Patents Examined by Christopher Verdier
  • Patent number: 10352242
    Abstract: A jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, the two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R2 is centered on the axis of a nozzle, the center-to-center distance of the nozzles being substantially equal to ?/2 times R2 or (?/2)R2.
    Type: Grant
    Filed: June 13, 2014
    Date of Patent: July 16, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sarah Chartier, Jean-Christophe Duffet
  • Patent number: 10352297
    Abstract: A wind power installation with a rotor which has two or more rotor blades and which is rotatably bearing-supported for rotation around a rotor rotation axis. The rotor is connected to a generator for generating electrical power. The rotor and the generator form a part of a turbine which is received by a turbine carrier. The turbine carrier is rotatably arranged at a supporting structure. The turbine is movably mounted in the turbine carrier via a bearing device so that the spatial position of the turbine in the turbine carrier can be modified. A pivoting range of the turbine corresponding to a pivoting range of the rotor rotation axis includes a first angle range and a second angle range relative to a reference plane, and the entire pivoting range is at least 120°.
    Type: Grant
    Filed: November 3, 2016
    Date of Patent: July 16, 2019
    Assignee: SKYWIND GMBH
    Inventors: Frank Richert, Sebastian Pflaum
  • Patent number: 10337517
    Abstract: An improved vacuum pump mechanism is described in which an intersecting solid or perforated element is arranged to intersect a channel member. Relative movement of the intersecting solid or perforated element and channel member causes gas molecules to be urged from inlet to an outlet of the pump. Gas molecules are constrained within the channel member and interaction of the gas molecules with the flat and smooth surfaces of the intersecting solid or perforated member influence momentum of the gas molecules so that they are directed towards the outlet. In one embodiment, the channel member is formed as a helix and the intersecting solid or perforated elements are disk-shaped. An alternative embodiment is provided having the channel member configured as a spiral and the perforated elements as cylindrical skirts. The pump provides significant improvements in pump capacity, reduced power consumption and size of pump.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: July 2, 2019
    Assignee: Edwards Limited
    Inventors: Nigel Paul Schofield, Ian David Stones, Stephen Dowdeswell
  • Patent number: 10337490
    Abstract: The present disclosure is directed to a pre-formed, continuous structural component for use in assembling a modular rotor blade for a wind turbine. Further, the structural component provides support to the modular rotor blade during operation. The pre-formed structural component includes a root portion and a body portion. The root portion is configured for mounting the structural component to a blade root section of the rotor blade. The body portion is configured to extend in a generally span-wise direction. Further, the body portion defines a predetermined cross-section having a flatback portion with a first end and a second end. In addition, the first and second ends each have a flange extending perpendicularly therefrom. Thus, each flange defines a mounting surface for one or more blade segments.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: July 2, 2019
    Assignee: General Electric Company
    Inventors: Christopher Daniel Caruso, Aaron A. Yarbrough, Daniel Alan Hynum
  • Patent number: 10316697
    Abstract: A steam turbine exhaust chamber cooling device includes a plurality of spray nozzles, and the plurality of spray nozzles inject spray water from an injection port to the turbine exhaust chamber. Here, a center line of the injection port is inclined with respect to a radial direction of a turbine rotor so that the plurality of spray nozzles inject the spray water in a direction counter to a rotation direction of the turbine rotor. An inclination angle ? at which the center line of the injection port is inclined to a forward side of the rotation direction with respect to the radial direction of the turbine rotor is in a relationship represented by the following formula (A), 25°???45°??(A).
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: June 11, 2019
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Xiaolan Wang, Yasuteru Kawai
  • Patent number: 10301008
    Abstract: A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.
