Patents Examined by Dwayne J. White
  • Patent number: 10605085
    Abstract: The present disclosure relates to a plurality of disks, on which outer circumferential surfaces a plurality of blades are arranged, and has an objective to provide a gas turbine disk including a plurality of cooling channels penetrating the side surfaces of the disks and spaced from each other in a circumferential direction, and reinforcement parts coupled to partial arcs of exits of the cooling channels so as to reduce stress concentrated on the cooling channels.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: March 31, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Sunghul Jung
  • Patent number: 10605097
    Abstract: A turbine rotor blade comprises: a blade effective part; a snubber disposed on radially outer side of the blade effective part; a platform disposed on radially inner side of the blade effective part; and an implanted part disposed on radially inner side of the platform. A first flow path is formed inside the implanted part for a cooling medium to pass through. A second flow path is formed inside the platform for the cooling medium having passed through the first flow to pass through. A blade effective part flow path is formed inside the blade effective part for the cooling medium having passed through the second flow path to pass through. A snubber flow path is formed inside the snubber for the cooling medium having passed through the blade effective part flow paths to pass through.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: March 31, 2020
    Assignee: Toshiba Energy Systems & Solutions Corporation
    Inventors: Kazutaka Tsuruta, Shoko Ito, Iwataro Sato
  • Patent number: 10598144
    Abstract: Embodiments of the present invention generally relate to a runner unit of a tidal power plant, and more particularly to a device for reversing a blade of the runner unit. The device according to the embodiments is lighter and more efficient with respect to known solutions which involve articulated mechanisms as it is based on a reversing servomotor including an annular piston which acts on the blade to be reversed.
    Type: Grant
    Filed: January 12, 2017
    Date of Patent: March 24, 2020
    Assignee: GE Renewable Technologies
    Inventors: Alain Mathieu, Erwan Pein
  • Patent number: 10598155
    Abstract: A wind turbine platform configured to float in a body of water and support a wind turbine thereon includes a buoyant hull platform. A wind turbine tower is centrally mounted on the hull platform and a wind turbine is mounted to the wind turbine tower. An anchor is connected to the hull platform and to the seabed, and a weight-adjustable mass is suspended from the hull platform.
    Type: Grant
    Filed: November 8, 2016
    Date of Patent: March 24, 2020
    Assignee: University of Maine System Board of Trustees
    Inventors: Habib J. Dagher, Anthony M. Viselli, Andrew J. Goupee
  • Patent number: 10598025
    Abstract: An airfoil includes an airfoil section defining an airfoil profile, the airfoil section including a core structure and a plurality of rods disposed adjacent the core structure.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Raymond Surace
  • Patent number: 10590774
    Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.
    Type: Grant
    Filed: January 22, 2015
    Date of Patent: March 17, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Kumar Bhaumik
  • Patent number: 10590779
    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 and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. 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. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10590786
    Abstract: A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.
    Type: Grant
    Filed: May 3, 2016
    Date of Patent: March 17, 2020
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Robert Charles Groves, II
  • Patent number: 10584712
    Abstract: An impeller in which blades and a shroud are bonded in a stable manner. The impeller is provided with a plurality of blades disposed on a base, and a shroud disposed facing the base across the blades. The shroud has a curved shape, wherein the shroud has a flat part in the outer periphery, protuberances are provided to flat surfaces of the blades, through-holes are provided to the flat part of the shroud, and, after the protuberances are inserted through the through-holes, the flat surfaces of the blades and the flat part of the shroud are bonded together by deforming the tips of the protuberances into thermally caulked parts larger in diameter than the opening diameters of the through-holes.
    Type: Grant
    Filed: December 26, 2014
    Date of Patent: March 10, 2020
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Hiroshi Ishikawa, Shinzo Urushidani, Yoshinori Tsurugai
  • Patent number: 10584709
    Abstract: A balance piston seal assembly for a balance piston of a compressor is provided. The balance piston seal assembly may include a balance piston seal configured to be disposed about the balance piston such that an inner radial surface of the balance piston seal and an outer radial surface of the balance piston define a radial clearance therebetween. The balance piston seal assembly may also include a plurality of heaters in thermal communication with the balance piston seal and configured to heat and thermally expand the balance piston seal and thereby increase a radial length of the radial clearance.
    Type: Grant
    Filed: March 17, 2016
    Date of Patent: March 10, 2020
    Assignee: DRESSER-RAND COMPANY
    Inventors: David J. Peer, Paul Morrison Brown, Richard J. Wiederien, Kirk Ryan Lupkes, Brian David Massey, James M. Sorokes, Mark J. Kuzdzal
  • Patent number: 10584718
    Abstract: An impeller includes a disk-shaped portion and rotor blades. The rotor blades include first rotor blades which includes a first curvature portion and second curvature portions. A center of a radius of curvature of the first curvature portion is on a first side. A center of a radius of curvature of each second curvature portion is on a second side. The radius of curvature of the second curvature portion radially outward is greater than the radius of curvature of the second curvature portion radially inward. The rotor blades include second rotor blades each of which is circumferentially between adjacent ones of the first rotor blades. Each second rotor blade includes third curvature portions. A center of a radius of curvature is on the second side. The radius of curvature of the third curvature portion radially outward is greater than the radius of curvature of the third curvature portion radially inward.
