Patents Examined by Dwayne J. White
  • Patent number: 9845810
    Abstract: Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: December 19, 2017
    Assignee: Concepts NREC, LLC
    Inventor: David Japikse
  • Patent number: 9845702
    Abstract: A stator damper is disclosed. The stator damper has a body section and a damper finger. The body section rests against a stator assembly and a portion of each damper finger rests against a compressor casing. The stator damper is radially compressed between the stator assembly and the compressor casing. Thus, the stator damper exerts a radial force against the stator assembly. In this manner, relative motion of the stator assembly is damped.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: December 19, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nicholas R. Leslie, David P. Dube, Randall J. Butcher
  • Patent number: 9845707
    Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: December 19, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Alain Porte, Matthieu Fargues
  • Patent number: 9845734
    Abstract: An air turbine start system is provided that includes an air turbine starter, a starter air valve, a turbine speed sensor, and a circuit. The starter air valve is movable between an open position, in which the pressurized air may flow into the air turbine starter, and a closed position, in which pressurized air does not flow into the air turbine starter. The turbine speed sensor is coupled to the air turbine starter, and is configured to sense the rotational speed of the turbine and supply a rotational speed signal representative thereof. The circuit is coupled to receive the rotational speed signal and is configured, upon receipt thereof, to determine whether the starter air valve is in the closed position or an open position.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: December 19, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Peter Kenneth Zeiner, Dave Oman, Jimmy Wiggins
  • Patent number: 9840936
    Abstract: A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.
    Type: Grant
    Filed: February 16, 2012
    Date of Patent: December 12, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
  • Patent number: 9841035
    Abstract: A heat dissipation fan includes a base plate, a frame formed on a side of the base plate, a stator received sin the frame, and a rotor below the stator and connected with the stator. The heat dissipation fan also has an air inlet, a first air outlet and a second air outlet. The air inlet is communicated with the first air outlet and the second air outlet. An angle is defined between each of the first air outlet and the second air outlet.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: December 12, 2017
    Assignee: CHAMP TECH OPTICAL (FOSHAN) CORPORATION
    Inventors: Hong-Tao Wu, Chih-Feng Hu
  • Patent number: 9835171
    Abstract: A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.
    Type: Grant
    Filed: August 20, 2010
    Date of Patent: December 5, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Keith D. Kimmel, Jack Wilson
  • Patent number: 9835135
    Abstract: A method for controlling a wind turbine may generally include operating the wind turbine at an initial power output that is greater than a rated power output associated with the wind turbine. The wind turbine may have an anticipated operational life at the rated power output. In addition, the method may include decreasing a power output of the wind turbine over time in order to maintain an actual operating life of the wind turbine substantially equal to or greater than the anticipated operational life. A final power output of the wind turbine at an end of the anticipated operating life may be less than the rated power output.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: December 5, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Samuel David Draper
  • Patent number: 9835055
    Abstract: An exemplary pullable drawer is arranged for removably protruding in a radial direction into an outer housing of a turbine, in order to make mechanical contact with an inner carrier being concentrically arranged within the outer housing. The pullable drawer has an essentially cylindrical body, which extends along a longitudinal drawer axis. A mechanical decoupling is provided, as the pullable drawer is divided along the longitudinal drawer axis into at least separate first and second parts. The first and second parts are coupled with each other by means of a releasable mechanical joint.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: December 5, 2017
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Stefan Gerzner, Marc Rauch, Ernst Vogt, Jose-Manuel Lopez
  • Patent number: 9828105
    Abstract: A nacelle assembly for a gas turbine engine includes an integrated afterbody mount case. The integrated afterbody mount case includes an outer ring and a plurality of spokes that extend radially inwardly from the outer ring. The outer ring includes a radially outer surface and a radially inner surface. The plurality of spokes are circumferentially disposed about the radially inner surface and extend radially inwardly from the radially inner surface.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: November 28, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Thomas G. Cloft
  • Patent number: 9828876
    Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Corporation
    Inventor: Matthew J. Kappes
  • Patent number: 9829004
    Abstract: Provided is a turbofan including a shroud, a main plate, and a plurality of blades. A main plate-side shoulder surface portion is curved so as to be distanced from the rotational center axis while approaching the blade trailing edge as the main plate-side shoulder surface portion is distanced from a main plate-side blade tip portion, and has a convexoconcave shape including a blade tip section and the main plate-side blade tip portion. An inner peripheral-side leading edge section includes the inner peripheral-side blade leading edge section main plate-side portion and an inner peripheral-side blade leading edge section tip-side portion including curves that protrude rearward in the rotational direction.
    Type: Grant
    Filed: October 15, 2013
    Date of Patent: November 28, 2017
    Assignee: Mitsubishi Electric Corporation
    Inventors: Takashi Ikeda, Masahiko Takagi, Makoto Kurihara
  • Patent number: 9828860
    Abstract: A compressor blade of a gas turbine includes an airfoil made of a fiber-reinforced plastic and a leading-edge element connected to said airfoil. The leading-edge element includes two partial elements, which are fabricated as separate elements and connected to one another, with the leading-edge element being connected to the airfoil essentially using the clamping effect of the two partial elements.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 9831653
    Abstract: Provided is a cable twist allowance system for a wind turbine system. The system includes a sun gear disposed within a tower of wind turbine, a pivot disk connected with the sun gear, a plurality of lever members, each including a plurality of cables and spaced a predetermined distance apart from each other, the plurality of level members being pivotably connected with a surface of the pivot disk and rotatable about the sun gear; and a plurality of compression members, each compression member corresponding to each lever member and adjusting a position of a respective lever member based on a radial force applied to the plurality of cables of the respective lever member.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: November 28, 2017
    Assignee: GE ENERGY POWER CONVERSION TECHNOLOGY LTD
    Inventor: Allen Michael Ritter
  • Patent number: 9828867
    Abstract: A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: November 28, 2017
    Assignee: United Technologies Corporation
    Inventor: Matthew Budnick
  • Patent number: 9828858
    Abstract: A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: November 28, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Eric Munoz, Edwin Lee Kite, John Pula, Charles M. Evans
  • Patent number: 9828866
    Abstract: A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: David Orus Fitts, David Robert Schumacher, Laurence Scott Duclos, Anand Aravindrao Kulkarni, David Bruce Knorr
  • Patent number: 9829008
    Abstract: A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.
    Type: Grant
    Filed: June 18, 2013
    Date of Patent: November 28, 2017
    Assignee: Nuovo Pignone Srl
    Inventors: Manuele Bigi, Massimo Camatti, Bhaskara Kosamana, Rajesh Mavuri, Massimiliano Borghetti, Rajesh Mamidi
  • Patent number: 9822800
    Abstract: The present disclosure relates to a support frame for a ventilation device for cooling a fluid which passes through a cooling circuit of a motor vehicle. The support frame comprises an opening, which is designed to receive a propeller, and a central support, which is positioned in a center of the opening. The central support is formed to receive a motor which activates the propeller, so as to generate a ventilation flow. The central support is attached through the opening to the support frame by retention arms. The retention arms extend according to a curved form, between the central support and a periphery of the opening.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: November 21, 2017
    Assignee: VALEO SYSTEMS THERMIQUES
    Inventors: Herve Pegues, Vincent Zuba
  • Patent number: 9822653
    Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: November 21, 2017
    Assignee: General Electric Company
    Inventors: Christopher Donald Porter, Christopher Lee Golden