Patents Examined by Adam W Brown
  • Patent number: 10227990
    Abstract: A number of variations may include a product including a rotor comprising a shaft having a rotation axis, a bearing at least partially surrounding the shaft allowing for rotation of the shaft within the bearing about the rotation axis, and a bearing housing comprising at least one fluid outlet passage constructed and arranged to flow fluid upward from the bearing to a top side of the bearing housing.
    Type: Grant
    Filed: May 5, 2017
    Date of Patent: March 12, 2019
    Assignee: BorgWarner Inc.
    Inventor: Jonathan Williams
  • Patent number: 10227962
    Abstract: A power plant includes a structure and a vehicle having at least one wing including a first wing part and a second wing part. The vehicle is arranged to be secured to the structure by at least one tether. The vehicle is arranged to move in a predetermined trajectory by a fluid stream passing the wing. The vehicle includes at least one turbine connected to a nacelle having a generator. At least the first wing part is arranged at a first angle relative to a horizontal center line of the wing. The nacelle is arranged to be attached to a surface of the wing facing the direction in which the first wing part is angled.
    Type: Grant
    Filed: July 12, 2013
    Date of Patent: March 12, 2019
    Assignee: MINESTO AB
    Inventor: Arne Quappen
  • Patent number: 10214804
    Abstract: A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage hub portion and centered on the central axis, and a plurality of first stage vanes positioned radially around and attached to the first stage disk portion. Each vane extends a vane height H away from the first stage disk portion and each vane has a first end positioned at a diameter D away from the central axis. The first stage turbine nozzle also includes a plurality of first stage throats defined between radially adjacent first stage vanes. Each first stage throat has a throat width W between radially adjacent first stage vanes. The first stage turbine nozzle also includes a coating on a sidewall of each first stage vane.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: February 26, 2019
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Kevin M. Rankin
  • Patent number: 10215029
    Abstract: A blade assembly including a rotor; a body portion connected to the rotor and having a space therein; and at least one vibration reduction member provided in the space.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: February 26, 2019
    Assignee: HANWHA POWER SYSTEMS CO., LTD.
    Inventor: Karl Wygant
  • Patent number: 10207792
    Abstract: A system and method for nose cone edge delamination repair is provided. A nose cone may comprise an outer skirt having an aft edge, a flange, and a pin landing. The system and method may comprise trimming the aft edge of the nose cone to form a repaired edge. A first layer of fiberglass may be placed over repaired edge. A second layer of fiber glass may be placed over the first layer and the repaired edge. The first layer and second layer may be trimmed to create a spot face to allow for lower tolerances when installing the nose cone into a gas turbine engine.
    Type: Grant
    Filed: May 23, 2016
    Date of Patent: February 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brian K. Holland
  • Patent number: 10208770
    Abstract: An axial flow fan improves air capacity and static pressure characteristics, and can ease stress at a leading edge portion of a blade base, even when a shape for noise reduction is adopted. An axial flow fan includes a boss portion and rotor blades. A rotor blade is segmented into a first area extending from the boss portion toward the outer peripheral side, and a second area connected to the first area and extending from the first area to the outermost periphery of the rotor blade. The distribution of a forward sweep angle varies quadratically in the first area, and the maximum forward sweep angle in the first area is not larger than the forward sweep angle in the second area. The distribution of chord-pitch ratio varies in a curved manner from the base as the minimum value in the first area, and is linear in the second area.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: February 19, 2019
    Assignee: MITSUBISHI ELECTRIC CORPORATION
    Inventors: Toshikatsu Arai, Hitoshi Kikuchi, Tsutomu Takahashi, Tatsushi Murakami
  • Patent number: 10196149
    Abstract: A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and attached to the second stage disk portion. Each second stage vane extends a vane height H away from the second stage disk portion and each second stage vane has a first end positioned at a diameter D away from the central axis. The second stage turbine nozzle also includes a plurality of second stage throats defined between radially adjacent second stage vanes. Each second stage throat has a throat width W between radially adjacent second stage vanes. The second stage turbine nozzle also includes a coating on a sidewall of each second stage vane, wherein a surface roughness of the sidewall is between 125 microinches Ra and 200 microinches Ra.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: February 5, 2019
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Kevin M. Rankin
  • Patent number: 10180071
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: January 15, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Daniel K. Vetters
  • Patent number: 10174741
    Abstract: The present invention relates to a blade pitch control apparatus for a small size wind power generator. More specifically, the present invention relates to a blade pitch control apparatus for a small size wind power generator configured to accomplish continuous generation by continuously maintaining the necessary rotating force of the blade by systematically operating the ball screw, spinner driver, and pitch angle controller when the rotation number of blades exceeds the reference rotation number by over wind speed, so that the blade pitch is automatically controlled.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: January 8, 2019
    Assignee: GU CO., LTD.
