Resilient, Flexible, Or Resiliently Biased Patents (Class 415/174.2)
  • Publication number: 20120288361
    Abstract: A brush seal for use between a rotating component and a stationary component in a turbomachine is disclosed. The brush seal according to embodiments of this invention includes a set of bristles having a fixed end and a free end, wherein the fixed end is attached to the rotating component with a mechanical clamping element and the free end extends towards the stationary component, and wherein the set of bristles are angled axially at an axial angle with respect to the rotating component. In one embodiment, the fixed end of the set of bristles are wrapped at least partially around a core element and the clamping element partially surrounds the core element and the fixed end of the set of bristles, wherein the clamping element secures the fixed end of the set of bristles within a circumferential groove in the rotating component.
    Type: Application
    Filed: July 20, 2012
    Publication date: November 15, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Guoqiang Lu, Mehmet Demiroglu, Binayak Roy, Deepak Trivedi, Xiaoqing Zheng
  • Patent number: 8231340
    Abstract: A leaf seal 10 in a rotary machine is located between a higher pressure region 14 and a lower pressure region 16 of the machine. Blow-down forces are greater on the lower pressure side 16 of the leaf seal 10 than on its higher pressure side 14, resulting in greater inward deflection of the leaves 20 on the lower pressure side of the seal than on its higher pressure side, leading in turn to greater wear of the leaves and the contacting rotor surface 44 on the lower pressure side 16 of the seal. To counteract this, the free ends 36 of the leaves 20 can be given a tapered profile 42 to gradually reduce the length of each leaf 20 over its width ‘w’ from its higher pressure side 14 to its lower pressure side 16, so that the leaves 20 are free to deflect under the blow-down forces by the amount of their reduction in length (a maximum of ‘x’), before they contact the rotor surface.
    Type: Grant
    Filed: January 21, 2011
    Date of Patent: July 31, 2012
    Assignee: ALSTOM Technology Ltd.
    Inventor: Neil Howes
  • Publication number: 20120189435
    Abstract: According to one aspect of the invention, an assembly for preventing fluid flow between turbine components includes a shim and a first woven wire mesh layer that includes a first surface coupled to a first side of the shim and a second surface of the woven wire mesh layer opposite the first surface. The assembly also includes a first outer layer coupled to the second surface of the woven wire mesh layer, where the first outer layer includes a high temperature non-metallic material.
    Type: Application
    Filed: January 24, 2011
    Publication date: July 26, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Victor John Morgan, Rebecca Evelyn Hefner, Stephen Gerard Pope
  • Patent number: 8221062
    Abstract: A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
    Type: Grant
    Filed: January 14, 2009
    Date of Patent: July 17, 2012
    Assignee: General Electric Company
    Inventors: Gary Charles Liotta, Thomas Raymond Farrell
  • Patent number: 8215894
    Abstract: A seal assembly for a rotational assembly includes a first seal, a second seal and a crossover support. The crossover support includes a first geometry that interacts with the first seal and a second, different geometry that interacts with the second seal.
    Type: Grant
    Filed: November 13, 2007
    Date of Patent: July 10, 2012
    Assignee: United Technologies Corporation
    Inventors: Jonathan Logan Miller, Brian P. Cigal
  • Publication number: 20120171024
    Abstract: A fan module includes a frame; a fan wheel; and a bearing holding structure having a hollow bearing cup, an elastic member, and a bearing. The frame has a base, on a center of which the hollow bearing cup is formed. A portion of an inner wall surface of the hollow bearing cup is radially inward protruded, forming a shoulder portion between the inner wall surface and the protruded portion. The elastic member includes a first and a second section tightly bearing on the shoulder portion and the inner wall surface, respectively, and the bearing is tightly supported on the elastic member. The fan wheel has a shaft extended through the bearing and is therefore rotatably mounted on the base and located in the frame. With the elastic member, the bearing is tightly received in the hollow bearing cup without colliding therewith, and stable operation of the bearing is ensured.
