Patents Examined by Woody A Lee, Jr.
  • Patent number: 11225949
    Abstract: A blade tip assembly for a wind turbine blade, comprising a conductive blade tip module, a receptor arrangement spaced from the conductive blade tip module, a coupler that electrically couples the conductive blade tip module to the receptor arrangement and an insulating member that insulates the coupler. The invention also can be expressed as a method for assembling a blade tip assembly for a wind turbine blade, the method comprising providing a blade tip module; providing the blade tip module with a coupler for electrically coupling the blade tip module to a down conductor of a lightning protection system; and encasing the coupler with an insulating member.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: January 18, 2022
    Assignee: Vestas Wind Systems A/S
    Inventors: Daniel Whitehouse, Richard Baker
  • Patent number: 11225912
    Abstract: A gear assembly for a gas turbine engine has an input gear adapted to be secured to a turbine shaft. An output gear is adapted to be secured to a compressor shaft, the input gear and the output gear having the same number of teeth. A pair of idler gear shafts is provided, each said idler gear shaft having a first stage gear meshed with the input gear to be driven by the turbine shaft at a first stage of speed change. A second stage gear is axially spaced from the first stage gear and rotates with the first stage gear. The second stage gear is meshed with the output gear to drive the compressor shaft at a second stage of speed change. Landmarks are provided for aligning the gears during assembly in a desired orientation.
    Type: Grant
    Filed: April 20, 2018
    Date of Patent: January 18, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Lazar Mitrovic
  • Patent number: 11221012
    Abstract: A turbo fluid machine includes a housing, a rotating member, and a motor. Part of fluid compressed by a compressor impeller is introduced into a motor accommodation space through an inlet-side flow passage that has an inlet-side fixed throttle, and is discharged from the motor accommodation space through an outlet-side flow passage that has an outlet-side fixed throttle. The outlet-side flow passage includes a connection part connecting to the motor accommodation space. The connection part is formed separately from a clearance between a second partition wall and a shaft, and is located opposite to a connection part of the inlet-side flow passage connecting to the motor accommodation space across the motor in an axial direction of the shaft. The inlet-side fixed throttle and the outlet-side fixed throttle are configured such that pressure in the motor accommodation space is higher than pressure in a turbine-wheel back pressure region.
    Type: Grant
    Filed: February 18, 2020
    Date of Patent: January 11, 2022
    Assignee: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI
    Inventors: Hidefumi Mori, Junya Suzuki, Kazuki Okazaki
  • Patent number: 11221020
    Abstract: A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: January 11, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Ghislain Maxime Romuald Madiot, Jean Bertucchi, Damien Joseph Cellier, Irwin Pierre Robert Kernemp, Aurelien Mazzella
  • Patent number: 11220325
    Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding that accommodates at most one of the at least two rotor assemblies, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein the air inlet region exhibits in circumferential direction of the cylindrical air duct an undulated geometry.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: January 11, 2022
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Uwe Kiesewetter, Sebastian Mores, Marius Bebesel, Rupert Pfaller
  • Patent number: 11220930
    Abstract: A turbine shroud assembly includes a carrier, a blade track segment, and an attachment pin. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a runner that faces the axis to define a portion of a primary gas path of the gas turbine engine and an attachment flange that extends radially away from the runner. The attachment pin is configured to mount the blade track segment to the carrier.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: January 11, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 11220915
    Abstract: A component wall of a hot gas component for a gas turbine, which in a double-walled design, has an outer wall which is hotter and an inner wall which is cooler during operation. The interior is divided by partition walls extending between the inner and outer walls. A coolant flows into the interior through inlet openings in the inner wall and out through outlet openings in the outer wall. An inlet cavity is directly connected to at least one of the inlet openings without being directly connected to outlet openings. A second cavity is provided directly next to the inlet cavity. The second cavity is directly connected, as an outlet cavity, only to at least one of the outlet openings, without being directly connected to inlet openings. The partition wall has at least one through-opening for conducting the coolant from the inlet cavity into the outlet cavity.