    Inventor: Jong Rai Lee
  • Patent number: 10173264
    Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Brandon S. Donnell
  • Patent number: 10161419
    Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: December 25, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian C D Care, Dale E Evans
  • Patent number: 10145383
    Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as ? ? = ? i - ? ? i - ? e where ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: December 4, 2018
    Assignee: Rolls-Royce Corporation
    Inventor: Bronwyn Power
  • Patent number: 10145378
    Abstract: A rotary machine characterized by being equipped with: a rotary drive part; a drive shaft that is rotated about a horizontally extending axis by the rotary drive part; a large gear that is fixed to the drive shaft; a bearing part that rotatably supports the drive shaft, and to which a lubrication oil is supplied; multiple pinions that are driven by being engaged with the large gear; multiple compression parts that are arranged so as to correspond to the multiple pinions and are respectively rotated by the pinions; and a plate that is installed between the bearing part and the large gear and covers at least a portion of the bottom half of the large gear so as to separate the large gear and the bearing part from each other.
    Type: Grant
    Filed: September 6, 2013
    Date of Patent: December 4, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Hiroyuki Miyata, Shinichiro Tokuyama
  • Patent number: 10132178
    Abstract: To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: November 20, 2018
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Koji Ishibashi, Susumu Nakano, Takeshi Kudo
  • Patent number: 10125788
    Abstract: Fan blade containment system includes circular tile layer of annular ceramic tiles attached to and extending radially inwardly from a shell, radially inner and outer annular surfaces of ceramic tiles bonded to a radially inner composite layer and the shell respectively with elastomeric inner and outer adhesive layers respectively. Elastomeric adhesive layers between circumferentially adjacent overlapped or scarfed edges along circumferential edges of the ceramic tiles overlap and mate along oppositely facing surfaces of adjacent ones of the ceramic tiles. Inner and outer adhesive layers and elastomeric adhesive layer may be a double-sided adhesive foam tape. Scarfed edges may be bevels or rabbets. Shell may be made of a metal or composite material. Fan blade containment system may be bonded to and extend inwardly from fan case circumscribing fan blades of a fan. Inner composite layer and composite outer shell may be co-cured with ceramic tiles therebetween.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: November 13, 2018
    Assignee: General Electric Company
    Inventors: Wendy Wen-Ling Lin, David Sujay Kingsley, Benjamin James Roby
  • Patent number: 10125744
    Abstract: The invention provides a lightning protection system for a wind turbine blade (10), whose structure comprises two structural shells (11, 13) with two caps (19, 21) formed by carbon fiber laminates and two spars (15, 17). In addition to a first subsystem formed by one or more lightning receptors connected to one or two conductor cables the lightning protection system comprises a second subsystem formed by lateral lightning receptors (30, 31) arranged at the leading and trailing edges of the wind turbine blade (10) in at least two cross sections (22, 23) of it connected with the caps (19, 21) and connecting means between the two subsystems for equipotentializing the lightning protection system.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: November 13, 2018
    Assignee: GAMESA INNOVATION & TECHNOLOGY, S. L.
    Inventors: Victor March Nomen, Francisco Javier Bandres Gomez, Javier Iriarte Eleta
  • Patent number: 10125724
    Abstract: A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gary D. Roberge, Andrew P. Berryann, Scott A. Carr
  • Patent number: 10119417
    Abstract: A turbocharger (300) having a rotatable shaft (312) passing through a bearing housing (303) with a turbine-end bearing support (580) with a support bar (600). A turbine-end bearing support (580) may include the support bar (600) with radial supports (610) and (620) connected to each opposite side (492) and (494) of cavity (496) of the bearing housing (303) wherein oil can flow in recesses (640) and (650) above the radial supports (610) and (620). Each radial support (610) and (620) of the support bar (600) is preferably integrated in the corresponding side (492) and (494). A turbine-end bearing support (580) may also include the support bar (600) with a rod portion (622) forming a bottom tie support bar (612) that supports the bottoms of both bearing supports (490) and (580), which are top-supported by the bearing housing (303). Each support bar (600) is preferably integral with the bearing support (580).
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: November 6, 2018
    Assignee: BorgWarner Inc.
    Inventor: Michael Bucking
  • Patent number: 10113439
    Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 30, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-Fran├žois Cortequisse
  • Patent number: 10107194
    Abstract: A gas turbine stage, in particular to an aircraft gas turbine. This gas turbine includes at least one casing having at least one bleed duct and at least one bore, and further includes at least one variable guide vane having a trunnion, a rotary plate, and a guide vane airfoil. The trunnion is disposed in the bore, and the guide vane airfoil is integrally formed with the rotary plate. The guide vane airfoil integrally formed with the rotary plate extends beyond this rotary plate in such a way that, viewed in the direction of flow of the gas path of the gas turbine, a flag corner of the guide vane airfoil, which corner faces the bleed duct and/or is in particular a virtual one, is located downstream of the beginning of the inlet opening of the bleed duct.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: October 23, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Lahmer, Harsimar Sahota