    Type: Application
    Filed: January 2, 2011
    Publication date: July 5, 2012
    Applicant: ASIA VITAL COMPONENTS CO., LTD.
    Inventor: Wen-Hao Liu
  • Publication number: 20120156011
    Abstract: An air cycle machine includes a bearing housing with a shaft bore. A rotor shaft is arranged in the shaft bore and includes knife edges extending from the rotor shaft. A seal engages the shaft bore and includes an outer diameter and an inner diameter providing a seal land axially aligned with the knife edges. A radial clearance between the seal land and the knife edges is nominally 0.006 inch. The inner diameter is arranged between lateral sides of the seal that define a width. In one example, a tapered surface extending at an angle relative to the outer diameter from the lateral side to the seal land, the tapered surface facing the large end. The outer diameter to the inner diameter provides a first ratio of 1.25-1.28, and the inner diameter to the width provides a second ratio of 4.33-5.58.
    Type: Application
    Filed: December 21, 2010
    Publication date: June 21, 2012
    Inventors: Victoria S. Richardson, Lawrence Binek, Craig M. Beers
  • Patent number: 8182156
    Abstract: A gas turbine engine bearing cage assembly includes: a first bearing cage having: an annular first bearing support ring; an annular first mounting flange; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the first mounting flange, the first spring arms defining an outer diameter; and a second bearing cage having: an annular second bearing support ring; an annular second mounting ring, the second mounting ring defining an inner diameter greater that the outer diameter; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the second mounting ring, the second spring arms defining spaces therebetween. The bearing cages are sized such that the first bearing cage can be received within the second bearing cage. The spaces are positioned to receive the first spring arms, permitting independent flexing motion of the first and second spring arms.
    Type: Grant
    Filed: July 31, 2008
    Date of Patent: May 22, 2012
    Assignee: General Electric Company
    Inventors: Ray Harris Kinnaird, Ning Fang
  • Patent number: 8177495
    Abstract: A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.
    Type: Grant
    Filed: March 24, 2009
    Date of Patent: May 15, 2012
    Assignee: General Electric Company
    Inventors: Christopher Sean Bowes, Ian David Wilson
  • Patent number: 8157502
    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: Grant
    Filed: December 19, 2007
    Date of Patent: April 17, 2012
    Assignee: SNECMA
    Inventors: Emmanuel Edeline, Charles Marciquet, Laurent Fabbri, Fabien Wahl
  • Patent number: 8141879
    Abstract: A side seal for sealing the side edges of adjacent combustors of a turbine engine include extended ends. The extended ends of the side seal abut and seal against inner and outer circumferential seals to prevent leakage of combustion gases.
    Type: Grant
    Filed: July 20, 2009
    Date of Patent: March 27, 2012
    Assignee: General Electric Company
    Inventors: Krishna Kumar Venkataraman, Kevin Weston McMahan, Timur R. Repikov, Kara Edwards
  • Patent number: 8133003
    Abstract: Disclosed is a seal for a turbomachine including at least one fixed component located proximate to a rotating component of the turbomachine defining a clearance therebetween. At least one magnet is located at the at least one fixed component. The at least one magnet is, when activated, capable of moving the at least one fixed component thereby adjusting the clearance between the fixed component and the rotating component. Further disclosed is a turbomachine utilizing the seal and a method for adjusting a position of at least one fixed component of a turbomachine.
    Type: Grant
    Filed: September 26, 2008
    Date of Patent: March 13, 2012
    Assignee: General Electric Company
    Inventors: Michael Alan Davi, David Andrew Stasenko
  • Patent number: 8133014
    Abstract: A triple acting radial seal used as an interstage seal assembly in a gas turbine engine, where the seal assembly includes an interstage seal support extending from a stationary inner shroud of a vane ring, the interstage seal support includes a larger annular radial inward facing groove in which an outer annular floating seal assembly is secured for radial displacement, and the outer annular floating seal assembly includes a smaller annular radial inward facing groove in which an inner annular floating seal assembly is secured also for radial displacement. A compliant seal is secured to the inner annular floating seal assembly. The outer annular floating seal assembly encapsulates the inner annular floating seal assembly which is made from a very low alpha material in order to reduce thermal stress.
