Patents Examined by Dwayne J. White
  • Patent number: 9759088
    Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.
    Type: Grant
    Filed: May 15, 2012
    Date of Patent: September 12, 2017
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jacques René Bart
  • Patent number: 9759079
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Grant
    Filed: May 28, 2015
    Date of Patent: September 12, 2017
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
  • Patent number: 9759183
    Abstract: A system and method for mounting a component to an internal web of a wind turbine blade includes, at a first mounting location on the internal web, at least one through-hole defined through the internal web. A bushing is located within the through-hole and is encased within an adhesive applied between the bushing and a wall of the through-hole. A plate is attached to each of the opposite panels of the internal web at the mounting location against an end face of the bushing, with each plate having a hole therein that is aligned with the through-hole. For mounting the component at the mounting location, a bolt is passed completely through the plates and bushing for attachment of a frame of the component to one of the plates.
    Type: Grant
    Filed: January 5, 2015
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventors: Afroz Akhtar, Saravakota Sambamurty, Bruce Clark Busbey, Wilfred A.A.W., Bart Jan Veldkamp
  • Patent number: 9759094
    Abstract: A pump for a gas turbine engine is provided. The pump includes a first drive track having a spline and a first gear each rigidly attached to a first driveshaft. The pump also includes a second drive track having a second gear rigidly attached to a second driveshaft. The second gear is mechanically coupled to the first gear. Additionally, a first lubrication supply pump is mechanically coupled to the first driveshaft and a second lubrication supply pump is mechanically coupled to the second driveshaft. The first and second lubrication supply pumps are together configured to provide a desired amount of lubrication to the gas turbine engine.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventor: Walter Decania Hutto, Jr.
  • Patent number: 9759187
    Abstract: A wind turbine with a wind turbine tower, a nacelle on the tower, a rotor hub rotatably mounted to the nacelle, and at least one wind turbine blade having a blade root mounted to the rotor hub, a tip end, a pressure side and a suction side connected to each other via a leading edge and a trailing edge, a first shell part having inner and outer surfaces and a second shell part having inner and outer surfaces, the shell parts having flanges that extend outwards from the trailing edge of the shell parts and away from the outer surface with gluing surfaces which are glued together when the two shell parts are placed on top of each other. This allows the glue line to be moved out of the inner area defined by the shell parts so that the glue process can be controlled more effectively.
    Type: Grant
    Filed: October 7, 2013
    Date of Patent: September 12, 2017
    Assignee: Envision Energy (Denmark) ApS
    Inventor: Wout Ruijter
  • Patent number: 9759227
    Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventors: Edward Charles Schurr, Svitlana Kalmyk
  • Patent number: 9752561
    Abstract: A method for detecting a rotor blade pitch angle adjustment fault of a rotor blade of a wind turbine is provided, the method includes measuring a rotor blade pitch angle speed; predicting, based on an actual rotor speed, a rotor blade pitch angle speed; indicating a fault, if a first criterion is satisfied, wherein the first criterion is satisfied, if deviation between the measured rotor blade pitch angle speed and the predicted rotor blade pitch angle speed exceeds a speed threshold.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: September 5, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventors: Per Egedal, Gustav Hoegh, Bjarne Skovmose Kallesoee
  • Patent number: 9752666
    Abstract: A torque converter for transferring torque from an input shaft to an output shaft, having a turbine wheel, an impeller connected to the input shaft to drive the turbine wheel hydrodynamically, a centrifugal force pendulum connected to the turbine wheel to damp torsional vibrations, a first torsion damper to drive the output shaft by means of the turbine wheel, and a converter clutch and a second torsion damper for selective torsionally damped coupling of the input shaft with the turbine wheel. One of the torsion dampers in this case includes two torsion damper elements, which are arranged in series with each other.
