Resilient, Flexible, Or Resiliently Biased Patents (Class 415/174.2)
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Patent number: 7571614Abstract: Turboshaft engine including two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two parts of the annular chamber.Type: GrantFiled: March 23, 2005Date of Patent: August 11, 2009Assignee: SnecmaInventors: Claude Lejars, Marica Mesic, Bruce Pontoizeau, Alexandre Roy, Patrice Suet
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Patent number: 7572099Abstract: A turbine engine includes a first turbine structure that supports a seal. The seal is movable within a recess of the first turbine structure. The seal is arranged in close proximity to a seal land of a second turbine structure for preventing a fluid from leaking past the seal and seal land. A thermal expansion member interconnects the first turbine structure and the seal. The thermal expansion member expands in response to an increase in temperature to move the seal toward the seal land preventing the typical enlarged gap between the seal and seal land resulting from thermal growth. In one example, the thermal expansion member, which is arranged at each opposing end of a seal segment, is a bimetallic coil spring supported on the first turbine structure by a cage. A free end of the coil spring is secured to the seal at the opposing end portions.Type: GrantFiled: July 6, 2006Date of Patent: August 11, 2009Assignee: United Technologies CorporationInventor: Mark E. Addis
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Publication number: 20090196742Abstract: A seal arrangement for sealing the space between a rotating element and a stationary element, the sealing arrangement comprising a compliant plate seal housing supported adjustably in the stationary element, the compliant plate seal housing supporting a compliant plate seal; and a spring system provided between the compliant plate seal housing and the stationary element to bias the compliant plate seal housing in a direction away from a surface of the rotating element. Alternatively, or additionally, one or more actuators may be provided to move the compliant plate seal housing in a direction away from a surface of the rotating element.Type: ApplicationFiled: February 4, 2008Publication date: August 6, 2009Inventors: Norman A. Turnquist, Frederick G. Baily, Bernard A. Couture, JR., Jason P. Mortzheim, Sean D. Feeny, William E. Adis, Shorya Awtar, Nikhil K. Verma
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Patent number: 7562880Abstract: A seal usable between two thermally movable components to prevent fluids from mixing. For instance, the seal may be used to seal thermally movable components of a turbine engine that may include, but are not limited to, leading edge shrouds, isolation rings, ring segments, and vane segments. The seal may be formed from a body having a cross-section generally orthogonal to a longitudinal axis and include a first side, a second side generally opposite to the first side, a first end, and a second end generally opposite to the first end. A compliant material may be coupled to the first or second end, or both, and may absorb thermal expansion of the two thermally movable components. The seal may reduce leakage flow paths between the seal and the thermally movable components.Type: GrantFiled: February 9, 2004Date of Patent: July 21, 2009Assignee: Siemens Energy, Inc.Inventors: Hubertus Edward Paprotna, David A. Little
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Publication number: 20090169376Abstract: A turbine nozzle segment includes a first band, an airfoil extending from the first band and a support attached to the first band. The support may have a plurality of circumferentially spaced apart tabs.Type: ApplicationFiled: December 29, 2007Publication date: July 2, 2009Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka, Peter Robert Griffiths
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Publication number: 20090169370Abstract: A turbine nozzle segment includes a band having a plurality of tabs, an airfoil extending from the band and a support structure attached to the tabs. The support structure has a plurality of biasing structures.Type: ApplicationFiled: December 29, 2007Publication date: July 2, 2009Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
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Publication number: 20090169369Abstract: A turbine nozzle segment includes a band having a plurality of circumferentially spaced apart tabs and a single airfoil extending from the band.Type: ApplicationFiled: December 29, 2007Publication date: July 2, 2009Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
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Patent number: 7549841Abstract: A turbomachine having a rotor blade with a tip seal formed between the blade tip and the shroud, where the tip seal is formed by a thin metal plate extending from the blade tip and bending away from the direction of rotation of the blade such that a flat surface of the thin metal plate floats against the shroud surface by a cushion of air formed due to the rotation. The tip seal is forced against the shroud surface due to centrifugal force from rotation so that the tip seals maintain a seal even in cases of high eccentricity. Because of the cushion of air formed from rotation, the tip seal does not wear from rubbing. The flexible plate tip seal is formed from a material such as titanium for use in a compressor, or from a high temperature resistant metal alloy such as Inco 625 for use in a turbine of a gas turbine engine.Type: GrantFiled: September 1, 2006Date of Patent: June 23, 2009Assignee: Florida Turbine Technologies, Inc.Inventor: Walter Marussich
