Patents Examined by Dwayne J. White
  • Patent number: 9879544
    Abstract: A turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.
    Type: Grant
    Filed: October 16, 2013
    Date of Patent: January 30, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David Waldman, Mark C. Morris, Malak Fouad Malak
  • Patent number: 9879566
    Abstract: A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: January 30, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mark C. Morris, David R. Waldman, Donald G. Godfrey, Brian G. Baughman, Mark McNair, Justin C. Mickelsen
  • Patent number: 9879549
    Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
    Type: Grant
    Filed: May 3, 2012
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventor: Laurent Gilles Dezouche
  • Patent number: 9879557
    Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Theodore W Hall, Michael G McCaffrey, Zachary Mott
  • Patent number: 9879556
    Abstract: An air seal for a gas turbine engine platform comprises a flow path platform, a seal retention ring, a finger seal. The seal retention ring is situated radially adjacent the flow path platform. The finger seal is retained by the seal retention ring between the flow path platform and the seal retention ring. The finger seal comprises a first ply with first keyhole slots, a second ply with second keyhole slots circumferentially offset relative to the first keyhole slots, and a foil layer. The foil layer is disposed between the first and second plies. The finger seal has a series of cooling holes in the outer circumferential segment to cool the outer diameter of the seal. In addition, leakage between the finger seal and the flow path platform cools the inner diameter of the seal.
    Type: Grant
    Filed: April 6, 2015
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Conway Chuong, Jeffrey J. Lienau, William Yeager
  • Patent number: 9879543
    Abstract: A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem.
    Type: Grant
    Filed: July 14, 2009
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: James W. Norris, James D. Hill
  • Patent number: 9882368
    Abstract: An electric arc detection system is presented. The electric arc detection system comprises a receiving antenna that receives electromagnetic radiation generated by an electric arc formed in an internal cavity of a non-conductive hollow structure, and a processing subsystem for determining an existence of the electric arc in the internal cavity based upon signals representative of the electromagnetic radiation.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: January 30, 2018
    Assignee: General Electric Company
    Inventor: Yaru Najem Mendez Hernandez
  • Patent number: 9869317
    Abstract: The present invention relates to a multi-stage vacuum pump having a plurality of compression stages 12, 14, 16, 18 20 and a booster stage 22. The pump 10 is arranged to pump a chamber 24. The pumping stages include respective rotors supported for rotation on one or more common drive shafts 26. A recirculation valve 28 is associated with the booster stage 22 for selective recirculation of pumped fluid from an outlet 32 to an inlet 30 of the booster stage above a predetermined pressure.
    Type: Grant
    Filed: February 7, 2013
    Date of Patent: January 16, 2018
    Assignee: Edwards Limited
    Inventor: Nigel Schofield
  • Patent number: 9869198
    Abstract: An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut.
    Type: Grant
    Filed: May 13, 2015
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventor: Mark Gregory Wotzak
  • Patent number: 9863440
    Abstract: Submersible pump which comprises: a first motor provided with a first outlet shaft; a pumping body in which an impeller is housed that is fixed to the first outlet shaft of the first motor and drivable by the latter in order to pump a process fluid from a suction mouth to a delivery mouth of the pumping body itself; a support casing fixed to the pumping body and provided, at a lower end thereof, with an inlet opening through which a flow of the process fluid is susceptible to enter into the support casing itself; a dispersion head arranged at the lower end of the support casing and drivable in order to remove detrital material, which is conveyed by the flow of the process fluid into the inlet opening of the support casing.
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: January 9, 2018
    Assignee: DRAGFLOW S.R.L.
    Inventors: Stefano Pol, Mariano Gardoni, Mario Sauro
  • Patent number: 9863252
    Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Damien Merlot, Etienne Ide, Philippe GĂ©rard Edmond Joly
  • Patent number: 9863272
    Abstract: A turbomachine of this disclosure includes a rotation shaft, a first impeller, a first bearing, and a second bearing. The first impeller is fixed to the rotation shaft and includes a low-pressure-side surface. The first bearing is adjacent to the low-pressure-side surface of the first impeller and supports the rotation shaft. The second bearing is disposed on an opposite side of the first impeller from the first bearing and supports the rotation shaft. The rotation shaft includes a first tapered portion gradually increasing in diameter toward the first impeller. The first bearing includes a first support surface supporting the first tapered portion.
