Patents Examined by Courtney D Heinle
  • Patent number: 11073138
    Abstract: A wind turbine nacelle platform structure including a beam assembly with at least two beams arranged to extend from a front region of a nacelle outward beyond the back end of the nacelle and a platform assembly mounted to the underside of the outward extending portion of the beam assembly. The disclosed further describes a wind turbine including a nacelle mounted on top of a tower, and such a nacelle platform structure secured to the nacelle.
    Type: Grant
    Filed: August 28, 2018
    Date of Patent: July 27, 2021
    Inventor: Thorkil Munk-Hansen
  • Patent number: 11066150
    Abstract: A propeller oil control system for a turboprop engine of an aircraft includes an engine control unit and a propeller oil controller. The engine control unit is operable to determine a flight phase of the aircraft and is configured to supply control commands. The propeller oil controller is coupled to receive a supply of oil and to discharge the oil at a discharge oil pressure. The propeller oil controller includes an electrohydraulic servo valve that receives the control commands moves to a plurality of positions between a first position and a mid-position, and a plurality of positions between the mid-position and a second position. The engine control unit only commands the electrohydraulic servo valve to move out of the first position when the engine control unit determines the aircraft is conducting a take-off roll or the aircraft is in flight.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: July 20, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Paul W. Futa, Jr., Sammuel Tillich, Steven Alan Lewis, Christopher Douglas Eick, Donald Striker, Michael Albert McPherson
  • Patent number: 11060410
    Abstract: A method of forming a protective sheath for an aerofoil component includes: providing a first sheath portion and a second sheath portion, the first sheath portion and the second sheath portion each comprising an inner surface, an outer surface and an end surface between the inner and outer surfaces and having a sacrificial flange at its distal end; positioning the first sheath portion and second sheath portion so that the inner surface of the first sheath portion abuts against the inner surface of the second sheath portion with the end surfaces of the first and second sheath portions aligned to form a mating edge; and joining the first sheath portion to the second sheath portion by welding along the mating edge, wherein the sacrificial flanges are completely consumed and a curved outer profile is formed.
    Type: Grant
    Filed: January 9, 2020
    Date of Patent: July 13, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Daniel J. Blair, Timothy J. Summers, Ewan F. Thompson
  • Patent number: 11053857
    Abstract: A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a an output shaft, drive shaft, and a retention mechanism selectively coupling the output shaft to the drive shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft.
    Type: Grant
    Filed: February 12, 2020
    Date of Patent: July 6, 2021
    Assignee: GE AVIATION SYSTEMS LLC
    Inventors: Eliel Fresco Rodriguez, David Allan Dranschak, Shiloh Montegomery Emerson Meyers, Harsha Sanjeewa Bulathsinghalage
  • Patent number: 11053926
    Abstract: A wind turbine including a support structure and one or more turbine blades is presented, that incorporates ways for reducing the radar cross section (RCS), wherein the support structure is notionally divided into an upper section in the shadow of the blade sweep area, and a lower section beneath the upper section, wherein the upper section is adapted to have the ways for reducing the RCS, and the lower section does not have the adaptation. The invention makes use of the realisation that the blade masking the tower as it rotates (or the blade being masked by the tower if facing away from a radar), contributes significantly to interference to radar systems, and so localised application of e.g. RAM can give good RCS reduction at a lower cost than treating the whole structure.
    Type: Grant
    Filed: September 26, 2019
    Date of Patent: July 6, 2021
    Assignee: QINETIQ LIMITED
    Inventors: Greg Peter Wade Fixter, Christopher Douglas James Spooner, Christopher James Perry, Vincent Savage
  • Patent number: 11053805
    Abstract: A vane ring assembly capable of preventing vibration of a vane, and wear damage caused thereby, by fixing the vane to a ring through a strong contact therebetween. The vane ring assembly includes a retaining ring having an inner peripheral surface in which a dovetail groove is formed; a vane including a dovetail inserted into the dovetail groove and an airfoil protruding from the dovetail in a radial direction of the retaining ring; and a locking key disposed between the dovetail and the dovetail groove and configured to press the dovetail into the dovetail groove. A method of assembling the vane ring assembly includes steps of inserting the dovetail into the dovetail groove; and forcibly pushing the locking key between the dovetail groove and the bottom surface of the dovetail.
    Type: Grant
    Filed: December 27, 2018
    Date of Patent: July 6, 2021
    Inventor: Joo Hwan Kwak
  • Patent number: 11047241
    Abstract: A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: June 29, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Scott W. Gayman, Brandon W. Spangler
  • Patent number: 11046422
    Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: June 29, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Marc Lavoie
  • Patent number: 11047252
    Abstract: Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (24), means (44) for taking off power from said low-pressure shaft, and a fan (28) that is driven by said low-pressure shaft by means of a reduction gear (32), said reduction gear comprising at least one first element (50) that is connected to said low-pressure shaft for conjoint rotation, at least one second element (56) that is connected to said fan for conjoint rotation, and at least one third element (52) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (60), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: June 29, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nils Bordoni, Guillaume Patrice Kubiak, Kevin Morgane Lemarchand
  • Patent number: 11047243
    Abstract: Disclosed herein is a gas turbine blade. The gas turbine blade includes a guide portion disposed adjacent to a direction-changing portion to guide the flow direction of cooling air in order to enhance the cooling efficiency of the turbine blade and promote the stable flow of the cooling air in a cooling passage.