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Patent number: 7549835Abstract: A system and method for extending seal life and for reducing leakage flow in a turbine engine is directed to an interface defined between a stationary component and a rotating component. A seal, which can be a flexible seal such as a brush seal, can be operatively attached to the stationary component. The rotating component has a first region at a first radius relative to the axis of rotation that transitions into a second region at a second, larger radius relative to the axis of rotation. In one embodiment, the rotating component can be selectively axially moved between a first position and a second position. In the first position, the seal is disposed over the first region so as to define a clearance. In the second position, the seal is disposed over the second region so as to decrease the size of the clearance.Type: GrantFiled: July 7, 2006Date of Patent: June 23, 2009Assignee: Siemens Energy, Inc.Inventor: Dieter Brillert
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Patent number: 7540708Abstract: A method of assembling a seal assembly for a turbine engine is provided, wherein the method includes providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween, and forming at least one recess within at least one of the outer ring portion and the neck portion. The method also includes extending a biasing mechanism across the seal ring such that the biasing mechanism is positively retained within the at least one recess.Type: GrantFiled: June 30, 2006Date of Patent: June 2, 2009Assignee: General Electric CompanyInventors: Kurt Neal Laurer, Kevin Joseph Barh, Bernard Arthur Couture, Jason Paul Mortzheim
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Publication number: 20090136339Abstract: A method for assembling a rotary machine is provided. The method includes providing at least one seal assembly that includes at least one annular seal housing defined by a top wall, a front wall, and a rear wall, that are connected together such that a cavity is defined within the housing, coupling a plurality of flexible plates within the cavity such that the plates are axially-spaced from the front wall and the rear wall within the cavity, coupling at least one side plate to the at least one annular seal housing such that the at least one side plate is moveable with respect the front wall and the rear wall, and coupling the at least one sealing assembly within a rotary machine to facilitate sealing between a rotary component and a stator component.Type: ApplicationFiled: November 27, 2007Publication date: May 28, 2009Inventors: Nikhil Kumar Verma, Jason Paul Mortzheim, Yogesh Sathe, Hrishikesh Vishvas Deo
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Publication number: 20090087307Abstract: A sealing assembly for achieving a fluid seal between a rotatable shaft and a housing circumscribing the rotatable shaft to inhibit fluid leakage therebetween a high pressure fluid region and a relatively lower pressure fluid region. The sealing assembly includes at least one primary seal, comprising an axial stack of a plurality of diaphragm members, including an upstream diaphragm and a downstream diaphragm. A plurality of finger seal plates are positioned between the upstream diaphragm and the downstream diaphragm. The plurality of diaphragm members define a passageway in fluid communication with the high pressure fluid region and a low pressure fluid region. The sealing assembly includes at least one secondary seal positioned within the passageway and configured to convert fluid from a high pressure axial pressure balance to a low pressure axial pressure balance thereby reducing a radially inward pressure load.Type: ApplicationFiled: September 28, 2007Publication date: April 2, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Donald I. Takeuchi, Bradley R. Tucker, Yates Y. Wong, Mingfong F. Hwang
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Patent number: 7484927Abstract: Disclosed herein is a packing ring assembly including a packing ring segment, a bar, a cover plate, and a spring. The packing ring segment has an axial slot. The bar is disposed within the slot. The cover plate is disposed along an outer periphery of the packing ring segment. And, the spring is compressed between the bar and the cover plate.Type: GrantFiled: April 14, 2006Date of Patent: February 3, 2009Assignee: General Electric CompanyInventors: Richard J. Chevrette, Flor Rivas, Frederick G. Baily, William E. Adis, Mark E. Kelly, Bernard A. Couture, Kurt N. Laurer
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Publication number: 20090028696Abstract: A bushing made from a thermoplastic polymer and circumferentially-oriented continuous high tensile modulus fibers is useful as a part for pumps and compressors and other similar types of apparatus. These parts may be useful at high temperatures and/or in very corrosive environments, often lengthen the time between required maintenance checks, and usually perform better than metal bushings under nonstandard operating conditions.Type: ApplicationFiled: July 21, 2008Publication date: January 29, 2009Inventors: Thomas P. Gannett, Joel D. Citron
