Patents Examined by Christopher Verdier
  • Patent number: 10731503
    Abstract: A turbocharger (10) comprising: a rotating shaft (14); a turbine wheel (12); a turbine housing (31); a scroll flowpath (34) having gas flowing therethrough that rotates and drives the turbine wheel (12); a nozzle flowpath (35) that guides gas radially inwards from the scroll flowpath (34) and supplies gas to the turbine wheel (12); and a vane (53) that adjusts the amount of gas introduced in the nozzle flowpath (35). The vane (53) comprises a guide section (60) that guides the gas flow (F) in the turbine wheel (12) radially inwards.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: August 4, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Toyotaka Yoshida, Toru Hoshi, Yosuke Dammoto, Yoji Akiyama
  • Patent number: 10731658
    Abstract: An axial fan includes a motor, an impeller, and a housing including a tubular air channel wall portion. The impeller includes a tubular impeller hub, and arranged in a circumferential direction on the impeller hub. Each blade includes a first portion where all of an inner circumferential developed blade, an outer circumferential developed blade, and an intermediate circumferential developed blade superimposed on each other overlap. The inner circumferential developed blade is a junction of the blade with the outer surface of the impeller hub. The outer circumferential developed blade is a radially outermost portion. The intermediate circumferential developed blade is a radially intermediate portion of the blade between the junction and the radially outermost portion. The radially outermost portion is at the shortest radial distance from the air channel wall portion in at least a portion of the first portion.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: August 4, 2020
    Assignee: NIDEC CORPORATION
    Inventors: Kazuhiro Inouchi, Junya Matsuyama
  • Fan
    Patent number: 10724536
    Abstract: A fan for a gas turbine engine, the fan comprising a first set of fan blades, each fan blade comprising a root and an axial retention feature provided on the root at a first position, and a second set of fan blades, each fan blade comprising a root and an axial retention feature provided on the root at a second position. Relative to the respective blade on which the respective retention feature is provided, the first position is different to the second position.
    Type: Grant
    Filed: February 16, 2018
    Date of Patent: July 28, 2020
    Assignee: Rolls-Royce plc
    Inventors: Antonios Kalochairetis, Gabriel Gonzalez-Gutierrez
  • Patent number: 10723448
    Abstract: A weight system for a rotor blade includes a weight box open in an outboard direction, a weight guide rod connected to the weight box, the weight guide rod extending in a spanwise direction through an interior of the weight box, and a span balance weight disposed within the weight box, the span balance weight being captured between the weight guide rod and the weight box.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: July 28, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Jared Mark Paulson, Bryan Marshall, Paul Sherrill, Bryan Judd
  • Patent number: 10724400
    Abstract: A support assembly for a load-bearing unit, a gas turbine engine including the support assembly, and a method of operation of the support assembly are provided. The support assembly includes a support element, a damper, and a variable stiffness member. The support element supports the load-bearing unit. The damper supports the support element and is configured to provide dampening of the load-bearing unit. The variable stiffness member is positioned between the damper and the load-bearing unit. The variable stiffness member is configured to provide a serial dampening of the load-bearing unit with the damper. The variable stiffness member includes a shape memory alloy.
    Type: Grant
    Filed: April 10, 2018
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: Shivaram Ac, Vidyashankar Ramasastry Buravalla, Ravindra Shankar Ganiger, Shuvajyoti Ghosh, Akash Joshi
  • Patent number: 10724392
    Abstract: A seal member is between a combustor around a rotor axis and a vane on a downstream side in an axial direction and defining a part of a combustion gas flow passage through which combustion gas is configured to flow, the seal member being configured to seal a gap between the combustor and the vane. The seal member has: an end face that faces the downstream side in the axial direction so as to face a lateral end face of the vane facing an upstream side in the axial direction; cooling channels through which cooling air is configured to be discharged from a plurality of openings defined in the end face in an array in a circumferential direction based on the rotor axis; and a clearance forming portion that protrudes further toward the downstream side in the axial direction than the end face in which the openings are defined.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: July 28, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kenta Taniguchi, Kenji Sato
  • Patent number: 10718221
    Abstract: A system for directing the flow of a fluid which comprises a channel for containing the fluid; an articulating vane positioned within the channel for directing the flow of the fluid, the vane comprising a fixed segment rigidly connected to the channel and a first moveable segment operably connected to the fixed segment by a first hub, the first hub configured to allow relative articulation between the segments; an actuator member operably connected to the moveable segment to articulate the moveable segment about the first hub; and wherein the vane further comprises a second moveable segment operably connected to the vane by a second hub, wherein the actuator member articulates the first and second moveable segments by applying a single moment to the first hubs.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: July 21, 2020
    Assignee: ROLLS ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Edward C. Rice
  • Patent number: 10710687
    Abstract: A front propeller on a main shaft communicated from one end to an engine transmission; the propeller having a hub and a plurality of blades extending radially outwardly from the hub; a rear propeller co-axially to, and spaced apart from, the front propeller rearwardly in an axial direction having a hub and a plurality of blades extending radially outwardly from the hub. An adaptor is coaxial with the main shaft and comprising a second shaft for supporting the rear propeller. A plurality of pitched-formed seating surfaces having ramps, are spaced apart from the second shaft in an axial direction. An adaptor communicates with the rear side of the front propeller in the axial direction; a plurality of locking elements are movable in the axial direction, each being in contact with the seating surfaces of the adaptor, and communicate with the rear propeller from the other end.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: July 14, 2020
    Inventor: Mehmet Nevres Ulgen
  • Patent number: 10711616
