And Axial Or Circumferential Expansion Patents (Class 415/138)
  • Patent number: 11073038
    Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.
    Type: Grant
    Filed: July 19, 2019
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 11021980
    Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.
    Type: Grant
    Filed: April 23, 2019
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: John T. Ols, Steven D. Porter
  • Patent number: 10975767
    Abstract: Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: April 13, 2021
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Koji Terauchi, Daisuke Uemura, Takuya Ikeguchi
  • Patent number: 10934873
    Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.
    Type: Grant
    Filed: November 7, 2018
    Date of Patent: March 2, 2021
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, John Patrick Pollinger
  • Patent number: 10927677
    Abstract: Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.
    Type: Grant
    Filed: March 15, 2018
    Date of Patent: February 23, 2021
    Assignee: General Electric Company
    Inventors: Darrell Glenn Senile, Matthew Mark Weaver, Alexander Martin Sener
  • Patent number: 10920609
    Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: February 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Hélène Myriam Condat, Stéphane Pierre Guillaume Blanchard, Sylvain Yves Jean Duval
  • Patent number: 10907540
    Abstract: A turbine section for a gas turbine engine includes an independently controllable wheel downstream of the first static vane structure and a turbine rotor downstream of the independently controllable wheel. A method of generating thrust for a gas turbine engine, includes rotating a independently controllable wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: February 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Jacob Shubinski
  • Patent number: 10858953
    Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include a blade track coupled with a turbine casing with a clip. The system may further include a nozzle guide vane coupled to the turbine casing. A cavity may be formed by an end of the blade track, the clip, and a portion of the nozzle guide vane. A heat shield may be positioned between the clip and the end of the blade track in the cavity such that an edge of the heat shield and the portion of the nozzle guide vane form a gap. The heat shield and the nozzle guide vane may be positioned such that the gap closes in response to the heat shield and the nozzle guide vane thermally expanding.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: December 8, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Marcel Schmidt
  • Patent number: 10858954
    Abstract: A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.
    Type: Grant
    Filed: October 18, 2018
    Date of Patent: December 8, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Bazot, Jérémy Philippe Pierre Edynak, Farhana Hussain, Fanny Marie Libes
  • Patent number: 10837319
    Abstract: A turbine center frame for a gas turbine having a plurality of first components and a plurality of second components alternately mutually adjacently disposed in circumferential direction and bounding a hot gas-conducting flow channel in radial direction, the first components each having two first overlapping portions, and the second components each having two second overlapping portions. In a transition from a first component to a second component, one of the first overlapping portions and one of the second overlapping portions overlap. A centering element, against which, the first components and the second components are braced along the circumferential direction and in the radial direction, centers the first components and the second components relative to a central axis of the turbine center frame.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: November 17, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Boeck
  • Patent number: 10830071
    Abstract: A multi-piece part includes multiple pieces fabricated via different types of fabrication processes, wherein the multiple parts are configured to be coupled to one another to form the assembly. At least one of the multiple parts is fabricated via an additive manufacturing method. The multi-piece part also includes a holder assembly that couples and holds together the multiple pieces of the multi-piece part, wherein the holder assembly comprises a reversible, mechanical-type coupling.