    Type: Grant
    Filed: December 26, 2017
    Date of Patent: June 29, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Min Seok Ko
  • Patent number: 11047396
    Abstract: A bearing packing according to the invention includes a first packing having an opening portion formed therein, the opening portion allowing a rotary shaft to penetrate through the first packing, and a second packing having an opening portion formed therein, the opening portion allowing the rotary shaft to penetrate through the second packing, and configured to be brought into engagement with the first packing in a direction of the rotary shaft, and a sealed space for sealing a hydrophobic fluid in is defined around a circumference of the rotary shaft that is surrounded by the first packing and the second packing.
    Type: Grant
    Filed: June 5, 2019
    Date of Patent: June 29, 2021
    Assignee: AGATSUMA CO., LTD.
    Inventor: Shinji Todokoro
  • Patent number: 11041478
    Abstract: Provided herein is a spar cap having a profile for guiding and receiving a shear web for wind turbine blade. Particularly, the present disclosure provides a pultruded spar cap having a bond gap feature to maintain a uniform space for distribution of bonding paste between the spar cap and shear web. Also, the spar cap is formed with locating features which guide and receive placement of the shear web.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: June 22, 2021
    Assignee: TPI Composites, Inc.
    Inventors: Wayne G. Monie, Nicholas Warchol, Michael Villar
  • Patent number: 11041505
    Abstract: A rotary machine blade (31) equipped with a clearance flow suppression blade section (34), the lean angle of which has one or more inflection points, and which is formed such that when the direction from a positive-pressure surface (31a) to a negative-pressure surface (31b) is taken as the normal direction, an inflection point (P1) of the lean angle positioned farthest toward the blade end (33) changes from the negative to the positive direction in the direction away from the blade end (33).
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: June 22, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Hironori Honda, Seiichi Ibaraki, Kenichiro Iwakiri, Tadashi Kanzaka
  • Patent number: 11040767
    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
    Type: Grant
    Filed: January 2, 2018
    Date of Patent: June 22, 2021
    Assignee: General Electric Company
    Inventors: Trevor Howard Wood, Kishore Ramakrishnan, Davide Giacché, Angela Knepper, Nicholas Bown, Rathakrishnan Bhaskaran
  • Patent number: 11034438
    Abstract: A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount, wherein the one or more sensors detect one or more parameters associated with the rotating shaft or the set of rotor blades.
    Type: Grant
    Filed: November 16, 2018
    Date of Patent: June 15, 2021
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Brian Edward Tucker, Glenn Alan Shimek, Leonard N. Jones, Joseph Wendelsdorf
  • Patent number: 11035238
    Abstract: An airfoil includes an airfoil body that extends between a leading edge and a trailing edge, a suction side and a pressure side, and a first end and a second end, a fitting located at one of the first end or the second end, the fitting including a body portion, a fillet portion, and a neck portion joining the body portion and the neck portion, the neck portion including a shelf, a fastener through the airfoil body, and a shroud having a complementary shape to the shelf such that the shroud nests in the shelf.
    Type: Grant
    Filed: February 11, 2020
    Date of Patent: June 15, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas D. Stilin, Jeremy L. Fox
  • Patent number: 11028721
    Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degree Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: June 8, 2021
    Assignee: Ratheon Technologies Corporation
    Inventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
  • Patent number: 11028703
    Abstract: An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf.
    Type: Grant
    Filed: June 7, 2018
    Date of Patent: June 8, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Emma J. Place
  • Patent number: 11027834
    Abstract: An inboard bearing attachment for carrying centrifugal force (“CF”) loads in a rotor blade assembly of a rotorcraft includes a CF fitting having a curved surface and a shear bearing retainer aligned with the curved surface. A mounting flange connected to either the CF fitting or the shear bearing retainer is used to mount the inboard bearing attachment to a yoke.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: June 8, 2021
    Assignee: Textron Innovations Inc.
    Inventors: Andrew Maresh, Troy Cyril Schank, Chyausong Tzeng, John Richard McCullough, Robert Wardlaw
  • Patent number: 11021957
    Abstract: A rotor disc retention assembly of a gas turbine includes a tension bolt, a rotor disc with a hub, a web, a blade retention arrangement, a rotational axis, a first axial side and a second axial side. The hub has a central bore around the rotational axis. The web is integrally formed with and extends radially outwards from the hub to the blade retention arrangement. The blade retention arrangement has a centre of mass. A radial plane perpendicular to the rotational axis passes through the centre of mass. The first axial side engages the tension bolt. The radial plane intersects the hub defining a first axial side portion towards the first axial side and a second axial side portion towards the second axial side. The second axial side portion has an axial extent which is between 10% and 30% greater than an axial extent of the first axial side portion.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: June 1, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventor: Colm Keegan