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Publication number: 20090028695Abstract: A bushing-like part made from a fluoropolymer and circumferentially oriented continuous high tensile modulus fibers is useful as a part for pumps and compressors and other similar types of apparatus. These parts may be useful at high temperatures and/or very corrosive environments, often lengthen the time between required maintenance checks, and usually perform better than metal bushings under nonstandard operating conditions.Type: ApplicationFiled: July 21, 2008Publication date: January 29, 2009Inventors: Thomas P. Gannett, Joel D. Citron
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Publication number: 20080232956Abstract: The invention relates to a turbine blade (63, 65) comprising a vane (67, 69) that runs along a blade axis (73, 75) and a platform region (61), which is located at the root of the vane (67, 69) and has a platform (71) that extends transversally to the blade axis (73, 75). The aim of the invention is to configure a delimitation (87) of a flow channel (5) of a gas turbine (1) in the simplest possible manner. To achieve this, the platform (71) is configured by an elastic sheet metal part (77, 79) that rests on the vane (67, 69). Said part leads to a gas turbine (1) comprising a flow conduit (5) that runs along an axis (3) of the gas turbine (1), said conduit having an annular cross-section for a working medium (M) and a second (9, 13) vane stage (7, 9, 11, 13) that is situated downstream of a first (7, 11) vane stage, which runs along the axis (3).Type: ApplicationFiled: January 12, 2005Publication date: September 25, 2008Inventors: Stefan Baldauf, Hans-Thomas Bolms, Michael Handler, Christian Lerner
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Publication number: 20080170937Abstract: Pump (1) comprising a rotary shaft (30), a bearing housing (80) that is fixed relative to the rotary shaft, at least one rolling bearing (70) the inner ring (71) of which is connected to the said rotary shaft and the outer ring (76) of which is able to slide in this housing along the axis of rotation of the rotary shaft. The bearing housing (80) comprises a shoulder (81) situated on one side of this bearing and able rigidly to prevent translational movement of the outer ring (76) along the axis of rotation, and a deformable elastic device (100) fixed to the housing on the other side of the bearing (70) so that the bearing lies between the shoulder and the elastic device.Type: ApplicationFiled: December 19, 2007Publication date: July 17, 2008Applicant: SNECMAInventors: Emmanuel Edeline, Charles Marciquet, Laurent Fabbri, Fabien Wahl
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Patent number: 7367776Abstract: A turbine engine stator assembly in juxtaposition across a radial gap with a rotary blading assembly includes a radially movable shroud and a gap control member made of at least one shape memory alloy (SMA). The SMA is selected and preconditioned to deform pre-selected amounts to change the radial length of the gap during engine operation responsive to temperature about the SMA. A fluid flow means delivers fluid to the SMA at pre-selected temperatures during engine operation.Type: GrantFiled: January 26, 2005Date of Patent: May 6, 2008Assignee: General Electric CompanyInventors: Robert Joseph Albers, Rafael Ruiz, Marcia Boyle, Christopher Charles Glynn
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Patent number: 7347662Abstract: A sealing arrangement between annular components 2, 4, for example in a gas turbine engine, comprises an L-shaped sealing ring 20. The sealing ring 20 has a first limb 24 received in a groove 28 in the first component 2, and a second limb 26 having a sealing face 30 which is maintained in contact with an abutment surface 32 on the second component 4 under the resilient action of the sealing ring 20. The second limb 26 is exposed to the pressure in a chamber 34 which assists the resilience of the sealing ring 20 in maintaining sealing contact between the sealing face 30 and the abutment surface 32. Bleed holes 38 are provided.Type: GrantFiled: October 3, 2005Date of Patent: March 25, 2008Assignee: Rolls-Royce plcInventor: Julian Glyn Balsdon
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Patent number: 7344356Abstract: A mechanical seal having a stationary ring and a rotating portion. The rotating portion includes a runner adjacent the stationary ring, an elastomer bellows adjacent the runner, a spring retainer plate and a spacer positioned between the elastomer bellows and the spring retainer plate. The spacer sets and maintains the elastomer bellows in proper position adjacent the runner.Type: GrantFiled: August 10, 2005Date of Patent: March 18, 2008Assignee: Wood Group ESP, Inc.Inventors: Steven Alan Howell, Edward Gross
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Patent number: 7344357Abstract: A method for assembling at least one seal assembly to a turbine having a casing extending at least partially around a rotor is provided. The method includes coupling the seal assembly to the casing such that the seal assembly extends into a fluid flow passage defined between the rotor and the casing and coupling at least one spring between the seal assembly and the casing to bias each seal assembly.Type: GrantFiled: September 2, 2005Date of Patent: March 18, 2008Assignee: General Electric CompanyInventors: Bernard Arthur Couture, Jr., Flor Del Carmen Rivas, Mark Edward Kelly, Jason Paul Mortzheim