    Type: Grant
    Filed: August 17, 2009
    Date of Patent: March 13, 2012
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Todd A Ebert, John A Carella
  • Patent number: 8109717
    Abstract: Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine.
    Type: Grant
    Filed: August 17, 2007
    Date of Patent: February 7, 2012
    Assignee: United Technologies Corp.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Patent number: 8109716
    Abstract: Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.
    Type: Grant
    Filed: August 17, 2007
    Date of Patent: February 7, 2012
    Assignee: United Technologies Corp.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Publication number: 20120027574
    Abstract: An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.
    Type: Application
    Filed: July 27, 2010
    Publication date: February 2, 2012
    Applicant: United Technologies Corporation
    Inventors: Philip R. Belanger, Susan M. Tholen
  • Patent number: 8087872
    Abstract: The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header.
    Type: Grant
    Filed: March 23, 2010
    Date of Patent: January 3, 2012
    Assignee: General Electric Company
    Inventors: Mahendra Singh Mehra, Nestor Hernandez Sanchez
  • Patent number: 8079809
    Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.
    Type: Grant
    Filed: June 26, 2008
    Date of Patent: December 20, 2011
    Assignee: Honeywell International Inc.
    Inventors: Al Selder, Raymond A. Sutyak, Donald R. Piscopo, Joseph A. Olsen, III, Marc Schmittenberg
  • Patent number: 8047767
    Abstract: A high pressure first stage turbine and seal assembly are described. In one embodiment, a high pressure turbine section is provided. The turbine section includes at least one stage, at least one rotor and a bucket assembly. The bucket assembly includes a bucket and an attachment fixture. The stage has a high root reaction during operation. An intermediate space is between the bucket assembly and a stationary component of the turbine section. A seal is provided between the stationary member and the rotor to facilitate preventing leakage from the intermediate space toward an end of the stage. Steam balance holes are provided in the rotor or the bucket to facilitate feeding steam towards an end of the turbine stage.
    Type: Grant
    Filed: September 28, 2005
    Date of Patent: November 1, 2011
    Assignee: General Electric Company
    Inventor: Michael Earl Montgomery
  • Publication number: 20110182722
    Abstract: Fluid leakage from high to low pressure sides through an annular gap formed between constructional members of a turbocharger and extending radially of a turbine shaft can be prevented. The turbocharger has a sealing device for prevention of fluid leakage from high to low pressure sides through a radially extending annular gap 15 formed between a shroud 10 and a shroud-confronting portion 14 which constitute the turbocharger, the sealing device having a frustoconical disc spring seal member 24 arranged in a pressed manner in the gap 15 between the shroud 10 and the shroud-confronting portion 14.
    Type: Application
    Filed: July 3, 2008
    Publication date: July 28, 2011
    Applicant: IHI Corporation
    Inventor: Yoshimitsu Matsuyama
  • Publication number: 20110171012
    Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
    Type: Application
    Filed: October 14, 2010
    Publication date: July 14, 2011
    Inventors: Daniel Kent Vetters, Timothy Hoffmann, Steven Arlen Klusman
  • Patent number: 7938616
    Abstract: A dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.
    Type: Grant
    Filed: October 5, 2007
    Date of Patent: May 10, 2011
    Assignee: SNECMA
    Inventors: Laurent Gille, Serge Rene Morreale
  • Patent number: 7918643
    Abstract: A compressor of a gas turbine engine comprises blades 2, 4 provided on blade platforms 8, 12 of a rotor. Stator vanes 20 lie between the blades 2, 4 and are connected to a vane support structure 22. Sealing rings 38 are secured to the vane support structure 22 to restrict air flow into stator wells 36 on each side of the vane support structure 22. The sealing rings 38 are made from a flexible material so that they deflect on installation of the vane support structure 22 in a direction radially inwards between the adjacent blade platforms 8, 12.
