Patents Examined by Dwayne J. White
  • Patent number: 9863272
    Abstract: A turbomachine of this disclosure includes a rotation shaft, a first impeller, a first bearing, and a second bearing. The first impeller is fixed to the rotation shaft and includes a low-pressure-side surface. The first bearing is adjacent to the low-pressure-side surface of the first impeller and supports the rotation shaft. The second bearing is disposed on an opposite side of the first impeller from the first bearing and supports the rotation shaft. The rotation shaft includes a first tapered portion gradually increasing in diameter toward the first impeller. The first bearing includes a first support surface supporting the first tapered portion.
    Type: Grant
    Filed: April 6, 2015
    Date of Patent: January 9, 2018
    Assignee: PANASONIC INTELLECTUAL PROPERTY MANAGEMENT CO., LTD.
    Inventor: Tadayoshi Shoyama
  • Patent number: 9863258
    Abstract: A method of forming a structural connection between a spar cap 14 and an aerodynamic fairing 12. A composite comprising an uncured matrix and a compressible solid is applied between the spar cap and fairing and is then compressed and cured to adhere the fairing to the spar cap. The cured matrix composite has a void volume of at least 20%. The high void volume means that as the fairing is compressed into place and compresses the composite, it has space in which to deform so as not to place undue stress on the fairing and to produce a lightweight connection.
    Type: Grant
    Filed: March 24, 2015
    Date of Patent: January 9, 2018
    Assignee: Blade Dynamics Limited
    Inventors: Paul Hayden, Harald Behmer
  • Patent number: 9863423
    Abstract: A conical impeller with a hub that has a conical surface extending into the interior of the impeller. The hub has spiral, slanting arms which are attached or integrally formed with a plurality of curved blades. The blades can be connected at the bottom by a ring. The intersection of the conical surface of the hub with the blade forms an upward path for fluids and their entrained particles or gases which have been brought into the interior of the impeller to effectively completely be ejected. The discharge edges of the blades and/or the conical surface of the hub may have openings for discharging gas into the fluid. The impeller imparts low shear to the fluid and its components, and the shear is independent or only depends slightly on the size of the impeller. The impeller minimizes or eliminates particle agglomeration and fouling of the impeller. The efficiency of and flow pattern produced by the impeller means that containers don't require the use of baffles.
    Type: Grant
    Filed: April 14, 2015
    Date of Patent: January 9, 2018
    Assignee: Enevor Inc.
    Inventor: Carl Roy Bachellier
  • Patent number: 9863278
    Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Patrick Sultana, Boucif Bensalah, Yannick Durand, Olivier Renon
  • Patent number: 9856034
    Abstract: An aircraft nacelle comprising a first and a second cowl mounted pivotably about an axis substantially parallel to a longitudinal axis of the nacelle and lockable to one another by at least one locking mechanism. The nacelle further comprises a device for providing a visual warning of a locking defect of the cowls. The device comprises a movable bolt associated with the locking mechanism and a movable edge plate mounted on the nacelle in line with said bolt with which it is associated, the movable edge plate being movable under the action of an operator between a protruding position, in which the edge plate is protruding from the nacelle and a locking mechanism is in an unlocked position, and a retracted position, in which the edge plate is immobilized within the nacelle by the bolt and the action of the locking of a locking mechanism.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: January 2, 2018
    Assignee: Airbus Operations (SAS)
    Inventor: Jacques Herve Marche
  • Patent number: 9856736
    Abstract: A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier.