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Patent number: 7338253Abstract: A sealing arrangement for the post impingement cavity of a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine energy 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 shroud to the outer shroud. The resilient shaped seal is located at a trailing edge of the respectively engaged inner and outer shrouds at an interface of the inner shroud and the outer shroud. In an example embodiment, a sealing groove is defined in the outer shroud for receiving the aft resilient seal.Type: GrantFiled: September 15, 2005Date of Patent: March 4, 2008Assignee: General Electric CompanyInventor: Tagir Robert Nigmatulin
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Patent number: 7334984Abstract: A low pressure turbine shroud assembly includes a backsheet with enhanced blade containment capabilities that is sized to be retrofitted into a conventional low pressure turbine assembly. The backsheet has first and second mounting rails at axially opposite ends thereof and a blade containment sheet shield disposed therebetween. The rails and the containment shield are of a uniformly increased thickness as compared with a conventional backsheet rail and containment shield design. The assembly also includes a modified mounting hook for mounting the improved backsheet to a case extending around the shroud. The mounting hook is of reduced thickness as compared with a conventional mounting hook for a conventional backsheet proportional to the increase in thickness of the backsheet. The assembly also can include a rub strip disposed between a radially inner surface of the backsheet and a turbine blade.Type: GrantFiled: December 24, 2004Date of Patent: February 26, 2008Assignee: Heico CorporationInventors: Frederick J. Stine, James W. Tucker, Stephen J. Szpunar
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Patent number: 7334985Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.Type: GrantFiled: October 11, 2005Date of Patent: February 26, 2008Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Dmitriy Romanov, Jeremy Drake, Gary Grogg, Gregory E. Reinhardt
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Publication number: 20080008582Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator blades extend between the rotor blades of axially adjacent disks. A knife edge seal is supported and retained by retaining flanges extending from a rim on each disk, and contacts the stator blades to limit the recirculation of air within the compressor. A plurality of lock assemblies are spaced about the circumference of disk backbones formed in each disk, with a plurality of knife edge seals located between each lock assembly. When in the lock position the lock assemblies reduce the slack used for assembly of the final knife edge seal to prevent shifting and rotating during operation.Type: ApplicationFiled: July 7, 2006Publication date: January 10, 2008Inventors: John T. Pickens, Tuy Tran, Allan R. Penda
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Publication number: 20080003100Abstract: A method of assembling a seal assembly for a turbine engine is provided, wherein the method includes providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween, and forming at least one recess within at least one of the outer ring portion and the neck portion. The method also includes extending a biasing mechanism across the seal ring such that the biasing mechanism is positively retained within the at least one recess.Type: ApplicationFiled: June 30, 2006Publication date: January 3, 2008Inventors: Kurt Neal Laurer, Kevin Joseph Barh, Bernard Arthur Couture, Jason Paul Mortzheim
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Patent number: 7309210Abstract: A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means, for vibration stabilizing.Type: GrantFiled: December 17, 2004Date of Patent: December 18, 2007Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, James W. Norris
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Patent number: 7287956Abstract: The turbine includes a diaphragm having a seal carrier mounted in opposition to seal teeth carried by the rotary component. The seal carrier includes a seal face having a coating of abradable material enabling the rotary component to abrade the material from the seal face. The seal carrier is removable from the diaphragm and is carried by an axial extension integral with or removable from the outer diaphragm ring. A spring may be interposed between the seal carrier and the stationary component.Type: GrantFiled: December 22, 2004Date of Patent: October 30, 2007Assignee: General Electric CompanyInventors: Robert James Bracken, Sterling Ray Hathaway, David Orus Fitts, Ron W. Korzun, Laurence Scott Duclos, William Edward Adis, Mark William Kowalczyk, Bernard Arthur Couture
