Patents Examined by Igor Kershteyn
  • Patent number: 11028695
    Abstract: A steam turbine according to an embodiment of the present invention includes: a rotor configured to rotate about an axis; a casing which houses the rotor; and a first stage including a first-stage stationary vane fixed to an inner wall portion of the casing and a first-stage rotor blade fixed to the rotor at downstream of the first-stage stationary vane. The rotor includes a first cavity having a concave shape and being formed on a portion facing the first-stage stationary vane, the first cavity being in communication with an inner space defined between the inner wall portion and the rotor at upstream of the first-stage stationary vane. The first-stage stationary vane includes a first-stage through hole which is in communication with the first cavity and which is formed through the first-stage stationary vane in a radial direction.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: June 8, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Ryo Takata, Soichiro Tabata
  • Patent number: 11028720
    Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the attachment tabs of each ring sector are maintained. The turbine ring assembly includes a first and a second annular flanges removably fastened to the first radial clamp, the second annular flange including a bearing shroud protruding upstream in the axial direction and having a radial bearing in contact with the central shroud.
    Type: Grant
    Filed: March 13, 2018
    Date of Patent: June 8, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Fabrice Marcel Noël Garin, Lucien Henri Jacques Quennehen
  • Patent number: 11028708
    Abstract: An impeller tube-type nozzle for a gas turbine, with an inlet section, a retraction section and an outlet section. The inlet section is a section of annular channel, the retraction section comprises multiple gas flow channels separated by multiple blades, each gas flow channel is encircled by an outer peripheral wall face, an inner peripheral wall face, a suction face of one of two adjacent blades and a pressure face of the other of the two adjacent blades, and inlets of the gas flow channels have a fan-shaped cross section. For each gas flow channel, along the direction of gas flow from the inlet of the gas flow channel to the outlet the fan-shaped cross section gradually smoothly transitions into a circular cross section.
    Type: Grant
    Filed: July 28, 2017
    Date of Patent: June 8, 2021
    Assignee: AECC COMMERCIAL AIRCRAFT ENGINE CO., LTD.
    Inventors: Jianbo Lyu, Hualing Luo, Shuzhen Hu, Xiande Pan, Guofeng Liu
  • Patent number: 11028710
    Abstract: A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: June 8, 2021
    Assignee: Siemens Energy, Inc.
    Inventors: David G. Maire, Daniel J. Ryan, Dhafer Jouini, Ahmed Kamel, Gerald J. Bruck
  • Patent number: 11021975
    Abstract: The gas turbine engine can have a first and second rotary components structurally joined to one another via a connector, a first spigot fit between the connector and the first rotary component, the first spigot fit forming an interference fit at a first operating condition and forming a gap at a second operating condition, a second spigot fit between the connector and the first rotary component, the second spigot fit forming an interference fit at the second operating condition and forming a gap at the first operating condition, the gas turbine engine being further configured to form a radial interference fit between the connector and the second rotary component in both the first and second operating conditions.
    Type: Grant
    Filed: February 12, 2019
    Date of Patent: June 1, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Yves Roussel, Max Bergeron-Fillion
  • Patent number: 11021990
    Abstract: A shroud assembly for gas turbine engine defining an axial direction, a radial direction, and a circumferential direction includes a shroud segment extending substantially along the circumferential direction and including a forward wall and an aft wall spaced along the axial direction from one another and defining a cavity therebetween; and a hanger assembly including a first attachment member and a seal member, the first attachment member attached to one of the forward wall or the aft wall of the shroud segment, and the seal member positioned within the cavity and interference fit against the other of the forward wall or the aft wall of the shroud segment.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventor: Sergio Filippi
  • Patent number: 11021963
    Abstract: A component is provided for a gas turbine engine. This component includes a monolithic body configured with an internal passage. The internal passage extends along a centerline within the monolithic body. The internal passage has a cross-sectional geometry perpendicular to the centerline. The cross-sectional geometry of at least a first portion of the internal passage has a teardrop shape.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence A. Binek, Jesse R. Boyer
  • Patent number: 11021233
    Abstract: An actuator rod assembly for a blade pitch control system is provided herein. The actuator rod assembly includes a tubular outer rod and an inner rod. The outer rod has a first end and a second end. The inner rod has a first end and a second end and extends through the tubular outer rod. The inner rod is tensioned against the tubular outer rod so as to place the outer rod in compression.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: June 1, 2021
    Assignee: CLAVERHAM LIMITED
    Inventors: Suat Bekircan, Paul Brewer, Reg Raval
  • Patent number: 11021988
    Abstract: A turbine ring assembly including ring sections forming a turbine ring and a ring support structure, each ring section having, along a section plane defined by an axial direction and a radial direction of the ring, a part forming an annular base with, in the radial direction, an inner face and an outer face, from which a first and a second fastening lug project, the structure including a central shroud, from which a first and a second radial clamp project, between which the fastening lugs of each ring section are maintained. It includes a first and a second annular flange detachably fixed to the first radial clamp, the second annular flange including a support shroud projecting upstream in the axial direction and having a radial support in contact with the central shroud.