    Type: Grant
    Filed: June 4, 2007
    Date of Patent: April 5, 2011
    Assignee: Rolls-Royce plc
    Inventor: Kevin J Weaver
  • Publication number: 20110064566
    Abstract: The invention relates to a device for impeller sealing in centrifugal pumps for fluid media, by means of which the gap between pump housing (1) and at least one impeller (2) is completely sealed against a transport of material from the pressure side (3) of impeller (2) to the suction side (4) thereof. According to the invention, a sealing ring comprising a rigid pressure ring (7) as well as an annular elastic sealing lip (8) joined with pressure ring (7) is disposed in pump housing (1) between pressure side (3) and suction side (4), whereby, when the centrifugal pump is in operation, sealing lip (8) is applied in sliding manner over the entire periphery of impeller (2) on a sliding surface (6) formed on impeller (2) in the region of impeller intake (5). For this purpose, the sealing ring is positioned in pump housing (1) by means of an adjusting member (9) and its sealing lip (8) inclined against said sliding surface (6) is pre-stressed.
    Type: Application
    Filed: May 15, 2009
    Publication date: March 17, 2011
    Inventor: Uwe Wuerdig
  • Patent number: 7901186
    Abstract: A seal assembly (60) for sealing first and second static parts (40A, 40B) with opposed slots (44A, 44B) together forming a pocket (46). The seal assembly (60) comprises a floor strip (70) positioned adjacent the pocket's floor (48) and a ceiling strip (80) positioned adjacent the pocket's ceiling (50). A connection (90) of the strips' central portions (72, 82) provides a flat hinge between cooperating hinge portions (76, 86). A first set of the hinge portions (76A-86A) converge for insertion into the first slot (44A) and a second set of hinge portions (76B-96B) converge for insertion into the second slot (44B). After such slot insertion and pocket installation, the converged hinge portions (76A-86A, 76B-86B) resiliently diverge within the pocket to seat the floor strip's end portions (74A, 74B) against the pocket's floor (48) and to seat the ceiling strip's end portions (84A, 84B) against the pocket's ceiling (50).
    Type: Grant
    Filed: September 12, 2007
    Date of Patent: March 8, 2011
    Assignee: Parker Hannifin Corporation
    Inventors: Kenneth W. Cornett, Christopher D. Mahoney
  • Publication number: 20110033283
    Abstract: A turbomachine rotor including a disc including a rim and axial slots machined in the rim for the individual housing of blades, a ring being attached to one face of the rim, the ring being pierced with holes in the axial continuation of the slots, at least some of the holes in the continuation of the slots including a plug. The plug includes a first half-plug made of a first wear-resistant material and a second half-plug made of a second material, one of the two half-plugs bearing on one side of the ring and the other bearing on the other side of the ring and being connected to one another through the hole. The plug is configured to form an anti-wear device.
    Type: Application
    Filed: April 7, 2009
    Publication date: February 10, 2011
    Applicants: SNECMA, Carbone Lorraine Composants
    Inventors: Thomas Chrzastek, Jean-Bernard Forgue, Dominique Gaveau, Patrick Jean-Louis Reghezza, Nicolas Christian Triconnet
  • Publication number: 20110020113
    Abstract: A seal structure is provided for preventing leakage of gases across a gap between first and second components in a turbine engine. The seal structure is adapted to be received in first and second adjacent slots provided in the first and second components. The seal structure may comprise: a wear resistant layer; and a deformable layer defined by a material having one of a varying density and a varying porosity.
    Type: Application
    Filed: July 22, 2009
    Publication date: January 27, 2011
    Inventor: Alexander R. Beeck
  • Publication number: 20110014035
    Abstract: A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.
    Type: Application
    Filed: June 29, 2010
    Publication date: January 20, 2011
    Inventors: Yoshitaka KOJIMA, Hideyuki Arikawa, Akira Mebata, Hiroyuki Doi, Hajime Toriya, Kenjiro Narita
  • Patent number: 7854584
    Abstract: A rotary machine includes a machine rotor, a bearing coupled to the machine rotor, a machine stator, and a sealing device disposed between the machine rotor and the machine stator. The sealing device includes a dry gas seal and first and second seals disposed between the dry gas seal and the bearing. One or both of the first and second seals includes a brush seal or more specifically a brush seal including a plurality of non-metallic fibers.
