Patents Examined by Woody A Lee, Jr.
  • Patent number: 10815973
    Abstract: Method for retrofitting a lightning protection device of a rotor blade of a wind turbine. In the method, a cable section of a lightning protection cable is stripped of insulation. A connection piece and a lightning protection receptor are fitted to the cable section which is stripped of insulation, so that the lightning protection receptor is electrically coupled to the lightning protection cable. The invention also relates to a rotor blade which is retrofitted using the method. The risk of lightning strikes in specific regions of a rotor blade can be reduced by the invention by means of the retrofitting operation.
    Type: Grant
    Filed: August 7, 2018
    Date of Patent: October 27, 2020
    Assignee: Senvion GmbH
    Inventor: Christian Flach
  • Patent number: 10815787
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: David Mikol, Kimberly Pash Boyington, Brian J. Schuler, Zhen Wu, Joseph Wieser, Xuedong Zhou, Sue-Li Chuang, John Joseph Papalia, Han J. Yu
  • Patent number: 10816205
    Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gary J Dillard, Russell B Hanson
  • Patent number: 10815800
    Abstract: An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip surface, and a rib. The first wall radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge. The second wall radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge. The third wall radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge. The tip surface circumferentially extends between the second wall and the third wall. The rib is radially spaced apart from the tip surface and circumferentially extends between the first wall and the third wall.
    Type: Grant
    Filed: December 5, 2016
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10808574
    Abstract: A turbomachine assembly includes annular stator surrounding rotor circumscribed and rotatable about centerline axis. One or more non-axisymmetric partial arc annular circular stiffeners are disposed around and on stator and may be helical. Non-axisymmetric partial arc annular circular stiffeners may extend about one third to one half of a circumference, be hollow, and located over one or more blade stages of rotor. One or more annular mid-span flanges may be attached to stator and axially positioned within the hollow partial arc annular circular stiffeners. One or more masses or externals may be attached to the stator or to at least one of the one or more annular mid-span flanges between ends of partial arc annular circular stiffeners. Annular stator and rotor may have matching frequencies causing rotating stator waves rotating with rotor. The stator may be fan casing surrounding fan rotor or labyrinth seal land surrounding labyrinth seal teeth.
    Type: Grant
    Filed: September 13, 2016
    Date of Patent: October 20, 2020
    Assignee: General Electric Company
    Inventors: Leslie Louis Langenbrunner, Tod Robert Steen
  • Patent number: 10808560
    Abstract: A turbine vane assembly includes an airfoil, a support strut, and an inner seal panel. The airfoil is formed to include an interior region of the airfoil. The support strut is located in the interior region of the airfoil and configured to carry loads that act on the airfoil. The inner seal panel extends at least partway about the axis to resist fluid communication between a region upstream of the inner seal panel and a region downstream of the inner seal panel.
    Type: Grant
    Filed: June 20, 2018
    Date of Patent: October 20, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 10801358
    Abstract: An alignment apparatus for aligning inlet guide vanes in a turbine having a turbine axis includes a tool body, a positioning block secured to the tool body, and a plurality of alignment pieces secured to the tool body. The positioning block may be affixed to the tool body such that when the positioning block is engaged with a leading edge of one of the inlet guide vanes, at least a portion of the alignment pieces is parallel to the turbine axis. The alignment pieces may be manually displaceable from the OFF position to the ON position into engagement with the inlet guide vanes to align one or more of the inlet guide vanes.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Piotr Hubert Wojciechowski, Lukasz Sajdak, Szymon Perkowski
  • Patent number: 10801516
    Abstract: A field of turbomachine rotor blades, and in particular a turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, together with at least one intermediate segment presenting a negative tangential slope, and a distal segment situated between the intermediate segment and the blade tip and presenting a positive tangential slope, wherein the distal segment extends over at most 30% of said blade height.