    Type: Grant
    Filed: March 12, 2018
    Date of Patent: March 10, 2020
    Assignee: NIDEC CORPORATION
    Inventor: Ryosuke Hayamitsu
  • Patent number: 10584640
    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: June 13, 2016
    Date of Patent: March 10, 2020
    Assignee: GE Aviation Systems LLC
    Inventors: Eliel Fresco Rodriguez, David Allan Dranschak, Shiloh Montegomery Emerson Meyers, Harsha Sanjeewa Bulathsinghalage
  • Patent number: 10584608
    Abstract: A gas turbine engine includes a rotor that has a rotor disk and a plurality of circumferentially-spaced blades. The rotor disk and the blades are co-rotatable about an axis. A case circumscribes the rotor. The rotor disk is tuned, with regard to centrifugal and thermal growth responsiveness, to the case for a given operational scenario of the gas turbine engine such that the rotor disk and case together provide a tuned clearance response. The operational scenario involves a series of engine events that include at least two of engine acceleration, engine deceleration, engine steady-state operation.
    Type: Grant
    Filed: July 28, 2015
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Dilip M. Shah
  • Patent number: 10584636
    Abstract: A turbine debris filter apparatus for preventing clogging of cooling holes of a turbine vane, the apparatus including a filter having non-planar geometry configured to be disposed upon a shroud of the turbine vane and a support including an interface to which the filter is attached and an opening for allowing air flow, wherein the interface is configured to receive and support the non-planar geometry and the opening is configured to align with an air inlet of the shroud.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: March 10, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS AMERICAS, INC.
    Inventors: Michael G. Durham, Scott T. Cloyd, Ramy A. Massoud, Antonio A. Melo, Tomoko Morikawa, Noah J. Rowe
  • Patent number: 10584676
    Abstract: Rotor blade assemblies for wind turbines are provided. A rotor blade assembly includes a rotor blade. In some embodiments, the rotor blade assembly further includes a surface feature configured on an exterior surface of the rotor blade, the surface feature having an exterior mounting surface. At least a portion of the exterior mounting surface has a contour in an uninstalled state that is different from a curvature of the exterior surface of the rotor blade at a mount location of the surface feature on the rotor blade. In other embodiments, the rotor blade assembly further includes a seal member surrounding at least a portion of a perimeter of the surface feature. The seal member contacts and provides a transition between the exterior surface and the surface feature.
    Type: Grant
    Filed: January 3, 2017
    Date of Patent: March 10, 2020
    Assignee: General Electric Company
    Inventors: James Robert Tobin, Scott Gabell Riddell, Michael Christopher Booth, Megan Michela Wilson
  • Patent number: 10577964
    Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: March 3, 2020
    Assignee: United Technologies Corporation
    Inventors: Jonathan Ortiz, Raymond Surace, Renee J. Jurek, Tracy A. Propheter-Hinckley
  • Patent number: 10577936
    Abstract: Turbomachinery hardware, used in a rotor assembly and a stator assembly, including an airfoil portion including a leading edge, a trailing edge, a pressure side, and a suction side, and a platform on which the airfoil portion is disposed. The platform including a platform axis, a pressure side mateface located adjacent to the pressure side of the airfoil portion and a suction side mateface located adjacent to the suction side airfoil portion, wherein a portion of a pressure side mateface includes a first geometry, and a portion of a suction side mateface includes a second geometry. The first geometry is selected from a group consisting of: oblique to a platform axis, and a first curved portion. The second geometry is selected from a group consisting of: oblique to the platform axis and a second curved portion.
    Type: Grant
    Filed: August 21, 2014
    Date of Patent: March 3, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, John W. Magowan
  • Patent number: 10577089
    Abstract: A dual axis bifilar vibration absorber system including a first bifilar vibration absorber having a first support provided with a first cantilevered end including a first opening and a second cantilevered end including a second opening. The first opening is spaced from the second opening along a first axis. A first mass is operatively connected to the first support. A second bifilar vibration absorber is collocated with the first bifilar vibration absorber. The second bifilar vibration absorber includes a support member having a first opening element and a second opening element. The second opening element is spaced from the first opening element along a second axis that is substantially perpendicular to the first axis. A second mass is operatively connected to the support member. The first mass is selectively pivotable about the second axis, and the second mass is selectively pivotable about the first axis.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: March 3, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Z. Kevin Wang, Larry B. Eastman
  • Patent number: 10570760
    Abstract: Flow path assemblies and methods for assembling such assemblies are provided. For example, a flow path assembly comprises a turbine nozzle segment including an airfoil extending axially between leading and trailing edges, an inner band defining a portion of a flow path inner boundary, and an outer band defining a portion of a flow path outer boundary. The airfoil includes a trailing edge portion defining the trailing edge and extending axially beyond the inner and outer bands such that the trailing edge is defined axially aft of the inner and outer band aft ends. The flow path assembly further comprises a shroud having a forward portion that extends axially along the trailing edge portion such that the forward portion defines the flow path outer boundary at the trailing edge portion. Methods of assembling flow path assemblies having a turbine nozzle assembly and inner and outer members also are provided.
    Type: Grant
    Filed: April 13, 2017
    Date of Patent: February 25, 2020
    Assignee: General Electric Company
    Inventor: Victor Hugo Silva Correia
  • Patent number: 10570749
    Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Charles Thistle, Yongxiang D. Xue