Patents Examined by Dwayne J. White
  • 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: 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: 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
  • 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: 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: 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: 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
  • 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
  • Patent number: 9739174
    Abstract: A panel connection assembly connects a panel to a casing including hanger, first locating, and second locating plates. The hanger plate has elongate body, first end, and opposite second end portions, with each of the first and second end portions having a circular profile. The hanger plate has a dumbbell shape. The first locating plate has a first circular locating aperture, the first locating aperture to accommodate the first end portion, and the second locating plate has a second circular locating aperture, the second locating aperture to accommodate the second end portion. In use, the first locating plate is secured to the casing, the second locating plate is secured to the panel, the first and second end portions are respectively accommodated within the first and second locating apertures with the elongate body portions extending therefrom, to connect the panel to the casing.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: August 22, 2017
    Assignee: ROLLS-ROYCE plc
    Inventor: Paul Robert Hayton
  • Patent number: 9732619
    Abstract: A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: August 15, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Dwayne K. Mecklenburg, Zachary Mott, David R. Griffin
  • Patent number: 9732727
    Abstract: A wind turbine system to provide electrical power in areas not connected to the electrical power grid. The wind turbine system includes a frame and a rotatable shaft supported by the frame. A ring and idler gear assembly is coupled to the rotatable shaft. An upper rotor assembly is coupled to the rotatable shaft. The upper rotor assembly is configured to rotate in a first direction and thereby to rotate the rotatable shaft in a first direction. A lower rotor assembly is coupled to the ring and idler gear assembly. The lower rotor assembly is configured to rotate in a second direction which is opposite of the first direction and thereby to rotate the rotatable shaft in the first direction via the ring and idler gear assembly.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: August 15, 2017
    Inventor: Robert R. West
  • Patent number: 9726038
    Abstract: The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material. The invention also relates to an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine, and to an aero engine having a housing (10), in which at least one insulation element (12) is arranged radially above at least one guide vane (14).
    Type: Grant
    Filed: July 11, 2014
    Date of Patent: August 8, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Erwin Bayer, Thomas Hess, Sven-Juergen Hiller, Peter Geiger
  • Patent number: 9726147
    Abstract: A method for stopping the operation of a wind turbine is disclosed. The method may generally include receiving signals associated with at least one operating condition of the wind turbine, analyzing the at least one operating condition with a controller of the wind turbine, implementing a first stopping procedure in order to stop operation of the wind turbine when analysis of the at least one operating condition indicates that a pitch system failure has occurred and implementing a second stopping procedure in order to stop operation of the wind turbine when analysis of the at least one operating condition indicates that a different wind turbine stop event has occurred.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: August 8, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Xiongzhe Huang, Danian Zheng
  • Patent number: 9726029
    Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.
    Type: Grant
    Filed: July 18, 2013
    Date of Patent: August 8, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Lubomir A. Ribarov, James S. Elder, Leo J. Veilleux, Jr.
  • Patent number: 9726185
    Abstract: A centrifugal compressor for compressing a fluid comprises a compressor wheel having a plurality of circumferentially spaced blades, and a compressor housing in which the compressor wheel is mounted. The compressor housing includes an inlet duct through which the fluid enters in an axial direction and is led by the inlet duct into the compressor wheel, and a wheel shroud located radially adjacent the tips of the blades. The wheel shroud has a port for bleeding off a portion of air flowing through the compressor. The bleed air enters an annular space, flows forward, and is injected back into the inlet flow through a plurality of circumferentially spaced slots defined through the wheel shroud. The slots are open at a leading edge of the wheel shroud.
    Type: Grant
    Filed: May 14, 2013
    Date of Patent: August 8, 2017
    Assignee: Honeywell International Inc.
    Inventors: Hua Chen, Vai Man Lei, Mike Gu, Catherine Yao, Jeff Duan
  • Patent number: 9725156
    Abstract: A fairing for a rotor, the fairing comprising a movable top half-shell, the fairing including a mover device provided with a slideway, the slideway being provided with a stationary portion secured to the head of the rotor, the slideway being provided with a movable portion secured to the top half-shell, the movable portion sliding in elevation along the stationary portion along an axis in elevation, the mover device including a driver device co-operating with the movable portion to move the movable portion in translation relative to the stationary portion from a closed extreme position to an open extreme position, and vice versa.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: August 8, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventor: Robin Moret
  • Patent number: 9726179
    Abstract: Wastewater pump comprising a reversible motor (110) driving a rotor (160) equipped with blades (170). The rotor (160) is a disc (165) bearing pivoting blades (170) each mounted on a radial spindle (167) borne by the rotor. Each blade (170) is composed of a plate (171) bearing an articulation node (175) engaged on the spindle and a cutter (172) on the back of the plate forming a prop supporting the plate in the active position when the rotor (160) is rotating in the forward direction (D), and the cutter (172) projecting in the peripheral direction when the rotor (160) turns in the reverse direction (R), the plate (171) being applied against the disc (165). A fixed ring surrounds the disc and bears at least one cutter (135).
    Type: Grant
    Filed: July 17, 2014
    Date of Patent: August 8, 2017
    Assignee: Societe D'Implantation Et De Diffusion D'Equipements Electro-Hydrauliques (S.I.D.E)
    Inventor: Stephané Dumonceaux