Patents Examined by Eric J Zamora Alvarez
  • Patent number: 10738760
    Abstract: The present invention is a vertical axis wind turbine contained in a housing designed to introduce turbulent flow to increase efficiency. One embodiment of the invention uses a three bladed propeller with deflectors mounted upstream of the propeller to increase the pressure on the trailing edge of the blades. In another embodiment, an electric generator is coupled to the vertical axis wind turbine to convert the kinetic energy of a moving fluid into electricity.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: August 11, 2020
    Inventor: Catalin Tutunaru
  • Patent number: 10738627
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Grant
    Filed: January 15, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • Patent number: 10731470
    Abstract: An airfoil defining a chordwise dimension, a spanwise dimension, a leading edge, a trailing edge, a root, and a tip, is generally provided. The airfoil includes a first material substrate defining a pressure side and a suction side. The first material substrate defines a plurality of discrete volumes extended from at least one of the pressure side or the suction side into the first material substrate. The plurality of discrete volumes is arranged at least partially along the chordwise dimension and a second material substrate different from the first material substrate is defined at least partially within the volume.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventor: David William Crall
  • Patent number: 10731469
    Abstract: A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.
    Type: Grant
    Filed: September 6, 2017
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: JinQuan Xu, James Tilsley Auxier
  • Patent number: 10731492
    Abstract: A component joint including a turbomachine component (10) having at least one component flange (11); a mating turbomachine component (20) connected thereto and having at least one mating component flange (21); and at least one seal (30) to provide a seal against an overpressure (p2?p1) on the component side, the at least one seal (30) having a sealing surface (31) that engages into a groove (12) of the turbomachine component (10), the groove (12) being disposed on a mating-component-flange-facing side of the component flange (11) and having a contact surface (13) for sealingly axially supporting the sealing surface (31).
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: August 4, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Alexander Kloetzer, Manfred Feldmann
  • Patent number: 10718350
    Abstract: A fan blade for a fan of a gas turbine engine is described which includes an airfoil having an inner core and an outer shell composed of different metals, and a galvanic separator therebetween. The galvanic separator including an adhesive layer covering said at least a portion of the inner core, and a non-conductive fabric covering the adhesive layer. A plurality of solid metal particles may be disposed on an outer surface of the non-conductive fabric layer, between the non-conductive fabric layer and the outer shell.
    Type: Grant
    Filed: November 24, 2016
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Kin-Leung Cheung
  • Patent number: 10718312
    Abstract: A wind turbine comprising a support structure for supporting a rotatable, substantially vertical hub wherein at least one substantially horizontal support arm is connected to the hub. At least one wind trap is connected to each of the at least one support arm, and each of the at least one wind trap supports at least one petal that may move between an open position, wherein wind is not blocked by the at least one petal, and a closed position, wherein the at least one petal blocks the wind thereby causing the wind to move the at least one wind trap and rotate the hub.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: July 21, 2020
    Assignee: Flying Diamonds Energy Company LLC
    Inventors: Brian Oslin, Alva B. Oslin
  • Patent number: 10711643
    Abstract: A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.
    Type: Grant
    Filed: August 25, 2017
    Date of Patent: July 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Cottet, Fabrice Michel François René Cretin, Christophe Paul Jacquemard, Christophe Marcel Lucien Perdrigeon, Leny Toribio
  • Patent number: 10683871
    Abstract: A novel fan blade support device is disclosed. The device may be installed on ceiling fan blades to provide support to the blade to prevent sagging and drooping. In another embodiment, the support device may be integrally installed into fan blades to prevent sagging and drooping.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: June 16, 2020
    Inventor: Joseph Cory Armstrong
  • Patent number: 10662965
    Abstract: A sealing structure includes: an insertion hole formed in a sealing plate; a sealing ring provided in the insertion hole; a first rotating body provided to the shaft, at least a part of the first rotating body positioned inside the insertion hole; a second rotating body disposed at a position apart from the compressor impeller than the first rotating body and having a maximum outer diameter larger than a minimum inner diameter of the insertion hole; and an annular receiving groove formed by the first rotating body and the second rotating body and receiving an inner circumferential surface side of the sealing ring.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: May 26, 2020
    Assignee: IHI Corporation
    Inventors: Yoshiaki Hirai, Nobuyuki Ikeya, Kouta Kimachi
  • Patent number: 10661890
    Abstract: A blade of a rotor for a rotary-wing aircraft is equipped with an outer covering extending along the span of the blade. This outer covering is provided with an extrados skin and with an intrados skin defining a cavity. The blade also includes a structure that extends into the cavity and connects the blade to a hub of the rotor. The cavity is filled with a filling material that includes at least one partition parallel to a chord of the blade and at least two independent blocks of filling material filling the cavity, thereby allowing the reduction of the torsional rigidity along the span of the blade.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: May 26, 2020
    Assignee: Airbus Helicopters
    Inventors: Damien Reveillon, Laurent Bianchi
  • Patent number: 10655480
    Abstract: According to one embodiment, a mini-disk of a gas turbine engine having an axis is provided. The mini-disk includes a bore, a web extending radially with respect to the axis of the gas turbine engine from the bore, a base extending axially with respect to the axis of the gas turbine engine from the bore, a connector located on an end of the base, the connector configured to connect with a hub arm of the gas turbine engine, and an expansion feature configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.