    Type: Grant
    Filed: October 18, 2013
    Date of Patent: September 5, 2017
    Assignee: Schaeffler Technologies AG & Co. KG
    Inventors: Benjamin Voegtle, Benjamin Daniel, Thorsten Krause
  • Patent number: 9752450
    Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly may include a blade outer air seal segment, a linkage and an actuation device. The linkage may include a shaft and a head, where the shaft is connected to the blade outer air seal segment and extends radially outward to the head. The actuation device may include a sloped slide block located radially within and engaged with the head. The actuation device may be configured to laterally translate the sloped slide block and thereby radially move the blade outer air seal segment.
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: September 5, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Duguay, Timothy M. Davis
  • Patent number: 9751603
    Abstract: Disclosed are a propulsion device for a ship and a ship having the same. The propulsion device may include a rotational shaft, a rear propeller fixed to the rotational shaft, a front propeller rotatably supported by the drive shaft in front of the rear propeller, a counter rotation unit disposed in an installation space of a stern of a ship body and including a plurality of gears configured to reverse rotation of the rotational shaft and transmit the reversed rotation to the front propeller and a gear box configured to receive the plurality of gears, a coupling unit configured to separably connect the rotational shaft with the counter rotation unit and cut off power transmission from the rotational shaft to the counter rotation unit upon disconnection therebetween, and a rotation preventing unit configured to prevent rotation of the front propeller when the coupling unit is separated.
    Type: Grant
    Filed: May 8, 2013
    Date of Patent: September 5, 2017
    Assignee: Samsung Heavy Ind. Co., Ltd.
    Inventors: Dong-Hyun Lee, Jong-Soo Seo, Tae-Goo Lee, Kwang-Jun Paik, Kwang-Kun Park, Seung-Myun Hwangbo, Ji Nam Kim, Hyuk Kwun
  • Patent number: 9751623
    Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements that define a predetermined number of torsion elements and a ring-shaped connection zone for attachment to a rotor hub associated with a rotor shaft of the multi-blade rotor, each flexbeam element passing the ring-shaped connection zone in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of the predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of the ring-shaped connection zone immediately following flexbeam element and is overlapped by at least one in the circumferential direction of the ring-shaped connection zone immediately preceding flexbeam element.
    Type: Grant
    Filed: January 12, 2015
    Date of Patent: September 5, 2017
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventor: Rupert Pfaller
  • Patent number: 9752672
    Abstract: A transmission turbo machine integrates drive units and/or driven units into a machine train via a transmission. The integrated transmission substantially comprises a central large wheel with a shaft and a plurality of pinions with pinion shafts. The large wheel is operatively connected to the pinions, and the ends of the pinion shafts are operatively connected to a drive unit and/or driven unit. The shaft of the large wheel is operatively connected to a drive unit and/or driven unit. The invention is characterized in that the drive unit and/or driven unit is an axial expander which is mounted in a cantilevering manner in one or more stages.
    Type: Grant
    Filed: September 18, 2013
    Date of Patent: September 5, 2017
    Assignee: MAN Diesel & Turbo SE
    Inventors: Emil Aschenbruck, Carsten Bennewa, Sven Boje, Bernd Risse, Philipp Gingter
  • Patent number: 9752455
    Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: September 5, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Rudolf Stanka, Christoph Lauer, Hans Stricker
  • Patent number: 9745070
    Abstract: Within examples, systems for multiple zone heaters for rotor craft are provided and methods for operation. An example system for a rotor craft comprises multiple blades coupled to a rotor and areas of the multiple blades divided into sections. A given blade includes an inboard section extending from the rotor outward and an outboard section extending from the inboard section to a tip of the given blade. The system also includes a plurality of first spanwise heater systems included on respective outboard sections of the multiple blades, a plurality of second spanwise heater systems included on respective inboard sections of the multiple blades, and a control unit coupled to the plurality of first spanwise heater systems and the plurality of second spanwise heater systems. Respective heater systems of the sections of multiple blades are energized in a sequence based on outside air temperature.
    Type: Grant
    Filed: November 11, 2014
    Date of Patent: August 29, 2017
    Assignee: The Boeing Company
    Inventors: Edward W. Brouwers, Andrew A. Peterson
  • Patent number: 9745853
    Abstract: A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.