    Type: Grant
    Filed: January 23, 2017
    Date of Patent: November 10, 2020
    Assignee: General Electric Company
    Inventors: Srikanth Chandrudu Kottilingam, David Edward Schick, Jon Conrad Schaeffer, Steven J. Barnell, Brian Lee Tollison, Yan Cui
  • Patent number: 10801369
    Abstract: An intermediate casing for a turbine engine, comprising at least one central hub and one shroud (12) which are positioned concentrically, and mutually mechanically connected by structural arms (11), with such casing comprising at least one sealing part (13) attached between the shroud (12) and a structural arm (11), with the sealing part (13) including at least one metal core and one seal.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: October 13, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Simon Pierre Claude Charbonnier, Patrick Jean-Louis Reghezza, Julien Roset, Yann Christophe Maurice Sarazin
  • Patent number: 10746055
    Abstract: An assembly of at least two members. One of the members supports the other member, the assembly defining an axial direction, a radial direction, and a circumferential direction, an inner member of the at least two members being received radially inside an outer member of the at least two members, wherein the inner member and the outer member am attached to each other by a support arrangement, the support arrangement including at least one floating support assembly as a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at the outer member. A displacement of support points in a radial direction results in an interrelated relative displacement of the support points in an axial direction end vice versa.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: August 18, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Meisam Sistaninia, Diego Ugel, Giovanni Cataldi, Martin Schaefer
  • Patent number: 10727656
    Abstract: A cable conduit may comprise a head end, a sleeve having a foot end, a boot, and a split grommet having a first upper surface, wherein the head end is coupled to the sleeve opposite the foot end, wherein the boot comprises a first flange and is coupled to the foot end, wherein the head end comprises a second flange having a second upper surface and a cutout penetrating into an interior volume of the sleeve, and wherein the split grommet is coupled about the inner diameter of the cutout.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher Waitkus, Mark T. McAuliffe, Randall Lee Greenberg, Colby S. Dunn
  • Patent number: 10655490
    Abstract: A seal arrangement comprising a first and second components made of a ceramic fiber composite material and comprising first and second bounding sections with first and second overlapping sections and first and second securing sections which are connected to and projects from the first and second bounding sections. The first and second overlapping sections are arranged at least partially overlapping such that the first and second bounding sections form an essentially continuous bounding surface. A separation between the first and second securing sections is at least partially sealed by a seal element which comprises at least one first sheet-metal element arranged along the first securing section and at least partially bridging the separation between the first and second securing sections.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: May 19, 2020
    Assignee: MTU AERO ENGINES AG
    Inventor: Alexander Boeck
  • Patent number: 10612419
    Abstract: A steam turbine includes: a stator vane disposed in a cylinder inside a casing through which steam flows from an upstream side toward a downstream side; and a stationary support that supports the stator vane relative to the casing. The stationary support includes: a first supporting body fixed to the casing, a second supporting body that connects the stator vane to the first supporting body; and a replacement body detachably disposed between the first supporting body and the second supporting body on the upstream side.
    Type: Grant
    Filed: February 23, 2016
    Date of Patent: April 7, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Katsumi Terada, Hiroaki Irikawa, Yuichi Sasaki
  • Patent number: 10563529
    Abstract: According to an embodiment, a turbine comprises: a cylindrical casing; and turbine stator blades arranged in the casing along a circumferential direction. The turbine stator blades each includes: a blade effective part; a coolant flow path through which a coolant flows in the blade effective part to cool the blade effective part; an outer ring sidewall provided on an outer periphery of the blade effective part; an inner ring sidewall provided on an inner periphery of the blade effective part; and a contact part provided at an end part of the inner ring sidewall with at least part thereof being along a flow direction of a working fluid, coming into contact with the inner ring sidewall of the adjacent blade during operation, and separating from the inner ring sidewall of the adjacent blade when the operation is stopped.
    Type: Grant
    Filed: September 7, 2017
    Date of Patent: February 18, 2020
    Assignee: Toshiba Energy Systems & Solutions Corporation
    Inventors: Kazutaka Tsuruta, Iwataro Sato, Hideyuki Maeda, Satoru Sekine
  • Patent number: 10451003
    Abstract: A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 22, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: David L. Sutterfield, Randall E. Yount
  • Patent number: 10451082
    Abstract: A gas turbine engine and an anti-rotation feature is disclosed. The gas turbine engine includes a fan case, a stator disposed within the fan case, and a wear liner disposed between the fan case and the stator, the wear liner including a wear liner body, and an anti-rotation feature affixed to the wear liner body, wherein the anti-rotation feature includes at least one mating surface to engage the stator to prevent rotation of the wear liner body.
    Type: Grant
    Filed: August 16, 2016
    Date of Patent: October 22, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Thomas Freeman
  • Patent number: 10443423
    Abstract: A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces.