    Type: Grant
    Filed: May 8, 2017
    Date of Patent: May 28, 2019
    Assignee: Kitty Hawk Corporation
    Inventor: Todd Reichert
  • Patent number: 10301965
    Abstract: A steam turbine in an embodiment includes a casing, a turbine rotor, a rotor blade cascade, a stationary blade cascade, and a spray unit, the rotor blade cascade and the stationary blade cascade being each arranged at a plurality of stages alternately in an axial direction of the turbine rotor. The turbine rotor is housed inside the casing. In the rotor blade cascade, a plurality of rotor blades are arranged in a circumferential direction of the turbine rotor. In the stationary blade cascade, a plurality of stationary blades are arranged in the circumferential direction of the turbine rotor between a diaphragm inner ring and a diaphragm outer ring. The spray unit sprays spray water to a space located upstream from a rotor blade cascade at a final stage among the rotor blade cascades at the plurality of stages inside the casing.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: May 28, 2019
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Naoki Shibukawa, Yoshifumi Iwasaki, Junichi Tominaga, Shinichiro Ohashi
  • Patent number: 10294819
    Abstract: An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: May 21, 2019
    Assignee: United Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott, Darrell Weidner, Chris Bates
  • Patent number: 10294958
    Abstract: The present disclosure relates generally to a cover for a fan blade. The cover encloses a hollowed portion formed in the fan blade and includes at least one extending portion that wraps around at least one of a trailing edge, a leading edge, and a root of the fan blade.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: May 21, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Kwan Hui, Michael A. Weisse
  • Patent number: 10294800
    Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: May 21, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Emanuele Facchinetti, Guillaume Wagner, Marc Henze
  • Patent number: 10287891
    Abstract: A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher S. McKaveney, Jason Elliott
  • Patent number: 10287903
    Abstract: Various embodiments include a steam turbine drum nozzle, along with a related assembly and steam turbine. Particular embodiments include a nozzle having: an airfoil; a radially inner sidewall coupled with a first end of the airfoil; and a radially outer sidewall coupled with a second end of the airfoil, the second end opposing the first end, wherein the radially outer sidewall includes: a first section radially outward of the airfoil; a thinned section coupled with the first section; and a second section coupled with the thinned section radially outward of the airfoil, the second section having a radially outer face and a circumferentially facing side abutting the radially outer face, wherein the second section includes a circumferentially extending slot, and wherein the second section includes a relief slot extending into a body of the second section from the circumferentially facing side.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Mark Richard Delorenzo
  • Patent number: 10280773
    Abstract: Various aspects include an alignment key for a turbomachine, along with a turbomachine including the alignment key and a related storage medium. In some cases, the alignment key includes: a body having primary axis and sized to engage a diaphragm slot in the turbomachine, the body having sidewalls extending along the primary axis; a chamfered tip section continuous with the body, the chamfered tip section sized to engage a casing slot in the turbomachine; and a slot extending through the body and the chamfered tip section, the slot having a first opening proximate an end of the body and a second opening proximate the chamfered tip section, wherein the sidewalls of the body taper from the end of the body toward the chamfered tip section.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: May 7, 2019
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Jesus Mendoza, Salvador Lopez Mata
  • Patent number: 10273903
    Abstract: A nacelle for a gas turbine jet engine for an aircraft includes plasma actuators that act as flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse or perpendicular to direction of travel of the engine.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: April 30, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Roy D. Fulayter, Crawford F. Smith, III
  • Patent number: 10267152
    Abstract: The present application relates generally to a piloted nut. The piloted nut may be used on a tie-shaft to apply an axial load to a rotor. A piloting feature on an exterior surface of the nut provides radial piloting to the rotor. The piloted nut may be used in a gas turbine engine to apply an axial load to a rotor.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: April 23, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David J. Wasserman, Ronald R. Gagnon, Jr., Christopher M. Juh, Larry A. Witherup, David B. Hudson
  • Patent number: 10267161
    Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: April 23, 2019
    Assignee: General Electric Company
    Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
  • Patent number: 10267180
    Abstract: A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: April 23, 2019
    Assignee: United Technologies Corporation
    Inventors: Frederick M Schwarz, Simon Pickford
  • Patent number: 10266247
    Abstract: A device for protecting an airfoil element made of a complex comprising a polymer film, a metal strip deposited on a part of the polymer film and an adhesive element to attach the polymer film on the airfoil element. The polymer film forms a protection against sand abrasion. The metal strip forms a protection against water abrasion of the airfoil element on which the complex is attached.
    Type: Grant
    Filed: February 28, 2015
    Date of Patent: April 23, 2019
    Assignees: Airbus SAS, Airbus Helicopters
    Inventors: Daniel Aliaga, Marie-Paule Guillou, Elisa Campazzi, Thomas Navarre
  • Patent number: 10253651
    Abstract: An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plurality of cooling holes than the flow control device in the second position. The plurality of cooling holes are upstream the flow control device relative a direction of flow through the turbomachine.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: April 9, 2019
    Assignee: United Technologies Corporation
    Inventor: Joseph T. Christians
  • Patent number: 10247040
    Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: April 2, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens