Resilient, Flexible, Or Resiliently Biased Patents (Class 415/174.2)
  • Publication number: 20090169370
    Abstract: 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: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
  • Publication number: 20090169369
    Abstract: A turbine nozzle segment includes a band having a plurality of circumferentially spaced apart tabs and a single airfoil extending from the band.
    Type: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
  • Patent number: 7549841
    Abstract: 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: Grant
    Filed: September 1, 2006
    Date of Patent: June 23, 2009
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Walter Marussich
  • Patent number: 7549835
    Abstract: 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: Grant
    Filed: July 7, 2006
    Date of Patent: June 23, 2009
    Assignee: Siemens Energy, Inc.
    Inventor: Dieter Brillert
  • Patent number: 7540708
    Abstract: 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: Grant
    Filed: June 30, 2006
    Date of Patent: June 2, 2009
    Assignee: General Electric Company
    Inventors: Kurt Neal Laurer, Kevin Joseph Barh, Bernard Arthur Couture, Jason Paul Mortzheim
  • Publication number: 20090136339
    Abstract: A method for assembling a rotary machine is provided. The method includes providing at least one seal assembly that includes at least one annular seal housing defined by a top wall, a front wall, and a rear wall, that are connected together such that a cavity is defined within the housing, coupling a plurality of flexible plates within the cavity such that the plates are axially-spaced from the front wall and the rear wall within the cavity, coupling at least one side plate to the at least one annular seal housing such that the at least one side plate is moveable with respect the front wall and the rear wall, and coupling the at least one sealing assembly within a rotary machine to facilitate sealing between a rotary component and a stator component.
    Type: Application
    Filed: November 27, 2007
    Publication date: May 28, 2009
    Inventors: Nikhil Kumar Verma, Jason Paul Mortzheim, Yogesh Sathe, Hrishikesh Vishvas Deo
  • Publication number: 20090087307
    Abstract: 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: Application
    Filed: September 28, 2007
    Publication date: April 2, 2009
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Donald I. Takeuchi, Bradley R. Tucker, Yates Y. Wong, Mingfong F. Hwang
  • Patent number: 7484927
    Abstract: 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: Grant
    Filed: April 14, 2006
    Date of Patent: February 3, 2009
    Assignee: General Electric Company
    Inventors: Richard J. Chevrette, Flor Rivas, Frederick G. Baily, William E. Adis, Mark E. Kelly, Bernard A. Couture, Kurt N. Laurer
  • Publication number: 20090028696
    Abstract: 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: Application
    Filed: July 21, 2008
    Publication date: January 29, 2009
    Inventors: Thomas P. Gannett, Joel D. Citron
  • Publication number: 20090028695
    Abstract: 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: Application
    Filed: July 21, 2008
    Publication date: January 29, 2009
    Inventors: Thomas P. Gannett, Joel D. Citron
  • Publication number: 20080232956
    Abstract: 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: Application
    Filed: January 12, 2005
    Publication date: September 25, 2008
    Inventors: Stefan Baldauf, Hans-Thomas Bolms, Michael Handler, Christian Lerner
  • Publication number: 20080170937
    Abstract: 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: Application
    Filed: December 19, 2007
    Publication date: July 17, 2008
    Applicant: SNECMA
    Inventors: Emmanuel Edeline, Charles Marciquet, Laurent Fabbri, Fabien Wahl
  • Patent number: 7367776
    Abstract: 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: Grant
    Filed: January 26, 2005
    Date of Patent: May 6, 2008
    Assignee: General Electric Company
    Inventors: Robert Joseph Albers, Rafael Ruiz, Marcia Boyle, Christopher Charles Glynn
  • Patent number: 7347662
    Abstract: 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: Grant
    Filed: October 3, 2005
    Date of Patent: March 25, 2008
    Assignee: Rolls-Royce plc
    Inventor: Julian Glyn Balsdon
  • Patent number: 7344357
    Abstract: 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: Grant
    Filed: September 2, 2005
    Date of Patent: March 18, 2008
    Assignee: General Electric Company
    Inventors: Bernard Arthur Couture, Jr., Flor Del Carmen Rivas, Mark Edward Kelly, Jason Paul Mortzheim
  • Patent number: 7344356
    Abstract: 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: Grant
    Filed: August 10, 2005
    Date of Patent: March 18, 2008
    Assignee: Wood Group ESP, Inc.