    Type: Grant
    Filed: March 13, 2018
    Date of Patent: June 1, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul Tableau, Sebastien Serge Francis Congratel, Clement Jean Pierre Duffau, Fabrice Marcel Noel Garin, Lucien Henri Jacques Quennehen
  • Patent number: 11014202
    Abstract: An applicator tool (40) for repairing damage (26) to a wind turbine blade (20) includes a spatula (42) including a flexible extrusion plate (44) and one or more spacers (60, 106) positioned proximate an inner surface (58) of the extrusion plate (44). The one or more spacers (60, 106) are configured to define a gap between an outer surface (34) of the wind turbine blade (20) and the inner surface (58) of the extrusion plate (44). A feed tube (86) is provided for supplying a coating material to the spatula (42), wherein the spatula (42) is configured to shape the coating material into a coating (30) over a damaged area (26) of the wind turbine blade (20).
    Type: Grant
    Filed: January 25, 2021
    Date of Patent: May 25, 2021
    Assignee: Vestas Wind Systems A/S
    Inventors: Aksel Petersen, Claus Engholm Nielsen, Lean Frandsen, Anders Tuxen, Ivar J. B. K. Jensen
  • Patent number: 11015618
    Abstract: A centrifugal compressor includes a compressor impeller attached to a rotary shaft and a housing accommodating the rotary shaft and the compressor impeller. The housing includes a suction portion formed upstream of the compressor impeller and a high pressure part formed on a rear face side of the compressor impeller and having a pressure higher than a pressure in the suction portion during rotation of the compressor impeller. The housing has a discharge passage formed for connecting the high pressure part to a low pressure part including the suction portion and a gas flow path upstream of the suction portion.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: May 25, 2021
    Assignee: IHI Corporation
    Inventors: Kuniaki Iizuka, Takashi Yoshida, Yuji Sasaki, Tatsumi Inomata, Takuya Ozasa, Ryosuke Yumoto, Takashi Mori
  • Patent number: 11015573
    Abstract: A wind turbine blade includes a first blade section and a second blade section configured to be coupled together at a joint interface. The blade further includes a connection joint for coupling the first and second blade sections together. The connection joint includes a plurality of connecting elements integrated into the first and second blade sections at the first and second blade interfaces. The connection joint further includes cross pins and fasteners for making the connection. A method of making a wind turbine blade section and a wind turbine blade made from such sections are also disclosed.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: May 25, 2021
    Assignee: Vestas Wind Systems A/S
    Inventor: Anton Bech
  • Patent number: 11015484
    Abstract: An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: May 25, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Gilles Gérard Claude Lepretre, Thierry Guy Xavier Tesson, Hubert Jean-Yves Illand, Lucien Henri Jacques Quennehen, Matthieu Arnaud Gimat
  • Patent number: 11015571
    Abstract: Inner covering for wind turbine blades and method for mounting same, wherein said covering consists of a wall cover with a flexible wall which is formed based on layers of composite materials, having shapes and dimensions being approximately the same as those of the inner area of the blade structural element, said cover being mounted on a support with which it is introduced inside the blade. Between the support and the cover, an inflatable chamber is arranged, which upon being inflated causes the cover to be compacted and adhered against the inner surface of the blade structural element.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: May 25, 2021
    Assignee: EMPRENDING BUSINESS, S.L.