    Type: Grant
    Filed: April 12, 2019
    Date of Patent: January 11, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Ole Geisen, Michael Hajduk
  • Patent number: 11220926
    Abstract: An apparatus for sealing an internal environment of a turbomachine includes a first chamber connectable in fluid communication with a high pressure environment of a turbomachine so that a working fluid can flow from the high pressure environment to the first chamber; and a second chamber in fluid communication with a lubrication circuit so that a lubricant can flow from the lubrication circuit to the second chamber. The first and second chambers are arranged in fluid communication with each other so that the working fluid can flow from the first to the second chamber. A return line for the working fluid is in fluid communication with the first chamber and connectable in fluid communication with a low pressure environment of the turbomachine so that the working fluid can flow from the first chamber to the low pressure environment. A pressure regulating device is included along the return line and is configured to provide a predetermined pressure drop.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: January 11, 2022
    Assignee: NUOVO PIGNONE SRL
    Inventors: Gabriele Mariotti, Rosaria Giordano, Lucrezia Bianco
  • Patent number: 11215055
    Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
    Type: Grant
    Filed: February 13, 2020
    Date of Patent: January 4, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Paul Stone
  • Patent number: 11215065
    Abstract: A turbine shroud assembly is adapted to extend around a turbine wheel mounted for rotation about a central reference axis of a gas turbine engine. The turbine shroud assembly includes a carrier segment made from metallic materials and a blade track segment made from ceramic matrix composite materials. The carrier extends at least partway about the axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 24, 2020
    Date of Patent: January 4, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling H. Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 11215059
    Abstract: An airfoil includes a ceramic airfoil section that defines leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The span of the airfoil section has first, second, and third radial span zones. There is a row of cooling holes in an aft 25% of the axial span. The row of cooling holes extends though the first, second, and third radial span zones. The cooling holes in the first radial span zone define a first pitch P1, the cooling holes in the second radial span zone define a second pitch P2, and the cooling holes in the third radial span zone define a third pitch P3, wherein P2<P3<P1.
    Type: Grant
    Filed: September 3, 2020
    Date of Patent: January 4, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Bryan P. Dube, Raymond Surace, Alex J. Schneider, Tyler G. Vincent
  • Patent number: 11215057
    Abstract: There is provided a turbine wheel includes a plurality of long blades and a plurality of short blades. A trailing edge of each short blade is positioned upstream of a trailing edge of each long blade in an axial direction of the turbine wheel, and at least one of a leading edge of each long blade or a leading edge of each short blade includes an inclined part which is inclined so that a distance to a rotational axis of the turbine wheel decreases toward a hub.
    Type: Grant
    Filed: January 16, 2017
    Date of Patent: January 4, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Toyotaka Yoshida, Yosuke Danmoto, Yoji Akiyama
  • Patent number: 11215191
    Abstract: A blower includes a rotor blade rotatable about a central axis extending in an axial direction, a motor that rotates the rotor blade, and a housing that surrounds the rotor blade and the motor. The housing includes stator blades extending in a forward rotation direction of the rotor blade toward an axially lower side of the blower, a porous wall including multiple holes arranged in both the radial direction and in the circumferential direction, and a cylinder portion extending in the axial direction and radially outward of the porous wall. The hole penetrates the porous wall through upper to lower surfaces thereof. The stator blade is axially below the rotor blade. An axially upper end portion of the porous wall is between an axially lower end portion of the rotor blade and an axially upper end portion of the stator blade.