    Inventors: Steven Alan Howell, Edward Gross
  • Patent number: 7338253
    Abstract: 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: Grant
    Filed: September 15, 2005
    Date of Patent: March 4, 2008
    Assignee: General Electric Company
    Inventor: Tagir Robert Nigmatulin
  • Patent number: 7334985
    Abstract: 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: Grant
    Filed: October 11, 2005
    Date of Patent: February 26, 2008
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Dmitriy Romanov, Jeremy Drake, Gary Grogg, Gregory E. Reinhardt
  • Patent number: 7334984
    Abstract: 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: Grant
    Filed: December 24, 2004
    Date of Patent: February 26, 2008
    Assignee: Heico Corporation
    Inventors: Frederick J. Stine, James W. Tucker, Stephen J. Szpunar
  • Publication number: 20080008582
    Abstract: 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: Application
    Filed: July 7, 2006
    Publication date: January 10, 2008
    Inventors: John T. Pickens, Tuy Tran, Allan R. Penda
  • Publication number: 20080003100
    Abstract: 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: Application
    Filed: June 30, 2006
    Publication date: January 3, 2008
    Inventors: Kurt Neal Laurer, Kevin Joseph Barh, Bernard Arthur Couture, Jason Paul Mortzheim
  • Patent number: 7309210
    Abstract: 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: Grant
    Filed: December 17, 2004
    Date of Patent: December 18, 2007
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris
  • Patent number: 7287956
    Abstract: 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: Grant
    Filed: December 22, 2004
    Date of Patent: October 30, 2007
    Assignee: General Electric Company
    Inventors: Robert James Bracken, Sterling Ray Hathaway, David Orus Fitts, Ron W. Korzun, Laurence Scott Duclos, William Edward Adis, Mark William Kowalczyk, Bernard Arthur Couture
  • Patent number: 7261515
    Abstract: 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: Grant
    Filed: August 10, 2005
    Date of Patent: August 28, 2007
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Shin Nishimoto, Tanehiro Shinohara, Hidekazu Uehara, Takashi Nakano
  • Patent number: 7229247
    Abstract: An integrated duct and baffle arrangement employing a hairpin transition area such that the construction is adapted to flex under thermal conditions.
    Type: Grant
    Filed: August 27, 2004
    Date of Patent: June 12, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Martin Jutras
  • Patent number: 7229246
    Abstract: 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: Grant
    Filed: September 30, 2004
    Date of Patent: June 12, 2007
    Assignee: General Electric Company
    Inventors: 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
  • Patent number: 7217089
    Abstract: 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: Grant
    Filed: January 14, 2005
    Date of Patent: May 15, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Martin Jutras
  • Patent number: 7201560
    Abstract: 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: Grant
    Filed: December 6, 2004
    Date of Patent: April 10, 2007
    Assignee: General Electric Company
    Inventors: Charles Thomas O'Clair, Richard Jon Chevrette, Carl A. Greco, Jeyaruban Amirtharajah
  • Patent number: 7201561
    Abstract: 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: Grant
    Filed: May 18, 2005
    Date of Patent: April 10, 2007
    Assignee: United States of America, as represented by the Secretary of Army
    Inventors: Wayne C. Parsons, Tracy A. Conklin
  • Patent number: 7192246
    Abstract: 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: Grant
    Filed: December 15, 2004
    Date of Patent: March 20, 2007
    Assignee: Rolls-Royce plc
    Inventors: Christopher Wright, Christopher J Finch
  • Patent number: 7186074
    Abstract: 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: Grant
    Filed: May 13, 2004
    Date of Patent: March 6, 2007
    Assignee: Alstom Technology, Ltd.
    Inventors: David Paul Blatchford, Richard Martin Bridge, Philip David Hemsley, Alan Hesketh, Adrian Lord
  • Patent number: 7175387
    Abstract: 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: Grant
    Filed: March 25, 2004
    Date of Patent: February 13, 2007
    Assignee: Alstom Technology Ltd.
    Inventors: Erhard Kreis, Markus Oehl, Ulrich Rathmann
  • Patent number: 7172388
    Abstract: 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: Grant
    Filed: August 24, 2004
    Date of Patent: February 6, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Remy Synnott
  • Patent number: 7156613
    Abstract: 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: Grant
    Filed: December 10, 2004
    Date of Patent: January 2, 2007
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Winfried-Hagen Friedl
  • Patent number: 7128323
    Abstract: 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 ā€œUā€-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 ā€œWā€-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: Grant
    Filed: August 11, 2004
    Date of Patent: October 31, 2006
    Assignee: Eagle Engineering Aerospace Co., Ltd.
