket secured to the inner margin of the inner rail. The radially inner end of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the legs of the supplemental seal are slit along their distal margin and staggered circumferentially relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.

Abstract: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a sealing surface on a rotatable component radially outwardly of the rotor surface. The contact between the brush seal and sealing surface lies along an axially upstream projecting flange of an annular platform such that heat generated by frictional contact between the bristles and the sealing surface has minimal effect on the rotor surface and hence rotor dynamics. A backup labyrinth seal is provided between the web and platform. Additionally, axially upstream projecting flanges are provided on the downstream buckets and which flanges are spaced radially outwardly of the rotor surface and lie in registration with the diaphragm web. Labyrinth teeth seal between the diaphragm web and the bucket flanges serving as a backup seal.

Abstract: A compliant woven tubular seal is provided in an arcuate cavity opening through an axial face of a plurality of shroud segments in opposition to a nozzle retaining ring. The annular composite tubular woven compliant seal includes a stainless steel inner metal core surrounded by an annular layer of silica fiber. Surrounding the silica fiber is a metal foil which prevents flow past the supplemental seal. An outer wear-resistant braiding serves as a protective covering and wear surface.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a radially outwardly projecting platform between axially adjacent wheels on the rotor. The brush seal is located upstream of the labyrinth seal teeth. The platform has at least one and preferably a pair of flanges or fins projecting in opposite axial directions adjacent radial outer ends of the platform. Non-uniform heat distribution resulting from the frictional contact between the bristles of the brush seal and a sealing surface on the platform along the rotor surface affecting rotor dynamics is thereby eliminated or minimized.

Abstract: An adjustable and stable pre-loading device equipped fan includes a stator, a first rigid spacer, a first bearing, an elastic device, a second bearing, a second rigid spacer, a rotor and a shaft. Among these, the stator includes a receptacle. The first bearing is formed on the first rigid spacer in the receptacle. The elastic device is formed in the receptacle and further on the first bearing. The second rigid spacer is formed on the second bearing on the elastic device. The rotor is coupled to the stator and has a blade structure. The first rigid spacer compresses the elastic device by means of the first bearing. The second rigid spacer compresses the elastic device by means of the second bearing. The distance between the first rigid spacer and the second rigid spacer is adjustable, thereby altering pre-loading applied on the first bearing and the second bearing.

Abstract: The knife edge air seal ring of a gas turbine is modified to receive a replacement or second seal ring portion having a wire brush seal. The replacement or wire brush air seal ring is mounted with the existing knife edge air seal mounting ring at a location so that the existing mounting ring may be used, while providing adequate strength and structural support for installation of the second, wire brush seal ring. The replacement seal ring may be provided with knife edge seals as well, if desired.

Abstract: To provide a water pump capable of preventing coolant leaked from a shaft sealing member from invading a bearing by a simple construction, a water pump has an outer ring of a bearing attached to an inner peripheral face of a pulley, an inner ring of the bearing attached to an outer peripheral face of a cylindrical portion of a housing and a shaft sealing member attached to an inner peripheral face of the cylindrical portion.