    Type: Grant
    Filed: August 25, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10436071
    Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel S. Rogers, Jeremy Drake, Brian C. McLaughlin
  • Patent number: 10378370
    Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott
  • Patent number: 10344606
    Abstract: A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.
    Type: Grant
    Filed: April 1, 2014
    Date of Patent: July 9, 2019
    Assignee: United Technologies Corporation
    Inventors: Jorge I. Farah, Conway Chuong, Dana P. Stewart
  • Patent number: 10344618
    Abstract: A mid-turbine frame (“MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.
    Type: Grant
    Filed: January 23, 2015
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: John E. Wilber
  • Patent number: 10260527
    Abstract: A method of damping a vibration in a rotatable member and a damping system for a rotatable machine are provided. The damping system includes one or more damping stages. The rotatable machine further comprising a casing at least partially surrounding the rotor. The casing includes inwardly extending vanes that include a radially outer root, a radially inner distal end, and a stationary body extending therebetween. The one or more damping stages includes a damper supportively coupled between one or more roots of the plurality of vanes and the casing, an air bearing fixedly coupled to one or more distal ends of the plurality of vanes and configured to bear against the rotatable body wherein the damping stage is configured to receive vibratory forces from the rotatable body through the air bearing and the vane and ground the received forces to the casing through the damper.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: April 16, 2019
    Assignee: General Electric Company
    Inventor: Tod Robert Steen
  • Patent number: 10233782
    Abstract: A turbine assembly of an engine is disclosed. The turbine assembly includes a nozzle ring for receiving exhaust gases from a combustion chamber having a plurality of guide vanes for guiding the exhaust gases, a stator ring disposed downstream to the nozzle ring, and a rotor disposed circumferentially within the stator ring. The stator ring includes a plurality of stator vanes adapted to receive the exhaust gases through the guide vanes of the nozzle ring. The stator ring is axially movable between a first position and a second position along at least one cross-key pin disposed between the stator ring and a turbine casing. Each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring.
    Type: Grant
    Filed: August 3, 2016
    Date of Patent: March 19, 2019
    Assignee: Solar Turbines Incorporated
    Inventor: Scott L. Stafford
  • Patent number: 10190500
    Abstract: The present invention provides a support duct for a gas turbine engine. The supported duct comprises at least one support frame having an aperture defined by an upper aperture wall, a lower aperture wall and opposing aperture side walls. It further comprises a duct extending through aperture, the duct comprising an upper panel in abutment with the upper aperture wall, a lower panel in abutment with the lower aperture wall and opposing side walls extending between the upper and lower panels. The opposing side walls of the duct are spaced from the opposing aperture side walls.
    Type: Grant
    Filed: May 13, 2015
    Date of Patent: January 29, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Jonathan Antony Cherry, Paul Robert Hayton
  • Patent number: 10138746
    Abstract: A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up protruding from the radially outer surface and configured to seal an interrupted surface.
    Type: Grant
    Filed: June 6, 2014
    Date of Patent: November 27, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Ryan C. McMahon
  • Patent number: 10072515
    Abstract: The disclosure relates Frame segment for a transition piece-turbine interface having a picture frame receptacle for axially receiving an aft end of a combustor transition piece. The frame segment can include an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web, wherein the upper horizontal element has mounting face for fixation to a vane carrier. The vertical web has a downstream face, facing towards a first stage of a turbine when installed in a gas turbine. The vertical web includes a cooling gas duct for supplying cooling gas to the downstream face of the vertical web.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: September 11, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fabien Fleuriot, Hans-Christian Mathews
  • Patent number: 10066837
    Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.
    Type: Grant
    Filed: February 20, 2015
    Date of Patent: September 4, 2018
    Assignee: General Electric Company
    Inventors: Richard Martin Dicintio, Elizabeth Angelyn Monaghan
  • Patent number: 9995178
    Abstract: A turbomachine component is provided having at least two sub-components that are separated by a parting joint and each have a sealing surface at the parting joint, at least one of the two sealing surfaces being convex in order to form a linear contact of the two sealing surfaces. At least one of the sealing surfaces has a coating on it which includes a hard material, is a maximum of 30 ?m thick and is applied using a vapour deposition method, or a coating which includes a chrome-containing alloy, is a maximum of 30 ?m thick and is applied by a vapour deposition method, or is a maximum of 300 ?m thick and applied using a thermal spraying method.