    Type: Grant
    Filed: April 6, 2015
    Date of Patent: January 9, 2018
    Assignee: PANASONIC INTELLECTUAL PROPERTY MANAGEMENT CO., LTD.
    Inventor: Tadayoshi Shoyama
  • Patent number: 9863258
    Abstract: A method of forming a structural connection between a spar cap 14 and an aerodynamic fairing 12. A composite comprising an uncured matrix and a compressible solid is applied between the spar cap and fairing and is then compressed and cured to adhere the fairing to the spar cap. The cured matrix composite has a void volume of at least 20%. The high void volume means that as the fairing is compressed into place and compresses the composite, it has space in which to deform so as not to place undue stress on the fairing and to produce a lightweight connection.
    Type: Grant
    Filed: March 24, 2015
    Date of Patent: January 9, 2018
    Assignee: Blade Dynamics Limited
    Inventors: Paul Hayden, Harald Behmer
  • Patent number: 9863423
    Abstract: A conical impeller with a hub that has a conical surface extending into the interior of the impeller. The hub has spiral, slanting arms which are attached or integrally formed with a plurality of curved blades. The blades can be connected at the bottom by a ring. The intersection of the conical surface of the hub with the blade forms an upward path for fluids and their entrained particles or gases which have been brought into the interior of the impeller to effectively completely be ejected. The discharge edges of the blades and/or the conical surface of the hub may have openings for discharging gas into the fluid. The impeller imparts low shear to the fluid and its components, and the shear is independent or only depends slightly on the size of the impeller. The impeller minimizes or eliminates particle agglomeration and fouling of the impeller. The efficiency of and flow pattern produced by the impeller means that containers don't require the use of baffles.
    Type: Grant
    Filed: April 14, 2015
    Date of Patent: January 9, 2018
    Assignee: Enevor Inc.
    Inventor: Carl Roy Bachellier
  • Patent number: 9863278
    Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Patrick Sultana, Boucif Bensalah, Yannick Durand, Olivier Renon
  • Patent number: 9856034
    Abstract: An aircraft nacelle comprising a first and a second cowl mounted pivotably about an axis substantially parallel to a longitudinal axis of the nacelle and lockable to one another by at least one locking mechanism. The nacelle further comprises a device for providing a visual warning of a locking defect of the cowls. The device comprises a movable bolt associated with the locking mechanism and a movable edge plate mounted on the nacelle in line with said bolt with which it is associated, the movable edge plate being movable under the action of an operator between a protruding position, in which the edge plate is protruding from the nacelle and a locking mechanism is in an unlocked position, and a retracted position, in which the edge plate is immobilized within the nacelle by the bolt and the action of the locking of a locking mechanism.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: January 2, 2018
    Assignee: Airbus Operations (SAS)
    Inventor: Jacques Herve Marche
  • Patent number: 9856736
    Abstract: A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier.
    Type: Grant
    Filed: October 17, 2013
    Date of Patent: January 2, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Frank Stiehler
  • Patent number: 9856739
    Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
    Type: Grant
    Filed: September 18, 2013
    Date of Patent: January 2, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Loris Bedrosyan, Ardeshir Riahi, Daniel C. Crites
  • Patent number: 9856852
    Abstract: The present invention relates to a floating wind energy harvesting apparatus for offshore installation, comprising an elongated wind turbine body extending along a longitudinal wind turbine body axis, said wind turbine body comprising a lower body portion and an upper body portion; wind turbine blades attached to the upper body portion; at least a first cavity inside said wind turbine body and arranged within a first radial distance from said longitudinal wind turbine body axis; at least a second cavity arranged within a second radial distance, greater than said first radial distance, from said longitudinal wind turbine body axis; at least a first pump for pumping water from said first cavity to said second cavity; and an energy converter attached to said wind turbine body for converting the rotation of said wind turbine body to electrical energy.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: January 2, 2018
    Assignee: SEA TWIRL AB
    Inventor: Daniel Ehrnberg
  • Patent number: 9850772
    Abstract: Seal assemblies for reducing leakage between components of turbomachinery include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, end blocks and ceramic fiber are coupled. The end blocks account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks protect the metallic shim from reaching harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: December 26, 2017
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Edip Sevincer, Anthony Marin