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Patent number: 7261515Abstract: A shaft sealing mechanism of an annular shape having at least one divided portion, which is installed in an annular space between a rotor and a stator, includes a group of thin plates. Outer peripheral ends of the thin plates are joined, and inner peripheral free ends come in contact with the rotor in a sliding manner so that a surface of the rotor and the thin plates form an acute angle to partition the annular space into a high-pressure region and a low-pressure region without being joined. At least a low-pressure gap near the divided portion is set to be larger than a low-pressure gap in a circumferential direction other than near the divided portion.Type: GrantFiled: August 10, 2005Date of Patent: August 28, 2007Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Shin Nishimoto, Tanehiro Shinohara, Hidekazu Uehara, Takashi Nakano
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Patent number: 7229246Abstract: A compliant seal assembly for a rotating machine is provided. The seal assembly includes a static member, a movable member and a biasing member. The static member is rigidly fixed to the machine at its fore and aft ends. The movable portion has a first sealing surface configured to seal against a rotating member and a rear surface, which may be exposed to a fluid pressure to urge the first sealing surface toward a sealing position with the rotating member. The static and the movable members further include sealing surfaces at their fore, aft and end faces to seal against leakage of gas between the static and the movable members. The biasing member is configured to support the movable member on the static member and to urge the movable member away from the sealing position so as to reduce force on the rotating member during contact of the rotating member with the first sealing surface of the movable member.Type: GrantFiled: September 30, 2004Date of Patent: June 12, 2007Assignee: General Electric CompanyInventors: Farshad Ghasripoor, Shorya Awtar, Norman Arnold Turnquist, Biao Fang, Carl Anthony Flecker, III, James William Stegmaier, Glenn Herbert Nichols, James Charles Przytulski, Kurt Grover Brink, Richard Cohen Lykins, Jeffrey Reid Thyssen, Mahmut Faruk Aksit
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Patent number: 7229247Abstract: An integrated duct and baffle arrangement employing a hairpin transition area such that the construction is adapted to flex under thermal conditions.Type: GrantFiled: August 27, 2004Date of Patent: June 12, 2007Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, Martin Jutras
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Patent number: 7217089Abstract: A ring seal is mounted in the annular gap between a shroud platform overhanging portion and the surrounding shroud support to minimize cooling air leakage through the shroud.Type: GrantFiled: January 14, 2005Date of Patent: May 15, 2007Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, Martin Jutras
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Patent number: 7201560Abstract: A packing ring holder assembly for packing seal segments about a steam turbine rotor includes a nozzle box and a holder cooperable to form a dovetail for securing packing ring segments to the nozzle box. A spring is interposed between the nozzle box and packing ring segment to bias the latter radially inwardly for sealing with the rotor. The holder includes a shoulder for preventing axial movement of the spring in one direction.Type: GrantFiled: December 6, 2004Date of Patent: April 10, 2007Assignee: General Electric CompanyInventors: Charles Thomas O'Clair, Richard Jon Chevrette, Carl A. Greco, Jeyaruban Amirtharajah
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Patent number: 7201561Abstract: A swashplate seal assembly sized for rotor shaft rotation therein, including an outer cover encircling the rotor shaft and covering a sealing ring having an inner circumference on which a resilient sealing wiper is inwardly disposed. The outer cover, sealing ring and resilient sealing wiper are sectioned in respective like-configured curved segments for disassembly without removing adjacent segments during inspections. Inboard of the sealing ring is a flanged seal ring having an outer surface diameter limited in size to allow positioning the seal ring within the sealing wiper. The seal ring is fitted on an outer perimeter of a bearing retainer positionable within the sealing ring, thereby positioning the seal ring outer surface in sliding engagement with the sealing wiper during rotor shaft rotation. The outer cover positioning and the engaging relationship between seal ring and sealing wiper operate to minimize contaminants intrusion along the rotor shaft during rotation.Type: GrantFiled: May 18, 2005Date of Patent: April 10, 2007Assignee: United States of America, as represented by the Secretary of ArmyInventors: Wayne C. Parsons, Tracy A. Conklin
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Patent number: 7192246Abstract: A seal arrangement, for example a brush seal 8? in a gas turbine engine, includes thermal matching means for matching the rates of response of a supporting ring 14?, 16? of the seal, and of a rotatable component 4 with which the seal cooperates, to thermal changes in the environment of the seal induced by changes in operating conditions. The thermal matching means may comprise a slugging mass 24 and/or thermal insulation 28. Alternatively, or in addition, the region 24 of the housing at which the seal 8? is mounted may be made from a relatively low thermal expansion material. These measures reduce the rate of expansion and contraction of the seal 8? as the temperature in the engine varies so as to match more closely the rate of expansion and contraction of a rotatable component with which the seal cooperates.Type: GrantFiled: December 15, 2004Date of Patent: March 20, 2007Assignee: Rolls-Royce plcInventors: Christopher Wright, Christopher J Finch