    Type: Grant
    Filed: November 7, 2012
    Date of Patent: June 12, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Jorg Schurhoff
  • Patent number: 9945261
    Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: April 17, 2018
    Assignee: SNECMA
    Inventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Regis Eugene Henri Servant
  • Patent number: 9945242
    Abstract: In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: April 17, 2018
    Assignee: General Electric Company
    Inventors: Christopher Paul Tura, Dylan James Fitzpatrick
  • Patent number: 9803486
    Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.
    Type: Grant
    Filed: December 31, 2013
    Date of Patent: October 31, 2017
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Robert F. Proctor, Sean E. Landwehr, Adam L. Chamberlain
  • Patent number: 9702252
    Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: July 11, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shezan Kanjiyani, Natalie Wali, Don Mittendorf, Lorenzo Crosatti
  • Patent number: 9650966
    Abstract: A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: May 16, 2017
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yasuro Sakamoto, Eisaku Ito, Susumu Wakazono, Koichi Ishizaka, Yukinori Machida
  • Patent number: 9140137
    Abstract: A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: September 22, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer
  • Patent number: 8888442
    Abstract: A turbine vane ring has radially outer and inner annular shrouds defining therebetween an annular gaspath. Circumferentially spaced-apart airfoil vanes extend radially across the gaspath between the outer and the inner shrouds. The radially outer shroud has a circumferentially continuous cylindrical wall extending axially from a leading edge to a trailing edge. A set of circumferentially distributed stress relieving slots is defined in the leading edge of the cylindrical wall at locations adjacent to the leading edge of at least some of said airfoil vanes. The stress relieving slots extend radially through the cylindrical wall from the radially inner surface to the opposed radially outer surface thereof.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: November 18, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Keppel Nyron Bharath, John Pietrobon, Vincent Paradis, Douglas MacCaul
  • Patent number: 8888441
    Abstract: Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Daniel Edward Jordy, William Edward Adis, Bernard Arthur Couture, Jr., Dexter Andrew Young
  • Patent number: 8684672
    Abstract: A brake system comprising a brake disc is disclosed. The brake system comprises at least one flexible portion. The at least one flexible portion is configured for compensating expansion of the brake disc and/or absorbing the expansion of the brake disc. The brake system is especially for a wind turbine generator.
    Type: Grant
    Filed: November 8, 2010
    Date of Patent: April 1, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventor: Soeren Oemann Lind
  • Patent number: 8678754
    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: Grant
    Filed: January 24, 2011
    Date of Patent: March 25, 2014
    Assignee: General Electric Company
    Inventors: Victor John Morgan, Rebecca Evelyn Hefner, Stephen Gerard Pope
  • Patent number: 8672616
    Abstract: A stator blade carrier, particularly for a gas turbine, is provided. The stator blade carrier includes a number of axial segments and is intended to attain a particularly high degree of operational reliability and long service life. To this end, two neighboring axial segments are connected to a number of tie rods, each enclosed by a support tube, wherein a spherical disk is arranged on at least one end of the respective support tube and mounted in a conical socket supported on the respective axial segment.
    Type: Grant
    Filed: September 16, 2009
    Date of Patent: March 18, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Roderich Bryk, Oliver Strohmeier
  • Patent number: 8649954
    Abstract: A system for controlling angular position of stator blades including: a mechanism for calculating a set angular position of the blades according to one of speeds; and a module for correcting the set position including: a mechanism for determining the angular position of the blades; a mechanism for measuring fuel flow rate of the turbine engine; a memory unit in which consecutive angular positions of the blades are combined with the fuel flow rates of the turbine engine measured at the angular positions; and a mechanism for determining a correcting angle according to the difference between the fuel flow rates measured between two consecutive angular position of the blades. A method for optimizing the common angular position can utilize the system.
