Patents Examined by Dwayne J. White
  • Patent number: 10001064
    Abstract: The present disclosure relates to an assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection, said structure including an inner face, on which the thermal protection is added, and an outer face constituting a portion of the inner surface of a cold flow path, the assembly including at least one channel put in fluid communication the inner face and the outer face of the structure.
    Type: Grant
    Filed: April 24, 2017
    Date of Patent: June 19, 2018
    Assignee: SAFRAN NACELLES
    Inventors: François Bellet, Cédric Renault
  • Patent number: 9995146
    Abstract: A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.
    Type: Grant
    Filed: April 29, 2015
    Date of Patent: June 12, 2018
    Assignee: General Electric Company
    Inventors: Adebukola Oluwaseun Benson, Nicholas Alvin Hogberg, Gary Michael Itzel, Mitchell Allan Merrill, Xiuzhang James Zhang
  • Patent number: 9988936
    Abstract: A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator can have an inlet for accepting a flow of cooling fluid, such that a the flow of cooling fluid separates into a major flow and a minor flow carrying particles or particulate matter along the minor flow into a particle collector comprising at least a portion of the particle separator. Particles become constrained to the minor flow and pass into the particle collector, while the major flow is separated into the remaining area of the interior chamber to remove the particles from the flow of cooling fluid passing into the interior chamber.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: June 5, 2018
    Assignee: General Electric Company
    Inventors: Hojjat Nasr, Gregory Michael Laskowski, Curtis Walton Stover, William Collins Vining
  • Patent number: 9988934
    Abstract: A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.
    Type: Grant
    Filed: July 23, 2015
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brandon W. Spangler
  • Patent number: 9988913
    Abstract: A method for forming a gas turbine engine component comprises the steps of forming a block of a high temperature alloy material. An external surface of the block is machined to form an external surface of a gas turbine engine component. At least one cooling passage within the component that is open to at least one end of the component is machined. At least one insert with a heat transfer feature is formed. The insert is installed within the at least one cooling passage. A component for a gas turbine engine is also disclosed.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 5, 2018
    Assignee: United Technologies Corporation
    Inventor: Brandon W. Spangler
  • Patent number: 9982547
    Abstract: A guide mechanism for a gas turbine has a casing supporting on its interior a duct delimited by radially inner and outer duct segments. A variable guide vane located at least partially within the duct can rotate about an axis of rotation to guide flow of a fluid in the duct. The radially inner duct segment is fastened to the guide vane and is retained on the casing element via the guide vane, which is mounted on the casing element via a bushing inserted in the radial direction from outside to inside into a passage opening of the casing element.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: May 29, 2018
    Assignee: MTU AERO ENGINES AG
    Inventor: Alexander Boeck
  • Patent number: 9982654
    Abstract: Wind turbine having a wind turbine tower, a nacelle provided on the wind turbine tower, a rotor hub rotatably mounted to the nacelle, and one or more wind turbine blades having a root end to be mounted to the rotor hub, a tip end, and pressure and suction sides connected to each other via a leading edge and a trailing edge. The wind turbine blade has a plurality of cross-sectional profiles arranged according to the surface of the suction side so that the surface of the suction side forms a line having a predetermined curvature which curves towards the pressure side of the wind turbine blade and/or forms an approximately straight line along at least part of the relative length. The line crosses each cross-sectional profile in that point on the pressure side where the maximum relative thickness of that profile perpendicular relative to its chord line is measured.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: May 29, 2018
    Assignee: Envision Energy (Denmark) ApS
    Inventor: Wout Ruijter
  • Patent number: 9976420
    Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.
    Type: Grant
    Filed: July 23, 2015
    Date of Patent: May 22, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Quang Tue Nguyen Tran, Rodrigo Rodriguez Erdmenger, Christopher Jon Potokar
  • Patent number: 9976433
    Abstract: A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.
    Type: Grant
    Filed: April 2, 2010
    Date of Patent: May 22, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Praisner, Eric A. Grover
  • Patent number: 9976427
    Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: May 22, 2018
    Assignee: United Technologies Corporation
    Inventors: Joshua Daniel Winn, David A. Niezelski
  • Patent number: 9976558
    Abstract: Example implementations relate to a fan module. The fan module may include an outer impeller having a first plurality of radial blades arranged between an inner circumference of the outer impeller and an outer circumference of the outer impeller. The outer impeller may be rotatable about a first axis of rotation. The fan module may include an inner impeller having a second plurality of radial blades, the inner impeller disposed within the inner circumference of the outer impeller and rotatable about a second axis of rotation.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: May 22, 2018
    Assignee: Hewlett-Packard Development Company, L.P.