    Type: Grant
    Filed: May 24, 2007
    Date of Patent: December 21, 2010
    Assignee: General Electric Company
    Inventors: Roderick Mark Lusted, Christopher Edward Wolfe, Eric John Ruggiero, Gabriele Mariotti
  • Patent number: 7832734
    Abstract: A seal arrangement for a turbo-engine, for sealing a peripheral gap between a rotor and a stator is provided. The stator a seal holder provided with at least one groove for respectively receiving a segmented, dynamic seal. Segments of the dynamic seal are made up of a plurality of brush seal segments, and free ends of bristles of the brush seal segments extend in the radial direction project from the respective groove and lie on the rotor. The or every groove for receiving the brush-type seal segments is designed without an undercut, the brush-type seal segments being received in the respective groove without an undercut in a positive manner.
    Type: Grant
    Filed: February 8, 2006
    Date of Patent: November 16, 2010
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Beichl, Alfons Gail
  • Patent number: 7827685
    Abstract: A seal and method of making seals utilises folds in order to form creases in a length of material such that the creases reinforce individual seal elements or surfaces whilst perforations or slots in a seal edge allow air leakage from one side of the seal element or surface to the other. Thus, air pressurisation can take place between spaced seal elements or surfaces and this allows air flotation or riding of a rotating component relative to a static housing component. The perforations are typically graduated from the seal edge in order to provide the best pressurisation and air-riding effect for proximity or gap control between the sealing edge and the rotating component surface. The slots effectively provide flexibility to the sealing edge such that the seal component emulates a brush seal.
    Type: Grant
    Filed: June 1, 2005
    Date of Patent: November 9, 2010
    Assignee: Rolls-Royce plc
    Inventor: Alison J McMillan
  • Publication number: 20100270747
    Abstract: The invention provides, in one aspect, a brush seal comprising brush seal bristles made up of component brush seal filaments. The component brush seal filaments comprise a polyether ketone comprising structural units derived from a diaryl ketone and a diphenolic compound and having a glass transition temperature in excess of 100° C. In a particular embodiment, the component brush seal filaments comprise PEEK. The novel brush seals provided by the present invention present a number of advantages over conventional non-metallic brush seals comprising KEVLAR filaments, such as enhanced friction characteristics and greater stability to fluid lubricants comprising groups reactive with the amide moieties present in aramid filaments such as KEVLAR.
    Type: Application
    Filed: April 24, 2009
    Publication date: October 28, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Farshad Ghasripoor, Biao Fang, Eric John Ruggiero, Vasanth Srinivasa Kothnur
  • Publication number: 20100254807
    Abstract: A seal plate for a turbine engine is provided. The turbine engine has a central axis. The seal plate comprises a forward face extending radially from the central axis. The forward face comprises a flat portion extending circumferentially around the central axis, and a front flow discourager coupled to the flat portion and extending outward from the flat portion.
    Type: Application
    Filed: April 7, 2009
    Publication date: October 7, 2010
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Steve Halfmann, Brandan Wakefield
  • Publication number: 20100239415
    Abstract: A spring assembly for a retractable turbine rotor seal supported in an arcuate segment may include in one embodiment a first radially inner restraining plate having a lower surface adapted to engage a surface of a turbine stator, and a flat upper surface provide with an upstanding hub; a second radially outer restraining plate having a flat lower surface and an upper surface adapted to engage a surface of the arcuate segment, the radially outer restraining plate formed with an opening receiving the upstanding hub; and at least one spring telescoped over the upstanding hub and exerting a radially outward biasing force on the second radially outer restraining plate, and adapted to exert a radially outward retracting force on the arcuate segment.
    Type: Application
    Filed: March 20, 2009
    Publication date: September 23, 2010
    Applicant: General Electric Company
    Inventors: Norman Arnold TURNQUIST, Shorya nmn AWTAR, Mustafa GURSOY, Karatik Mangudi VARADARAJAN
  • Patent number: 7798769
    Abstract: A ceramic seal element (200) for use in a turbo-machine comprises a first, rigid portion (210) comprising ceramic fibers (212) bound within a ceramic matrix binder (214), a second, flexible portion (220) comprising ceramic fibers (222), and a third, rigid portion (230) comprising ceramic fibers (232) bound within a ceramic matrix binder (234). Ceramic fibers (222) retain a desired flexibility because they are not bound in ceramic matrix binder. In some embodiments the ceramic fibers (212, 222, 232) are stacked as horizontally disposed layers (225). Also, the fibers (212, 222, 232) of any layer (225) comprise bundles of fibers wherein some of the bundles extend continuously across portions (210, 220, 230). An alternative sealing element (300) comprises a first, rigid portion (310) comprising ceramic fibers (312) that are bound within a ceramic matrix binder (314), and a second, flexible portion (320) that comprises ceramic fibers (313) that retain a desired flexibility. Methods of manufacture are disclosed.
    Type: Grant
    Filed: February 15, 2007
    Date of Patent: September 21, 2010
    Assignee: Siemens Energy, Inc.
    Inventor: Douglas A. Keller
  • Patent number: 7731478
    Abstract: Methods and apparatus for a packing ring segment assembly for sealing a turbine gas path are provided. The assembly includes a sealing portion including radially inwardly directed teeth, and a dovetail mounting portion including a hollowed out portion including a biasing member internal to the packing ring segment. The biasing member is coupled to the packing ring segment and configured to engage a pair of annular shoulders of a dovetail groove in the turbine such that the packing ring segment is biasing radially outward at relatively low turbine loads and low working pressure, and at relatively high turbine loads and high working pressure a working fluid overcomes the radial biasing member forces and urge the packing ring segment radially inward.
    Type: Grant
    Filed: May 25, 2006
    Date of Patent: June 8, 2010
    Assignee: General Electric Company
    Inventors: Richard Chevrette, Frederick G. Baily
  • Patent number: 7726940
    Abstract: Assembly of segmented seals can be problematic in areas of limited space for an introductory tapered mandrel and where there are the problems with damage to the seal surfaces 23, 24. By the present method and arrangement, a seal formed from segments 22 is expanded to an expanded state and then retained at that state by the use of a sacrificial material 26 in the gaps 25 between the segments 22 opened by expansion. The sacrificial material 26 is typically a low melting temperature wax and so is removed when the seal arrangement reaches its operating temperature.
    Type: Grant
    Filed: August 4, 2006
    Date of Patent: June 1, 2010
    Assignee: Rolls-Royce PLC
    Inventor: Guy David Snowsill
  • Patent number: 7726936
    Abstract: Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.
    Type: Grant
    Filed: July 25, 2006
    Date of Patent: June 1, 2010
    Assignee: Siemens Energy, Inc.
    Inventors: Douglas A. Keller, Steven J. Vance, Christian X. Campbell
  • Publication number: 20100068042
    Abstract: A brush seal for a turbo-machine for sealing a gap between a rotating and a stationary component is disclosed. Elastically flexible bristles are arranged in a plurality of rows that are adjacent to each other. A film or a disk is arranged between at least two rows of bristles, the film or the disk extending in the longitudinal direction of said bristles.
    Type: Application
    Filed: August 13, 2007
    Publication date: March 18, 2010
    Inventors: Stefan Brück, Matthias Neef, Erik Sulda, Norbert Sürken
  • Patent number: 7651317
    Abstract: A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.
    Type: Grant
    Filed: June 28, 2006
    Date of Patent: January 26, 2010
    Assignee: SNECMA
    Inventors: Gilles Alain Marie Charier, Franck Christian Conan, Thomas Julien Roland Earith, Marc Leandri
  • Publication number: 20100008769
    Abstract: A sealing system for sealing a gap between a dovetail tab of a bucket and a rotor. The sealing system may include a sealing slot positioned about the dovetail tab and a pivot plate positioned within the sealing slot. The sealing slot may include a pivot point and a rest ledge such that the pivot plate pivots about the pivot point and into the gap when the bucket rotates.