    Type: Grant
    Filed: September 23, 2010
    Date of Patent: February 11, 2014
    Assignee: SNECMA
    Inventors: David Julien Boyer, Cedrik Djelassi, Julien Alexis Louis Ricordeau
  • Patent number: 8636466
    Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: January 28, 2014
    Assignee: Techspace Aero S.A.
    Inventor: Jean-François Cortequisse
  • Patent number: 8613590
    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: Grant
    Filed: July 27, 2010
    Date of Patent: December 24, 2013
    Assignee: United Technologies Corporation
    Inventors: Philip R. Belanger, Susan M. Tholen
  • Patent number: 8613589
    Abstract: To provide a thermal insulation structure for a structural member and a scroll structure which can be easily used even in integrally constructed structural members and which can ensure reliability and thermal insulation properties. Provided are securing portions (52 and 53) extending outward from an outer wall of the structural member; a press plate (55) attached to the securing portions (52 and 53), with a gap between the press plate and the outer wall; and a thermal insulation member (56) disposed between the outer wall and the press plate (55).
    Type: Grant
    Filed: March 27, 2009
    Date of Patent: December 24, 2013
    Assignees: Pebble Bed Modular Reactor (Pty) Limited, Mitsubishi Heavy Industries, Ltd.
    Inventors: Shoki Yamashita, Toshihiro Inoue
  • Patent number: 8608427
    Abstract: An arrangement for optimizing the running clearance for turbomachines of the axial type, such as turbocompressors, gas turbines, and steam turbines, in particular for compressors of stationary gas turbines, by controlling the inner diameter, which is relevant to the running clearance, of at least one stator structure that surrounds a rotor blade ring, including: the stator structure has a closed, circular inner ring, a circular outer ring that is situated concentric to the inner ring at a radial distance therefrom, and a plurality of links that integrally connect the inner ring to the outer ring, the links being circumferentially inclined at a defined angle (?) to the radial direction and distributed around the circumference of the stator structure, and the arrangement includes an adjustment device for rotating the inner ring relative to the outer ring with elastic modification of the running clearance-relevant inner diameter (D) of the inner ring.
    Type: Grant
    Filed: August 8, 2007
    Date of Patent: December 17, 2013
    Assignee: MTU Aero Engines GmbH
    Inventor: Alexander Böck
  • Patent number: 8591182
    Abstract: A device (10) for suspending gas channel elements, in particular for suspending guide blades or guide blade segments or gas channel segments, on a housing of a gas turbines is provided. The device comprises first plate-shaped elements (11, 12, 13, 14) and second plate-shaped elements (15, 16, 17), whereby the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected together by web-like elements (18) which extend in an essentially perpendicular manner in relation to the first and second elements and form a meandering or crenelated profile.
    Type: Grant
    Filed: December 15, 2004
    Date of Patent: November 26, 2013
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Morgenstern, Rudolf Stanka
  • Patent number: 8534076
    Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
    Type: Grant
    Filed: June 9, 2009
    Date of Patent: September 17, 2013
    Assignee: Honeywell Internationl Inc.
    Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn
  • Patent number: 8523518
    Abstract: Systems, methods, and apparatus for linking machine stators are provided. A bracket may be utilized to link adjacent stators within a machine, for example, a turbine. The bracket may include a body portion, a first plurality of extensions, and a second plurality of extensions. The body portion may include a first edge operable to align with a base of a first stator and a second edge opposite the first edge and operable to align with a base of a second stator. The first plurality of extensions may extend from the first edge and may be operable to align with at least one corresponding groove on the base of the first stator. The second plurality of extensions may extend from the second edge and may be operable to align with at least one corresponding groove on the base of the second stator. When utilized to link the first stator and the second stator, the bracket may facilitate a reduction of vibrations in the first stator and the second stator.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: September 3, 2013
    Assignee: General Electric Company
    Inventors: Lisa A. Wichmann, Thomas R. Tipton, Nick Martin