    Inventors: Chienlung Yang, Kuan-Ting Wu
  • Patent number: 9976567
    Abstract: The present invention relates to a rotor (90) applied to an extractor-fan assembly (80) for agricultural machines, especially for sugar-cane harvesters, the rotor (90) comprising a set of blades (1) fixed to a hub (2). Each of the blades (1) has such a construction that defines a root angle (3) that may range from 47 to 59 degrees, a medium angle (4) that may range from 53 to 69 degrees and a trailing angle (5) that may range from 66 to 78 degrees. Due to the construction angles of the blades (1), the air flow comes in contact with the rotor (9) smoothly, without any turbulence in its displacement, which results in high efficiency and efficacy of the extractor-fan assembly (80).
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: May 22, 2018
    Assignee: MARCHESAN IMPLEMENTOS E MAQUINAS AGRICOLAS TATU S.A.
    Inventors: Dacio Helene Junior, Valter Palmute
  • Patent number: 9970298
    Abstract: A balancing device for a rotating part of a turbomachine, includes a ferrule pierced with a plurality of ports, a balancing screw passing through each port, each balancing screw including a body and a head, the head of each balancing screw being pierced with a recess, the balancing screws being of at least one first type, the recess of the screws of the first type being formed by a driving recess from which an additional recess extends.
    Type: Grant
    Filed: January 6, 2014
    Date of Patent: May 15, 2018
    Assignee: SNECMA
    Inventors: Jean-Luc Le Strat, Hervé Pohier, Romain Jean-Louis Robert Thory
  • Patent number: 9970442
    Abstract: A molten metal pump assembly (10) and method to fill complex molds with molten metal, such as aluminum. The pump assembly includes an elongated shaft (16) connecting a motor (14) to an impeller (22). The impeller is housed within a chamber (18) of a base member such that rotation of the impeller draws molten metal into the chamber at an inlet (48) and forces molten aluminum through an outlet (50). A first bearing (36) is adapted to support the rotation of the impeller at a first radial edge (32) and a second bearing (38) is adapted to support the rotation of the impeller at a second radial edge. A bypass gap (60) is interposed between the second bearing and the second radial edge. Molten metal leaks through the bypass gap at a predetermined rate to manipulate a flow rate and a head pressure of the molten metal such that precise control of the flow rate is achieved.
    Type: Grant
    Filed: April 18, 2012
    Date of Patent: May 15, 2018
    Assignee: PYROTEK, INC.
    Inventor: Jon Tipton
  • Patent number: 9970455
    Abstract: A compressor includes a housing; an impeller rotatably installed in the housing; a guidance unit connected to the housing at a first end of the guidance unit and configured to guide a fluid discharged by the impeller, the guidance unit configured to change a flow direction; and a scrolling unit connected to a second end opposite to the first end of the guidance unit. A width of an opening via which the fluid enters a circular space of the scrolling unit is about 1.5 to about 3.5 times a height of the guidance unit.
    Type: Grant
    Filed: July 15, 2015
    Date of Patent: May 15, 2018
    Assignee: HANWHA POWER SYSTEMS CO., LTD.
    Inventors: Jongjae Cho, Yeonhwa Cho, Bonggun Shin, Kangsoo Im
  • Patent number: 9970319
    Abstract: An airfoil body includes an airfoil wall defined between an internal cavity surface and an external airfoil surface. A pad extends from the internal cavity surface. A cooling hole extends from the external airfoil surface, through the airfoil wall and through the pad for fluid communication through the airfoil wall.
    Type: Grant
    Filed: May 4, 2015
    Date of Patent: May 15, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James M. Koonankeil, Edward F. Pietraszkiewicz
  • Patent number: 9963990
    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: May 8, 2018
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites, Inc.
    Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Patent number: 9957806
    Abstract: A method for the manufacture of a double-row blade wheel for a fluid-flow machine that includes a first grid row with a plurality of first blades and a second grid row with a plurality of second blades is provided. The method includes the following steps: manufacturing a first grid row or segments of the first grid row; manufacturing a second grid row or segments of the second grid row, independently of the first row; and after the respective manufacture, connecting the first grid row to the second grid row or connecting segments of the first grid row and/or of the second grid row to one another or to one of the grid rows.
    Type: Grant
    Filed: March 9, 2015
    Date of Patent: May 1, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Erik Johann, Jens Ortmanns
  • Patent number: 9938835
    Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: April 10, 2018
    Assignee: General Electric Company
    Inventors: Andrew Paul Giametta, David Richard Johns
  • Patent number: 9938831
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: April 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, James W. Norris