    Type: Application
    Filed: July 8, 2008
    Publication date: January 14, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Brian P. Arness, Louis Veltre, Ariel Kelsey Coleman Harter, John D. Ward
  • Patent number: 7637719
    Abstract: A sealing arrangement, especially for a flow engine, for non-hermetically sealing a gap (12) between a rotor (10) and a stator (11), which comprises a seal having a plurality of sealing elements that are fixed to a sealing element support, said sealing element support being at least partially disposed in a receptacle (16) which is defined by a supporting element (17) and a cover element (18) is disclosed. The sealing element support is configured as a ring that is interrupted once or several times. Free ends (19, 20) of the sealing element support overlap in the area of interruptions in the circumferential direction. The contours of the supporting element (17) and the cover element (18) are adapted to the contours of the sealing element support and the sealing elements (15). At least one end (19, 20) of every part of the sealing element support is associated with an antirotation device (21, 22).
    Type: Grant
    Filed: August 3, 2005
    Date of Patent: December 29, 2009
    Assignee: MTU Aero Engines GmbH
    Inventor: Wilhelm Graebeldinger
  • Patent number: 7597535
    Abstract: A fan module adapted to be assembled onto a system frame includes a body, a fan assembly, and at least two connecting elements. The body has an accommodating space. The fan assembly is disposed in the accommodating space. The connecting elements are protruded from the body, and the connecting elements are inserted to and connected with a plurality of holes of the system frame.
    Type: Grant
    Filed: June 22, 2006
    Date of Patent: October 6, 2009
    Assignee: Delta Electronics, Inc.
    Inventors: Chun-Nan Wu, Kuo-Tung Hsu
  • Patent number: 7584924
    Abstract: A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array.
    Type: Grant
    Filed: January 31, 2007
    Date of Patent: September 8, 2009
    Assignee: Go Aircraft Ltd.
    Inventor: Gordon Y. W. Ow
  • Publication number: 20090206554
    Abstract: A method is provided for assembling a turbine engine. The method includes providing a retro-fit seal ring assembly that includes a plurality of unitary, arcuate ring segments that are circumferentially-spaced about a center axis of the ring assembly. Each of the plurality of ring segments includes a body and at least one integrally formed tooth that extends radially inward therefrom. The methods also includes extending at least one fastener through the body of each of the plurality of ring segments, and removably coupling each of the plurality of ring segments to an outer surface of a stationary component within the turbine engine using the at least one fastener.
    Type: Application
    Filed: February 18, 2008
    Publication date: August 20, 2009
    Inventors: Mark Kevin Bowen, Steven Sebastian Burdgick, Jason Paul Mortzheim, William Edward Adis, Eric Diederich Iken
  • Patent number: 7571614
    Abstract: 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: Grant
    Filed: March 23, 2005
    Date of Patent: August 11, 2009
    Assignee: Snecma
    Inventors: Claude Lejars, Marica Mesic, Bruce Pontoizeau, Alexandre Roy, Patrice Suet
  • Patent number: 7572099
    Abstract: 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: Grant
    Filed: July 6, 2006
    Date of Patent: August 11, 2009
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Publication number: 20090196742
    Abstract: 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: Application
    Filed: February 4, 2008
    Publication date: August 6, 2009
    Inventors: Norman A. Turnquist, Frederick G. Baily, Bernard A. Couture, JR., Jason P. Mortzheim, Sean D. Feeny, William E. Adis, Shorya Awtar, Nikhil K. Verma
  • Patent number: 7562880
    Abstract: 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: Grant
    Filed: February 9, 2004
    Date of Patent: July 21, 2009
    Assignee: Siemens Energy, Inc.
    Inventors: Hubertus Edward Paprotna, David A. Little
  • Publication number: 20090169376
    Abstract: 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: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka, Peter Robert Griffiths