Patents Examined by David E Sosnowski
  • Patent number: 10788048
    Abstract: An inlet guide vane assembly is provided. The inlet guide vane assembly includes a housing, a rotating shaft rotatably located in the housing, a vane portion connected to the rotating shaft, a bushing portion located between the rotating shaft and the housing, and an elastic portion located between the bushing portion and the rotating shaft.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: September 29, 2020
    Assignee: HANWHA AEROSPACE CO., LTD.
    Inventor: Jin Hyoung Kim
  • Patent number: 10781707
    Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
    Type: Grant
    Filed: September 14, 2018
    Date of Patent: September 22, 2020
    Assignee: United Technologies Corporation
    Inventors: David M. Dyer, Zachary J. Jeske, Michael Ronan, Matthew E. Bintz, John P. Tirone, Scott Gammons, Michael C. Firnhaber, Mark E. Simonds
  • Patent number: 10781790
    Abstract: A bulkhead assembly for a wind turbine blade is described, wherein a pressure relief conduit is provided at the bulkhead to allow for pressure to equalise across the bulkhead. This helps to prevent faults or cracks in the bulkhead assembly due to differences in pressure on either side of the bulkhead. Furthermore, liquid traps and/or filter media can be accommodated in the conduit to prevent the passage of liquids or other matter across the bulkhead.
    Type: Grant
    Filed: September 11, 2018
    Date of Patent: September 22, 2020
    Assignee: LM WP PATENT HOLDING A/S
    Inventors: Aanchal Saini, Utsa Majumder, Christian Munk Christensen, Christian Roed Lysemose, Peter Hansen, Finn Kjaer Nielsen
  • Patent number: 10781697
    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 core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10781789
    Abstract: A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a rigid winglet associated with the wingtip and having a winglet body extending substantially normal to one of a suction side and a pressure side of the elongate body to a termination point that is rearward of the trailing edge. In an embodiment, the structure is a rotor blade that may be incorporated into a wind turbine.
    Type: Grant
    Filed: August 5, 2015
    Date of Patent: September 22, 2020
    Assignee: BIOMERENEWABLES INC.
    Inventor: Ryan Church
  • Patent number: 10774659
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.
    Type: Grant
    Filed: March 12, 2018
    Date of Patent: September 15, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark F. Zelesky, Andrew S. Aggarwala
  • Patent number: 10767867
    Abstract: A bearing support may include a central shaft, a flange shaft, and a tube boss. The central shaft may include a central longitudinal axis extending between a first end and a second end of the bearing support. The flange shaft may extend radially outward of the central shaft at an acute angle, relative to the central longitudinal axis from the first end to the second end, and the flange shaft may include a rim defining an aperture. The tube boss extends from the central shaft radially outward through the aperture, according to various embodiments. An annular channel may be between the rim and the tube boss.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Todd A. Davis, Christopher M. Valva, Daniel Rosen, Armando Amador, Aneil S. Hegde, Ramin M. Rafatpanah
  • Patent number: 10767486
    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Richard K. Hayford, Steven J. Ford
  • Patent number: 10767489
    Abstract: An engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component.
    Type: Grant
    Filed: August 16, 2016
    Date of Patent: September 8, 2020
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10760497
    Abstract: Provided is a gas turbine starting device which has a sun gear, a planetary carrier, an internal gear, and a planetary gear, the sun gear, the planetary carrier and the internal gear serving as rotating bodies rotating about an axis; and a variable speed power source which has a rotor connected to one of the rotating bodies in the planetary gear mechanism. A rotating shaft of the gas turbine is connected to one of the rotating bodies other than the rotating body to which the variable speed power source is connected, and the rotating shaft of the compressor is connected to the remaining one of the rotating bodies other than the rotating bodies to which the rotor of the variable speed power source and the rotating shaft of the gas turbine are connected.
    Type: Grant
    Filed: February 23, 2015
    Date of Patent: September 1, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Masahiro Kobayashi, Yasushi Mori
  • Patent number: 10759530
    Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.
    Type: Grant
    Filed: October 26, 2018
    Date of Patent: September 1, 2020
    Assignee: Bell Textron Inc.
    Inventors: David E. Heverly, II, Frank B. Stamps, Michael Smith
  • Patent number: 10759510
    Abstract: The present disclosure discusses a method of and an arrangement for the lubrication of a controllable pitch propeller of a marine vessel. The lubrication is based on continuous lubricant circulation from the hydraulic powerpack to the hub and back to the oil tank, when the marine vessel is sailing ahead with propeller blades locked in a desired position. The lubrication is performed by maintaining, at least when the propeller blades are locked in a desired position, a pressure difference between the astern oil chamber and the lubricant chamber for circulating lubricant from the astern oil chamber via the lubricant chamber to the oil tank.
    Type: Grant
    Filed: March 5, 2015
    Date of Patent: September 1, 2020
    Assignee: WÄRTSILÄ NETHERLANDS B.V.
    Inventors: Lukasz Bartnik, Robert Vogels
  • Patent number: 10760441
    Abstract: The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: September 1, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Olivier Arnaud Fabien Lambert, Franck Robert Drouet, Gaël Frédéric Claude Cyrille Evain
  • Patent number: 10753216
    Abstract: A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity.
    Type: Grant
    Filed: August 20, 2018
    Date of Patent: August 25, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Brandon W. Spangler
  • Patent number: 10746033
    Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Jose R. Paulino
  • Patent number: 10738756
    Abstract: Certain embodiments are directed to a vertical axis unidirectional rotor for wave energy conversion, said rotor comprising a plurality of spatially distributed lift-type and/or drag-type blades and a shaft, said rotor performing unidirectional rotation in waves about the shaft that is vertically oriented.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: August 11, 2020
    Assignee: THE BOARD OF REGENTS OF THE UNIVERSITY OF TEXAS SYSTEM
    Inventor: Yingchen Yang
  • Patent number: 10731473
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel A. Snyder, Tracy A. Propheter-Hinckley, Dominic J. Mongillo
  • Patent number: 10731492
    Abstract: A component joint including a turbomachine component (10) having at least one component flange (11); a mating turbomachine component (20) connected thereto and having at least one mating component flange (21); and at least one seal (30) to provide a seal against an overpressure (p2?p1) on the component side, the at least one seal (30) having a sealing surface (31) that engages into a groove (12) of the turbomachine component (10), the groove (12) being disposed on a mating-component-flange-facing side of the component flange (11) and having a contact surface (13) for sealingly axially supporting the sealing surface (31).
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: August 4, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Alexander Kloetzer, Manfred Feldmann
  • Patent number: 10731493
    Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.
    Type: Grant
    Filed: April 10, 2014
    Date of Patent: August 4, 2020
    Assignee: Ratheyon Technologies Corporation
    Inventors: Timothy M. Davis, Mark J. Rogers, Mark Broomer, Craig R. McGarrah, Carson A. Roy Thill
  • Patent number: 10731470
    Abstract: An airfoil defining a chordwise dimension, a spanwise dimension, a leading edge, a trailing edge, a root, and a tip, is generally provided. The airfoil includes a first material substrate defining a pressure side and a suction side. The first material substrate defines a plurality of discrete volumes extended from at least one of the pressure side or the suction side into the first material substrate. The plurality of discrete volumes is arranged at least partially along the chordwise dimension and a second material substrate different from the first material substrate is defined at least partially within the volume.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventor: David William Crall