    Type: Grant
    Filed: October 17, 2013
    Date of Patent: January 2, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Frank Stiehler
  • Patent number: 9856739
    Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
    Type: Grant
    Filed: September 18, 2013
    Date of Patent: January 2, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Loris Bedrosyan, Ardeshir Riahi, Daniel C. Crites
  • Patent number: 9856852
    Abstract: The present invention relates to a floating wind energy harvesting apparatus for offshore installation, comprising an elongated wind turbine body extending along a longitudinal wind turbine body axis, said wind turbine body comprising a lower body portion and an upper body portion; wind turbine blades attached to the upper body portion; at least a first cavity inside said wind turbine body and arranged within a first radial distance from said longitudinal wind turbine body axis; at least a second cavity arranged within a second radial distance, greater than said first radial distance, from said longitudinal wind turbine body axis; at least a first pump for pumping water from said first cavity to said second cavity; and an energy converter attached to said wind turbine body for converting the rotation of said wind turbine body to electrical energy.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: January 2, 2018
    Assignee: SEA TWIRL AB
    Inventor: Daniel Ehrnberg
  • Patent number: 9850772
    Abstract: Seal assemblies for reducing leakage between components of turbomachinery include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, end blocks and ceramic fiber are coupled. The end blocks account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks protect the metallic shim from reaching harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: December 26, 2017
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Edip Sevincer, Anthony Marin
  • Patent number: 9845734
    Abstract: An air turbine start system is provided that includes an air turbine starter, a starter air valve, a turbine speed sensor, and a circuit. The starter air valve is movable between an open position, in which the pressurized air may flow into the air turbine starter, and a closed position, in which pressurized air does not flow into the air turbine starter. The turbine speed sensor is coupled to the air turbine starter, and is configured to sense the rotational speed of the turbine and supply a rotational speed signal representative thereof. The circuit is coupled to receive the rotational speed signal and is configured, upon receipt thereof, to determine whether the starter air valve is in the closed position or an open position.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: December 19, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Peter Kenneth Zeiner, Dave Oman, Jimmy Wiggins
  • Patent number: 9845810
    Abstract: Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: December 19, 2017
    Assignee: Concepts NREC, LLC
    Inventor: David Japikse
  • Patent number: 9845702
    Abstract: A stator damper is disclosed. The stator damper has a body section and a damper finger. The body section rests against a stator assembly and a portion of each damper finger rests against a compressor casing. The stator damper is radially compressed between the stator assembly and the compressor casing. Thus, the stator damper exerts a radial force against the stator assembly. In this manner, relative motion of the stator assembly is damped.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: December 19, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nicholas R. Leslie, David P. Dube, Randall J. Butcher
  • Patent number: 9845698
    Abstract: A belly band seal for use in a multi-stage turbomachine having plural rotor disks includes a seal strip positionable in a space between a pair of arms defined by opposing portions of adjoining rotors. The seal strip includes opposite edges for locating in respective slots in end faces of said pair of arms. The belly band seal further includes an anti-rotation structure disposed on a radially inner surface of the seal strip. The anti-rotation structure is configured as a cantilever having a pivoted end fixed to the radially inner surface and a free end comprising a radially inwardly extending engagement member for removably positioning in a radial recess in one of the arms. The cantilever is configured so as to urge the engagement member toward the radial recess by spring action. The radial recess is configured to constrain a tangential movement of the engagement member upon being positioned therein.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: December 19, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Robert T. Brooks, Manish S. Gurao
  • Patent number: 9845707
    Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: December 19, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Alain Porte, Matthieu Fargues
  • Patent number: 9840936
    Abstract: A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.
    Type: Grant
    Filed: February 16, 2012
    Date of Patent: December 12, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
  • Patent number: 9841035
    Abstract: A heat dissipation fan includes a base plate, a frame formed on a side of the base plate, a stator received sin the frame, and a rotor below the stator and connected with the stator. The heat dissipation fan also has an air inlet, a first air outlet and a second air outlet. The air inlet is communicated with the first air outlet and the second air outlet. An angle is defined between each of the first air outlet and the second air outlet.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: December 12, 2017
    Assignee: CHAMP TECH OPTICAL (FOSHAN) CORPORATION
    Inventors: Hong-Tao Wu, Chih-Feng Hu
  • Patent number: 9835055
    Abstract: An exemplary pullable drawer is arranged for removably protruding in a radial direction into an outer housing of a turbine, in order to make mechanical contact with an inner carrier being concentrically arranged within the outer housing. The pullable drawer has an essentially cylindrical body, which extends along a longitudinal drawer axis. A mechanical decoupling is provided, as the pullable drawer is divided along the longitudinal drawer axis into at least separate first and second parts. The first and second parts are coupled with each other by means of a releasable mechanical joint.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: December 5, 2017
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Stefan Gerzner, Marc Rauch, Ernst Vogt, Jose-Manuel Lopez
  • Patent number: 9835135
    Abstract: A method for controlling a wind turbine may generally include operating the wind turbine at an initial power output that is greater than a rated power output associated with the wind turbine. The wind turbine may have an anticipated operational life at the rated power output. In addition, the method may include decreasing a power output of the wind turbine over time in order to maintain an actual operating life of the wind turbine substantially equal to or greater than the anticipated operational life. A final power output of the wind turbine at an end of the anticipated operating life may be less than the rated power output.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: December 5, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Samuel David Draper
  • Patent number: 9835171
    Abstract: A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.
    Type: Grant
    Filed: August 20, 2010
    Date of Patent: December 5, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Keith D. Kimmel, Jack Wilson
  • Patent number: 9828876
    Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Corporation
    Inventor: Matthew J. Kappes