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Patent number: 7186074Abstract: A drum-type rotor carries an annular row of moving blades having root portions held within a slot in the periphery of the rotor. A turbine casing surrounds the rotor and carries a static blade assembly with an annular row of static blades which, together with the annular row of moving blades, constitutes an impulse turbine stage. The static blade assembly has a radially inner static ring confronting a periphery of the rotor with a seal acting therebetween. The static blade assembly has an outer static ring which has a substantially greater thermal inertia and stiffness then the inner static ring and is capable of sufficient radial sliding relative to the casing so as to accommodate relative thermal expansion and contraction of the outer static ring and the turbine casing.Type: GrantFiled: May 13, 2004Date of Patent: March 6, 2007Assignee: Alstom Technology, Ltd.Inventors: David Paul Blatchford, Richard Martin Bridge, Philip David Hemsley, Alan Hesketh, Adrian Lord
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Patent number: 7175387Abstract: A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows. A sealing element (4) of plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.Type: GrantFiled: March 25, 2004Date of Patent: February 13, 2007Assignee: Alstom Technology Ltd.Inventors: Erhard Kreis, Markus Oehl, Ulrich Rathmann
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Patent number: 7172388Abstract: A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and second gas turbine engine components for spring loading the first and second gas turbine engine components relative to one another.Type: GrantFiled: August 24, 2004Date of Patent: February 6, 2007Assignee: Pratt & Whitney Canada Corp.Inventor: Remy Synnott
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Patent number: 7156613Abstract: In a gas turbine, the compressor load is reduced and the turbine load is increased for controlled bearing load reduction by forming a low-pressure chamber (8) that is shielded from the compressor air at the compressor (1) and a high-pressure chamber (9) that is supplied with compressor air at the turbine along the high-pressure shaft (2). The pressures can be controlled within specific limits. Controlled bearing load reduction allows high speeds and a long service life of the bearings.Type: GrantFiled: December 10, 2004Date of Patent: January 2, 2007Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Winfried-Hagen Friedl
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Patent number: 7128323Abstract: Primary objective of the present invention is to provide a seal device wherein the seal surfaces of the device are always brought into close contact against the side walls of the mounting slot regardless of fluid conditions. The seal device has two seal portions located to both sides of a bight shaped elastic portion which has a “U”-shaped cross section wherein the respective seal portions have a first side portion and a second side portion. The second side portions of the seal portions abut against each other in a symmetric manner in order to form a “W”-shaped seal body element. The end portions of the both second side portions of the seal body element are joined and seal surfaces are defined on the outer side surfaces of the both first side portions.Type: GrantFiled: August 11, 2004Date of Patent: October 31, 2006Assignee: Eagle Engineering Aerospace Co., Ltd.Inventors: Tetsuya Iguchi, Hidetoshi Kasahara, Jun Hiromatsu
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Patent number: 7121790Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).Type: GrantFiled: June 14, 2004Date of Patent: October 17, 2006Assignee: ALSTOM Technology Ltd.Inventors: Arkadi Fokine, Anatoli Kwasnikov, Igor Ossipov, Christoph Pfeiffer, Joerg Stengele, Sergey Trifonov
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Patent number: 7101147Abstract: A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to each other in a flow path between a region of high fluid pressure and a region of low fluid pressure. The sealing arrangement comprises at least two resilient sealing strips, each strip having a portion formed along at least part of its width to locate in a groove provided along adjacent faces of the relatively moveable parts. The remaining portion of each of the sealing strips has a substantially flat surface which, in operation, abuts a corresponding flat surface of an adjacent sealing strip, thereby forming a seal.Type: GrantFiled: March 11, 2004Date of Patent: September 5, 2006Assignee: Rolls-Royce PLCInventor: Julian G. Balsdon