    Type: Grant
    Filed: August 31, 2015
    Date of Patent: August 29, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Ching-Pang Lee, Nan Jiang, Jae Y. Um, Harry Holloman, Steven Koester
  • Fan
    Patent number: 9745996
    Abstract: A fan casing includes an impeller housing, a mixed-flow impeller located within the impeller housing, and a motor for driving the impeller. The impeller includes a hub connected to the motor, and a plurality of blades connected to the hub, each blade comprising a leading edge located adjacent the air inlet of the impeller housing, an inner side edge connected to and extending partially about the outer surface of the hub, an outer side edge located opposite to the inner side edge, and a blade tip located at the intersection of the leading edge and the outer side edge. The leading edge comprises an inner portion located adjacent the hub, and an outer portion located adjacent the blade tip, and wherein the inner portion is swept rearwardly from the hub to the outer portion, and the outer portion is swept forwardly from the inner portion to the blade tip.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: August 29, 2017
    Assignee: Dyson Technology Limited
    Inventor: Michal Rafal Nurzynski
  • Patent number: 9744563
    Abstract: An undulatory structure and methods for the fabrication and use thereof. The undulatory structure includes a buckled sheet and one or more work input elements for deforming the buckled sheet in an undulating manner wherein each point in a series of points on a sinuously-shaped profile of the buckled sheet travels at least partially along a figure eight-shaped path. The undulatory structure can be adapted for use as a solid-state transducer wherein the buckled sheet provides mechanical advantage without appreciable opposition from elastic restoring forces, thereby achieving improved force, displacement and efficiency characteristics.
    Type: Grant
    Filed: September 26, 2011
    Date of Patent: August 29, 2017
    Assignee: TECHTONIC PTY LTD
    Inventors: Zachariah Benjamin, Colin Robert Smith
  • Patent number: 9745858
    Abstract: A turbine seal plate includes an inner rim with a labyrinth seal land that defines a central bore having a labyrinth seal diameter. The turbine seal plate also includes a housing coupling ring arranged radially outward of the inner rim. A housing pilot extends axially from the housing coupling ring and substantially parallel to the labyrinth seal land with respect to a radially inner portion of the housing pilot. The housing pilot has a housing pilot thickness, and a ratio of the housing pilot thickness to the labyrinth seal diameter is between 0.08 and 0.14. A frusto-conical body extends between the radially inner portion of the housing pilot and the inner rim of the turbine seal plate.
    Type: Grant
    Filed: June 5, 2015
    Date of Patent: August 29, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Craig M. Beers, Eric Chrabascz
  • Patent number: 9745956
    Abstract: A rotor blade of a wind turbine having a pultruded spar cap is disclosed. The rotor blade includes a blade root and a blade tip. The blade root includes at least one root insert. The rotor blade also includes at least one spar cap constructed of a plurality of pultruded members grouped together to form one or more layers from the blade tip towards the blade root. Further, the pultruded members separate into one or more pultruded member bundles as the spar cap approaches the blade root. The pultruded member bundles fit within the root insert, along with the blade bolts, such that compression and tension loads of the rotor blade are transferred through the pultruded members.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: August 29, 2017
    Assignee: General Electric Company
    Inventors: Stephen Bertram Johnson, Christopher Daniel Caruso
  • Patent number: 9739175
    Abstract: An additional pad 27 is additionally and integrally arranged from an outer surface of a flange 17 opposite to a contacting side of the flange 17 to a small-diameter curved surface of a bend 19 and from there to an end of an outer surface of a part body 13. On an outer surface side of the additional pad 27, a fastening seat 27f is formed by machining. An area end PAe of a processed area PA formed by machining is positioned on the part body 13 beyond the bend 19.
    Type: Grant
    Filed: October 18, 2013
    Date of Patent: August 22, 2017
    Assignees: IHI Corporation, IHI AEROSPACE CO., LTD.
    Inventors: Takashi Harada, Yu Shigenari, Koichi Inagaki, Agamu Tanaka, Tadahiro Ishigure