    Inventor: Emmanuel Garcia De La Pena Razquin
  • Patent number: 11008112
    Abstract: A Laminar Inducing Apparatus (LIA) inducing laminar airflow to a turbine engine or a propulsion fan. The LIA produces turbulent-free airflow with a light aerospace structure that can replace single purpose structure in the wing or empennage. Laminar airflow to the propulsion fan or the turbine engine is ensured in a greater number of flight conditions and angles of attack. Active control of flight can be enhanced by the manipulating the turbulent boundary surface as a flight control surface. LIA simply reduces the risk of FOD or bird strike damage. In addition to the engineered, laminar benefits, LIA provides greater safety from ground ingested FOD and more silent vertical take-off and landing. In summary, LIA ensures laminar airflow and acoustic attenuation to a propulsion fan or a turbine engine for a greater number of flight conditions, angles of attack, and from ground ingested FOD during vertical takeoff and landing.
    Type: Grant
    Filed: June 7, 2019
    Date of Patent: May 18, 2021
    Inventor: Bryan B Solstin
  • Patent number: 11008894
    Abstract: A clip for an air seal assembly, comprising a clip base having a control ring interface; a biasing element coupled to the clip base opposite the control ring interface; wherein the clip is insertable into a clip receiver and configured to engage a notch of a blade outer air seal and configured to detachably couple with a clip mounting flange.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: May 18, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Dean W. Johnson, Thomas E. Clark
  • Patent number: 11009027
    Abstract: A vacuum rotor system is provided comprising a hollow rotor with a rotor jacket that is open at both ends perpendicular to the axis of rotation and with at least two hubs that are connected to the inside of the rotor jacket and that are suitably mounted in appropriate bearings so that the rotor can rotate. A machine housing that encloses the rotor and that has at least one gas outlet opening to discharge gases from the machine housing. A vacuum system that is connected to the gas outlet opening and that has at least one forepump for generating a fore-vacuum pressure in the machine housing. At least one first gas removal device with a gas pick-up opening is arranged in the machine housing between the hub and the appertaining open end of the rotor jacket.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: May 18, 2021
    Inventors: Hubert Reischl, Edwin Zimmermann
  • Patent number: 11008874
    Abstract: A turbine blade includes a root to be mounted to a rotor; a platform having an inner side and an outer side, the inner side being coupled to the root; an airfoil extending from the outer side of the platform in a radial direction of the rotor and including an outer end on which a blade tip is formed; a protrusion formed in the blade tip; and a blade cooling passage that is formed inside the airfoil and communicates with an exit hole formed in the blade tip, the blade cooling passage to pass cooling fluid through the airfoil such that the cooling fluid exits the airfoil through the exit hole. The protrusion includes an outer side surface that is flush with an outer end surface of the airfoil and protrudes in a direction perpendicular to the radial direction to prevent hot combustion gas from invading the blade cooling passage.
    Type: Grant
    Filed: April 25, 2019
    Date of Patent: May 18, 2021
    Inventor: Seok Beom Kim
  • Patent number: 11008872
    Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
    Type: Grant
    Filed: December 14, 2018
    Date of Patent: May 18, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
  • Patent number: 11008946
    Abstract: A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the static components axially movable relative to each other, the sealing assembly including the two static components and a sealing element segmented in the circumferential direction, a first end of the sealing element being axially coupled in a groove at the first sealing bank facing an opposite second end bearing axially against the second sealing bank, as well as a stator vane assembly including a casing component of an axial turbomachine, which has at least one casing hook, and further including a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook which projects from the platform and bears against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air.
    Type: Grant
    Filed: June 19, 2019
    Date of Patent: May 18, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Janine Sangl, Armin Kammerer