    Type: Grant
    Filed: January 18, 2016
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, Julian Partyka
  • Patent number: 10641284
    Abstract: A centrifugal blower assembly includes a housing and a blower wheel coupled to the housing. The blower wheel includes a plurality of blades circumferentially-spaced about an axis of rotation. Each blade includes a length and is oriented at a first angle along the length with respect to the rotational axis. The centrifugal blower assembly also includes a plurality of circumferentially-spaced fins coupled in flow communication with said blower wheel, said plurality of fins configured to direct an inlet airflow into the blower wheel such that a relative velocity direction of the inlet airflow is oriented at the first angle with respect to the rotational axis.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: May 5, 2020
    Assignee: REGAL BELOIT AMERICA, INC.
    Inventors: Sahand Pirouzpanah, Shradha S. Nahar
  • Patent number: 10626742
    Abstract: An inner ring according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface as well as a plurality of bearing mounts for a respective guide vane plate of a guide vane. The bearing mounts each have an opening in the outer inner ring surface as well as a bottom face lying radially opposite the opening. At least two of the bearing mounts are separated from each other by a separating wall and are connected to each other in a region of their bottom face by a through-opening. A guide vane cascade according to the invention for a turbomachine has an inner ring according to the invention and a plurality of guide vanes inserted into the bearing mounts.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: April 21, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Lothar Albers, Georg Zotz, Vitalis Mairhanser
  • Patent number: 10619495
    Abstract: A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: April 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Gérard Edmond Joly, François Jean Comin, Laurent Jablonski, Damien Merlot, Jean-Marc Claude Perrollaz
  • Patent number: 10619485
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: April 14, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Pierre Hervé Fernand Marche, Ludovic Pintat, Vincent Nicolas Leonardon, Thomas Michel Julien Mervant, Renaud Gabriel Constant Royan
  • Patent number: 10612415
    Abstract: An assembly for rotational equipment includes a stationary structure and a rotating structure. The stationary structure is configured with a first fluid conduit. The rotating structure is configured with a second fluid conduit and a fluid scoop for the second fluid conduit. The second fluid conduit is fluidly coupled with the first fluid conduit through an annular plenum formed by and radially between the stationary structure and the rotating structure. The fluid scoop projects radially into the annular plenum.
    Type: Grant
    Filed: August 29, 2017
    Date of Patent: April 7, 2020
    Assignee: United Technologies Corporation
    Inventor: Hung Duong
  • Patent number: 10612515
    Abstract: A vertical axis wind turbine (VAWT) with improved and optimized wind-directing, wind-shaping, and wind-power conversion features is disclosed. The shapes of these features directly affect the ability of the VAWT to use the power of moving air, such as wind, to spin a rotor and create torque on a rotor shaft to generate electricity. The wind-power-conversion mechanical efficiency of the invention is significantly improved over previous efforts, to the point that the invention can convert wind energy into electrical power at a price-to-performance ratio that competes with or surpasses existing alternative energy technologies.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: April 7, 2020
    Assignee: DME Wind Energy Corporation
    Inventors: Sid J. Reyna, Patrick R. Conarro
  • Patent number: 10605098
    Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: March 31, 2020
    Assignee: General Electric Company
    Inventors: Thomas Earl Dyson, Nicholas William Rathay, Brendon James Leary, Gregory Terrence Garay, Gustavo Adolfo Ledezma, David Wayne Weber, Aaron Ezekiel Smith
  • Patent number: 10598149
    Abstract: A rotor blade of a wind turbine including at least one vortex generator is provided. The vortex generator is attached to the surface of the rotor blade and is located at least partially within the boundary layer of the airflow flowing across the rotor blade. The vortex generator is exposed to a stagnation pressure, which is caused by the fraction of the airflow passing over the vortex generator and of which the magnitude depends on the velocity of the fraction of the airflow passing over the vortex generator. The vortex generator is arranged and prepared to change its configuration depending on the magnitude of the stagnation pressure acting on the vortex generator. Furthermore, an aspect relates to a wind turbine for generating electricity with at least one such rotor blade.
    Type: Grant
    Filed: June 30, 2017
    Date of Patent: March 24, 2020
    Assignee: SIEMENS GAMESA RENEWABLE ENERGY A/S
    Inventors: Busra Akay, Peder Bay Enevoldsen