    Inventors: Tetsuya Iguchi, Hidetoshi Kasahara, Jun Hiromatsu
  • Patent number: 7121790
    Abstract: 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: Grant
    Filed: June 14, 2004
    Date of Patent: October 17, 2006
    Assignee: ALSTOM Technology Ltd.
    Inventors: Arkadi Fokine, Anatoli Kwasnikov, Igor Ossipov, Christoph Pfeiffer, Joerg Stengele, Sergey Trifonov
  • Patent number: 7101147
    Abstract: 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: Grant
    Filed: March 11, 2004
    Date of Patent: September 5, 2006
    Assignee: Rolls-Royce PLC
    Inventor: Julian G. Balsdon
  • Patent number: 7090459
    Abstract: 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: Grant
    Filed: March 31, 2004
    Date of Patent: August 15, 2006
    Assignee: General Electric Company
    Inventors: Nitin Bhate, Raymond Edward Chupp, Kevin Bruce, Alberto Jose Negroni, Ronald Ralph Cairo
  • Patent number: 7090224
    Abstract: 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: Grant
    Filed: September 1, 2004
    Date of Patent: August 15, 2006
    Assignee: Eagle Engineering Aerospace Co., Ltd.
    Inventors: Tetsuya Iguchi, Jun Hiromatsu, Toru Kono
  • Patent number: 7086649
    Abstract: 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: Grant
    Filed: October 24, 2002
    Date of Patent: August 8, 2006
    Assignee: SNECMA Moteurs
    Inventor: Daniel Georges Plona
  • Patent number: 7070388
    Abstract: 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: Grant
    Filed: February 26, 2004
    Date of Patent: July 4, 2006
    Assignee: United Technologies Corporation
    Inventors: Sen Y. Meng, David H. Loh
  • Patent number: 7059821
    Abstract: 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: Grant
    Filed: May 7, 2003
    Date of Patent: June 13, 2006
    Assignee: General Electric Company
    Inventors: Alison Carol Farrell, Douglas Carl Hofer, Norman Douglas Lathrop, Raymond Kenneth Overbaugh, Jr., Kenneth James Robertson, Michael Joseph Boss
  • Patent number: 7059829
    Abstract: 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: Grant
    Filed: February 9, 2004
    Date of Patent: June 13, 2006
    Assignee: Siemens Power Generation, Inc.
    Inventor: Chad Marcus Garner
  • Patent number: 7040861
    Abstract: 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: Grant
    Filed: March 4, 2004
    Date of Patent: May 9, 2006
    Assignee: General Electric Company
    Inventors: Samuel Gregory Clifford, Michael Joseph Boss, David Forrest Loy, Norman Douglas Lathrop
  • Patent number: 6997677
    Abstract: 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: Grant
    Filed: March 5, 2003
    Date of Patent: February 14, 2006
    Assignee: General Electric Company
    Inventors: Jonathan Munshi, Bernard Arthur Couture
  • Patent number: 6984106
    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.
    Type: Grant
    Filed: January 8, 2004
    Date of Patent: January 10, 2006
    Assignee: General Electric Company
    Inventor: Jeff Brian Thompson
  • Patent number: 6979172
    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.
    Type: Grant
    Filed: January 2, 2003
    Date of Patent: December 27, 2005
    Assignee: Saint-Gobain Ceramics & Plastics, Inc.
    Inventor: Sprague Benjamin Mackenzie
  • Patent number: 6932567
    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.
    Type: Grant
    Filed: December 19, 2002
    Date of Patent: August 23, 2005
    Assignee: General Electric Company
    Inventors: Robert Joseph Albers, Marcia Jean Boyle, Rafael Ruiz
  • Patent number: 6923618
    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.
    Type: Grant
    Filed: September 26, 2003
    Date of Patent: August 2, 2005
    Inventor: William Hudgens
  • Patent number: 6921245
    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.
    Type: Grant
    Filed: February 11, 2003
    Date of Patent: July 26, 2005
    Assignee: Envirotech Pumpsystems, Inc.
    Inventor: Joel Quinn