    Abstract: An airfoil includes a core structure that has an airfoil portion that defines at least a portion of an airfoil profile. The airfoil portion has first and second opposed ends. A support wall extends from the first end. An endwall panel is attached to the support wall adjacent the airfoil portion.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: July 14, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Raymond Surace
  • Patent number: 10703466
    Abstract: A propulsor hub is provided and includes a casing including an inner annular part and blade-connection parts extending outwardly from the inner annular part, a liner having inner and outer opposed radial ends, the liner being disposed about a corresponding one of the blade-connection parts with the inner radial end thereof at a distance from the inner annular part and a weighted element securely disposed about the corresponding one of the blade-connection parts to abut the outer radial end of the liner.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: July 7, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: David A. Darrow, Jr., Ron William Waldo, Christopher L. Winslow
  • Patent number: 10702964
    Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
    Type: Grant
    Filed: December 4, 2017
    Date of Patent: July 7, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Patrick D. Couture
  • Patent number: 10704531
    Abstract: A wind turbine rotor blade with a rotor blade tip, a rotor blade root, and a rotor blade connection in the region of the rotor blade root with a rotationally symmetrical flange coupling is provided which has a first and a second end. The first end of the flange coupling has multiple bores for receiving fastening means for fastening to a hub of a wind turbine. The second end is fastened in or on material of the rotor blade root. The second end extends in the direction of an axis of rotation of the flange coupling.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: July 7, 2020
    Assignee: Wobben Properties GmbH
    Inventor: Alexander Hoffmann
  • Patent number: 10697310
    Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: June 30, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Corey D. Anderson, Jeremy Styborski
  • Patent number: 10697320
    Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.
    Type: Grant
    Filed: January 10, 2018
    Date of Patent: June 30, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Roy D. Fulayter, Michael G. Meyer
  • Patent number: 10697425
    Abstract: A shear web for a wind turbine blade is described. The shear web comprises a panel and a web head. A longitudinal edge of the panel is received within a slot defined in the web head. A plurality of discrete spring features are attached to the longitudinal edge of the panel. The spring features are mutually spaced apart at intervals along the length of the longitudinal edge. The spring features compress against a base of the slot when the longitudinal edge region of the panel is inserted into the slot.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: June 30, 2020
    Assignee: Vestas Wind Svstems A/S
    Inventors: Anton Bech, Steve Wardropper
  • Patent number: 10690008
    Abstract: A steam turbine casing includes a lower half part having a plurality of lower support portions projecting horizontally around a lower half part body; an upper half part connected onto the lower half part; a support member fixed to an upper surface part of a respective one of the lower support portions; and a plurality of support columns each having a lower end part on a frame and an upper end part to which a lower surface part of the support member fixed to a corresponding one of the lower support portions. Thus, thermal deformation of the casing is suppressed, and a suitable clearance can be maintained between the casing and a turbine.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: June 23, 2020
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yukihiro Otani, Takahiro Miyamoto, Tomoyuki Onishi, Katsuhisa Hamada
  • Patent number: 10683759
    Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: June 16, 2020
    Assignee: General Electric Company
    Inventors: William Scott Zemitis, Jacob Charles Perry, II, Melbourne James Myers, Ajay Gangadhar Patil, Richard Ryan Pilson
  • Patent number: 10677091
    Abstract: An airfoil includes a supply passage to provide a coolant, an airfoil section that has walls that define an internal cavity, a baffle seated in the internal cavity, and a seal proximate the edge of the baffle. The baffle is seated such that there is a gap between the baffle and at least one of the walls. The baffle includes a baffle wall that has cooling holes and that defines an interior baffle region. The seal seals off the gap such that the coolant that exits the supply passage will be directed to flow into the interior baffle region.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: June 9, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10676954
    Abstract: A lightweight, portable battery-powered overhead fan including secure attachments for a standard outdoor canopy or other like article is provided. Such a fan further includes blades that are configured with resilient connectors that allow for such blades to tilt or fold for stowing purposes while also securely attaching during actual use in a safe and reliable manner. In this way, each blade attaches to a centrally located portion that rotates during fan operation. The canopy attachments are provided in stowable fashion as well to permit compact transport of the overall fan device to and from an event for which a canopy is erected. Such a device further includes the potential for a fluid reservoir and atomizer component to deliver fluid droplets for increased cooling purposes as well as a light integrated therein or attached thereto. A canopy including such a fan device is also encompassed within this invention.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: June 9, 2020
    Inventor: Matthew Oppenheim
  • Patent number: 10677080
    Abstract: A seal system for a moving blade system of a gas turbine includes a seal carrier including a ring section extending in the axial direction and the circumferential direction, on which a radially inner seal element is situated. A first flange section and a second flange section extend outwardly from the ring section in the circumferential direction and the radial direction and are situated at a distance from each other in the axial direction. An inner shroud section of at least one guide blade or of at least one guide blade segment includes a sealing section extending inwardly in the radial direction and in the circumferential direction, the sealing section being accommodated between the first flange section and the second flange section of the seal carrier and being connected thereto. A disk-like first seal is situated upstream from the first flange section with respect to the main flow direction of a working medium and partially abuts the first flange section radially inwardly.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: June 9, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Hermann Klingels