    Type: Grant
    Filed: December 12, 2019
    Date of Patent: January 4, 2022
    Assignee: NIDEC CORPORATION
    Inventor: Yuta Tokuno
  • Patent number: 11215195
    Abstract: A suction-and-discharge flow path includes a circumferential flow path that extends in an arc shape about an axis and an external communication path that is connected to both ends of the circumferential flow path. The circumferential flow path has a uniform flow path cross-sectional area in a circumferential direction, and a convex curved surface having a convex curved surface shape is provided between an outer peripheral wall surface of the circumferential flow path and a second inner wall surface of the external communication path. In a case where, when viewed in the axis direction, a curvature radius of the convex curved surface is defined as R and a radial dimension of the circumferential flow path is defined as W, a relationship of W?R?3W is established.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: January 4, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Akihiro Nakaniwa, Hirofumi Higuchi
  • Patent number: 11208908
    Abstract: Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.
    Type: Grant
    Filed: December 5, 2019
    Date of Patent: December 28, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Simon Schmalfuss
  • Patent number: 11208895
    Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, compressor, and core shaft connecting turbine to the compressor; a fan located upstream of engine core, the fan containing a plurality of fan blades mounted for rotation about an engine axis, each blade of the plurality of fan blades having a leading edge and trailing edge extending across a span of an airflow duct from blade root to tip; and a gearbox that receives an input from core shaft and outputs drive to fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the trailing edge of each blade is characterized by a metric M defined as a rate of change of an angle of trailing edge between 0.4 and 0.8 of the span divided by an area averaged trailing edge angle, M being not less than around 4.
    Type: Grant
    Filed: October 7, 2020
    Date of Patent: December 28, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Benjamin Mohankumar, Mark J Wilson, Cesare A Hall
  • Patent number: 11208198
    Abstract: A vane includes a fiber reinforcement having a three-dimensional weaving densified by a matrix, the fiber reinforcement including in a single woven part a root portion and an airfoil portion extending along a longitudinal direction between the root portion and a vane tip portion and along a transverse direction between a leading edge portion and a trailing edge portion. The airfoil portion includes first and second extrados and intrados faces. The fiber reinforcement includes a non-interlinking forming a housing inside the fiber reinforcement, a conformation part being present in the housing. The non-interlinking extends over a non-interlinked area inside the airfoil portion of the fiber reinforcement included between the root portion and the vane tip portion in the longitudinal direction and between the leading edge portion and the trailing edge portion in the transverse direction, the non-interlinking also opening outside the airfoil portion of the fiber reinforcement.
    Type: Grant
    Filed: January 15, 2020
    Date of Patent: December 28, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vivien Mickaël Courtier, Dominique Gerhardt Mayhew, Adrien Jacques Philippe Fabre
  • Patent number: 11208911
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 23, 2020
    Date of Patent: December 28, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Keith Sadler, Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco
  • Patent number: 11208890
    Abstract: A boundary layer turbomachine can include a housing defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing. The boundary layer turbomachine can also include a rotor assembly disposed in the rotor chamber and configured to rotate about an axis of rotation. The rotor assembly can have a plurality of disks spaced apart along the axis of rotation and defining an interior opening along the axis of rotation. The fluid can pass through gaps between the disks and the interior opening as the fluid moves through the housing.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: December 28, 2021
    Inventors: Billy W. Helton, Mark W. Jones
  • Patent number: 11209004
    Abstract: Air compressor comprising a centrifugal-type compression wheel defining an axial direction and a radial direction, an air intake opening extending circumferentially around the compression wheel and opening onto a compression part, the compression part comprising a first portion forming a volute for the ejection of compressed air which is mounted facing the compression wheel in the radial direction, and an at least partly annular second portion extending around the first portion, the second portion comprising a central orifice receiving at least part of the compression wheel and an air deflection torus, the volute being made of metallic material and the torus made of thermoplastic material filled with non-metallic elements, the thermoplastic material having a thermal expansion corresponding to that of the metallic material.
    Type: Grant
    Filed: May 28, 2019
    Date of Patent: December 28, 2021
    Assignee: Safran Electical & Power
    Inventors: Nicolas Stefanovic, Michael Polin, Arnaud Genin