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Patent number: 7090459Abstract: A seal having a first seal mechanism adapted for insertion between a first structure and a second structure, wherein the first structure is in communication with a first medium and the second structure is in communication with a second medium. The seal also includes a second seal mechanism, which is pressuringly biasable against the first seal mechanism and against the second structure by the second medium. In certain embodiments, a system has a first structure in communication with a first medium and a second structure houses a seal assembly between the first and second structures. The seal assembly includes an interface seal disposed against the first structure and a flexible seal pressuringly biased against the second structure and the interface seal by a second medium.Type: GrantFiled: March 31, 2004Date of Patent: August 15, 2006Assignee: General Electric CompanyInventors: Nitin Bhate, Raymond Edward Chupp, Kevin Bruce, Alberto Jose Negroni, Ronald Ralph Cairo
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Patent number: 7090224Abstract: Primary objective of the present invention is to effect a seal against assembly clearances formed between components which admit flows of high temperature fluids or are subjected to vibrations.Type: GrantFiled: September 1, 2004Date of Patent: August 15, 2006Assignee: Eagle Engineering Aerospace Co., Ltd.Inventors: Tetsuya Iguchi, Jun Hiromatsu, Toru Kono
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Patent number: 7086649Abstract: A gasket, sliding about the axis of rotation of a part to be brought closer to or to be spaced apart from another part with which it provides tightness through a pair of lips provided on a ring. The gasket includes a portion of the ring capable of bending to modify the clearance between the corresponding lip and the part, the pressure prevailing in an intermediate cavity, the balance of forces on the joint and hence the clearance and the leak flow rate allowed before the gasket, which is advantageous in particular in a case of ventilation gas for refrigerating an element of the machine in controlled operating conditions.Type: GrantFiled: October 24, 2002Date of Patent: August 8, 2006Assignee: SNECMA MoteursInventor: Daniel Georges Plona
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Patent number: 7070388Abstract: An inducer rotor rotatably mountable in an inducer for pressurizing fluid traveling through the inducer. The inducer rotor includes a hub. The hub has a central axis and a plurality of blades extending radially outward from the hub. Each blade extends from a root portion that is next to the hub, to a tip portion that is opposite the root. The rotor further includes a shroud extending circumferentially between each pair of adjacent blades within the plurality of blades. The shroud has an inner surface facing the central axis and an outer surface that is opposite the inner surface. Between the inner and outer surface of the shroud is defined a thickness. The shroud thickness varies circumferentially around the shroud.Type: GrantFiled: February 26, 2004Date of Patent: July 4, 2006Assignee: United Technologies CorporationInventors: Sen Y. Meng, David H. Loh
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Patent number: 7059821Abstract: A method to facilitate sealing between a rotary component and a stationary component is provided. The rotary component includes at least one bucket secured thereon, the bucket having a flow admission side and a flow exit side. The method includes coupling a spill strip in a gap defined between the rotary and stationary component, wherein the spill strip has a substantially flat contact surface, and coupling a cover to a radially outer tip of the bucket, wherein a protrusion extends from the bucket cover to contact the substantially flat contact surface of the spill strip.Type: GrantFiled: May 7, 2003Date of Patent: June 13, 2006Assignee: General Electric CompanyInventors: Alison Carol Farrell, Douglas Carl Hofer, Norman Douglas Lathrop, Raymond Kenneth Overbaugh, Jr., Kenneth James Robertson, Michael Joseph Boss
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Patent number: 7059829Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.Type: GrantFiled: February 9, 2004Date of Patent: June 13, 2006Assignee: Siemens Power Generation, Inc.Inventor: Chad Marcus Garner
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Patent number: 7040861Abstract: A method and apparatus for reducing self sealing flow in a combined cycle double flow steam turbine, the method and apparatus include providing a brush seal in a packing ring of a packing ring assembly at either end defining the double flow steam turbine.Type: GrantFiled: March 4, 2004Date of Patent: May 9, 2006Assignee: General Electric CompanyInventors: Samuel Gregory Clifford, Michael Joseph Boss, David Forrest Loy, Norman Douglas Lathrop
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Patent number: 6997677Abstract: A method and apparatus for assembling a steam turbine is provided. The method includes performing a finite element analysis to determine a cross-section of a sealing member, positioning the sealing member in a leakage path defined between an inner casing and an outer casing such that a leakage flow activates the sealing member. The apparatus includes a groove defined in a channel, a divider positioned in the channel such that a gap defined between the divider and the channel defines a leakage path, and a sealing member that extends at least partially within the groove and positioned to substantially prevent a flow though the leakage path.Type: GrantFiled: March 5, 2003Date of Patent: February 14, 2006Assignee: General Electric CompanyInventors: Jonathan Munshi, Bernard Arthur Couture