    Type: Grant
    Filed: August 5, 2016
    Date of Patent: October 13, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Roger Felipe Montes Parra, Prasaad Cojande
  • Patent number: 10801341
    Abstract: A gas engine turbine has a transition duct (100) that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel (130) is formed through the transition duct panel (112), the exit frame (114) and the connection (116). The continuous exit section cooling channel (130) reduces the need for effusion channels in the transition duct. The continuous exit section cooling channel (130) further reduces costs and improves the emissions associated with the transition duct (100) of the gas engine turbine.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: October 13, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Manish Kumar, Daniel Cassar
  • Patent number: 10801473
    Abstract: The present disclosure is directed to a hub crane assembly for a wind turbine. The hub crane assembly includes an adjustable articulating arm mountable at a first height on a hub of the wind turbine at a hinge point, a first hoist mountable at a second height of the wind turbine, the second height being greater than the first height, and a support component secured to the first hoist and a first attachment point of the articulating arm. Further, the first hoist is configured to rotate the articulating arm about the hinge point via the support component such that, as the articulating arm rotates, a clearance distance between the wind turbine and the articulating arm changes.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Daniel Gomez Mora, Jacob Thomas Hoyt, Michael Royce Johnson
  • Patent number: 10801344
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A skin core cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nicholas M. LoRicco, Steven Bruce Gautschi
  • Patent number: 10801520
    Abstract: A centrifuge turbo machinery includes an impeller which rotates about an axis to pressure-feed fluid flowing along the axis to an outer side in a radial direction, and a casing which accommodates the impeller and has a facing surface facing the impeller in an axial direction. A convex portion relatively close to the impeller and extending in the radial direction and a concave portion relatively spaced apart from the impeller and extending in the radial direction are alternately and continuously formed on the facing surface in a circumferential direction.
    Type: Grant
    Filed: August 14, 2018
    Date of Patent: October 13, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Takeshi Sano, Taiki Asahara
  • Patent number: 10800542
    Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: October 13, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Erik Harrington, Andrew N. Baines
  • Patent number: 10794225
    Abstract: A turbine with a supersonic separator disposed upstream of the turbine. The supersonic separator imparts a swirl on a vapor stream to remove any heavier components. A superheated vapor stream from the supersonic separator is passed through the turbine to reduce the pressure of the vapor stream. At the same time, electricity is generated by the superheated vapor stream via a turbine wheel. The turbine and the supersonic separator can be integrally formed, or they can be discrete components.
    Type: Grant
    Filed: March 16, 2018
    Date of Patent: October 6, 2020
    Assignee: UOP LLC
    Inventors: Stanley Joseph Frey, Michael Van de Cotte
  • Patent number: 10794396
    Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and including an inner wall, the inner wall of the outer nacelle including a plurality of pre-swirl contours positioned forward of the fan blades of the fan along an axial direction and extending inwardly along a radial direction.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: October 6, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Christopher James Kroger, Trevor Wayne Goerig, Tsuguji Nakano, Jeffrey Donald Clements
  • Patent number: 10794394
    Abstract: A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher W. Strock, James O. Hansen
  • Patent number: 10793243
    Abstract: The present invention relates to a foldable propeller (1) for a boat, e.g. for a sailboat or a multihull yacht, where the foldable propeller (1) comprises a hub (2) with a plurality of blades, each blade comprising a blade root arranged to pivot around a separate pivot pin in order to be either in a first operative orientation, where the blade (4) is pointing mainly in a radial direction, or in a second inoperative orientation, where the blade is pointing mainly in an axial direction. The hub (2) comprises a number of hub flanges (28) for holding the pivot pins (9). The pivot pin (9) comprises at its second end (21) a head (26) with a recess (24) that accommodates the first end (20) of another of the pivot pins (9) inside the head (26).
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: October 6, 2020
    Assignee: Flexofold ApS
    Inventors: Jack Skrydstrup, Ulrik Nielsen
  • Patent number: 10787912
    Abstract: Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.
    Type: Grant
    Filed: April 25, 2018
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • Patent number: 10787251
    Abstract: A helicopter has a mast axis and a rotorcraft blade assembly. The rotorcraft blade assembly has a main body and a blade tip movable relative to the main body. The rotorcraft blade assembly is selectively rotatable about the mast axis.
    Type: Grant
    Filed: January 14, 2018
    Date of Patent: September 29, 2020
    Assignee: Textron Innovations Inc.
    Inventor: Christopher Edward Foskey
  • Patent number: 10781827
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jason Elliott, Daniel C. Falk, Myron L. Klein, Ethan C. Drew, James H. Moffitt, Darryl Whitlow, Byron R. Monzon, Jay Thomas Abraham, William R. Graves