Patents Examined by Adam W Brown
  • Patent number: 10145383
    Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as ? ? = ? i - ? ? i - ? e where ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: December 4, 2018
    Assignee: Rolls-Royce Corporation
    Inventor: Bronwyn Power
  • Patent number: 10145378
    Abstract: A rotary machine characterized by being equipped with: a rotary drive part; a drive shaft that is rotated about a horizontally extending axis by the rotary drive part; a large gear that is fixed to the drive shaft; a bearing part that rotatably supports the drive shaft, and to which a lubrication oil is supplied; multiple pinions that are driven by being engaged with the large gear; multiple compression parts that are arranged so as to correspond to the multiple pinions and are respectively rotated by the pinions; and a plate that is installed between the bearing part and the large gear and covers at least a portion of the bottom half of the large gear so as to separate the large gear and the bearing part from each other.
    Type: Grant
    Filed: September 6, 2013
    Date of Patent: December 4, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Hiroyuki Miyata, Shinichiro Tokuyama
  • Patent number: 10132178
    Abstract: To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: November 20, 2018
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Koji Ishibashi, Susumu Nakano, Takeshi Kudo
  • Patent number: 10125744
    Abstract: The invention provides a lightning protection system for a wind turbine blade (10), whose structure comprises two structural shells (11, 13) with two caps (19, 21) formed by carbon fiber laminates and two spars (15, 17). In addition to a first subsystem formed by one or more lightning receptors connected to one or two conductor cables the lightning protection system comprises a second subsystem formed by lateral lightning receptors (30, 31) arranged at the leading and trailing edges of the wind turbine blade (10) in at least two cross sections (22, 23) of it connected with the caps (19, 21) and connecting means between the two subsystems for equipotentializing the lightning protection system.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: November 13, 2018
    Assignee: GAMESA INNOVATION & TECHNOLOGY, S. L.
    Inventors: Victor March Nomen, Francisco Javier Bandres Gomez, Javier Iriarte Eleta
  • Patent number: 10125788
    Abstract: Fan blade containment system includes circular tile layer of annular ceramic tiles attached to and extending radially inwardly from a shell, radially inner and outer annular surfaces of ceramic tiles bonded to a radially inner composite layer and the shell respectively with elastomeric inner and outer adhesive layers respectively. Elastomeric adhesive layers between circumferentially adjacent overlapped or scarfed edges along circumferential edges of the ceramic tiles overlap and mate along oppositely facing surfaces of adjacent ones of the ceramic tiles. Inner and outer adhesive layers and elastomeric adhesive layer may be a double-sided adhesive foam tape. Scarfed edges may be bevels or rabbets. Shell may be made of a metal or composite material. Fan blade containment system may be bonded to and extend inwardly from fan case circumscribing fan blades of a fan. Inner composite layer and composite outer shell may be co-cured with ceramic tiles therebetween.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: November 13, 2018
    Assignee: General Electric Company
    Inventors: Wendy Wen-Ling Lin, David Sujay Kingsley, Benjamin James Roby
  • Patent number: 10125724
    Abstract: A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gary D. Roberge, Andrew P. Berryann, Scott A. Carr
  • Patent number: 10119417
    Abstract: A turbocharger (300) having a rotatable shaft (312) passing through a bearing housing (303) with a turbine-end bearing support (580) with a support bar (600). A turbine-end bearing support (580) may include the support bar (600) with radial supports (610) and (620) connected to each opposite side (492) and (494) of cavity (496) of the bearing housing (303) wherein oil can flow in recesses (640) and (650) above the radial supports (610) and (620). Each radial support (610) and (620) of the support bar (600) is preferably integrated in the corresponding side (492) and (494). A turbine-end bearing support (580) may also include the support bar (600) with a rod portion (622) forming a bottom tie support bar (612) that supports the bottoms of both bearing supports (490) and (580), which are top-supported by the bearing housing (303). Each support bar (600) is preferably integral with the bearing support (580).
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: November 6, 2018
    Assignee: BorgWarner Inc.
    Inventor: Michael Bucking
  • Patent number: 10113439
    Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 30, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 10107194
    Abstract: A gas turbine stage, in particular to an aircraft gas turbine. This gas turbine includes at least one casing having at least one bleed duct and at least one bore, and further includes at least one variable guide vane having a trunnion, a rotary plate, and a guide vane airfoil. The trunnion is disposed in the bore, and the guide vane airfoil is integrally formed with the rotary plate. The guide vane airfoil integrally formed with the rotary plate extends beyond this rotary plate in such a way that, viewed in the direction of flow of the gas path of the gas turbine, a flag corner of the guide vane airfoil, which corner faces the bleed duct and/or is in particular a virtual one, is located downstream of the beginning of the inlet opening of the bleed duct.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: October 23, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Lahmer, Harsimar Sahota
  • Patent number: 10107266
    Abstract: A device removes moisture from a hydraulic medium (2) with at least one gaseous drying medium (3). The drying medium (3) is air and/or some other working gas with a moisture absorption capability. The drying medium is conducted by a delivery device (4) from an area surrounding the hydraulic medium (2) to the hydraulic medium (2) when the moisture content of the gaseous drying medium (3) is lower than the degree of water saturation of the hydraulic medium (2).
    Type: Grant
    Filed: May 14, 2011
    Date of Patent: October 23, 2018
    Assignee: HYDAC FILTER SYSTEMS GMBH
    Inventors: Jörg Kleber, Andreas Wilhelm
  • Patent number: 10107127
    Abstract: A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James Hill, Brian Merry, Gabriel Suciu
  • Patent number: 10100840
    Abstract: The present invention relates to a fan wheel structure comprising a cover body connected with a plurality of fan blades, a hub, and a plurality of fan blades. The cover body is disposed on a hub. The hub has a top surface and a receiving space defined on the top surface. Each of the fan blades has a joining end protruding into the receiving space. The cover body has a clamping side combined with the top surface of the hub and a plurality of joining grooves spaced around the cover body and individually combined with the corresponding joining ends of the fan blades to fix the fan blades.
    Type: Grant
    Filed: March 8, 2016
    Date of Patent: October 16, 2018
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventors: Liang-Hua Xu, Te-Chung Wang
  • Patent number: 10094239
    Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: October 9, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
  • Patent number: 10094226
    Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: October 9, 2018
    Assignee: General Electric Company
    Inventors: Aaron Ezekiel Smith, Metodi Blagoev Zlatinov, Thomas Earl Dyson
  • Patent number: 10072525
    Abstract: A gas turbine engine comprising a casing, a bonding patch (10, 22) bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch (10, 22) comprising a bonding region (12) configured to receive an adhesive for bonding the patch (10, 22) to a surface. A plurality of de-bonding elements (16) is configured to be movable relative to the bonding region (12) in response to an energizing signal.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: September 11, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Christopher Benson
  • Patent number: 10065243
    Abstract: A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy.
    Type: Grant
    Filed: October 1, 2012
    Date of Patent: September 4, 2018
    Assignee: United Technologies Corporation
    Inventor: Christopher W. Strock
  • Patent number: 10060281
    Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher W Strock, Changsheng Guo, Yan Chen
  • Patent number: 10054106
    Abstract: A counterweight system for a wind turbine is provided. The wind turbine comprises a rotor hub positioned on a wind turbine tower such that the rotor hub is configured to rotate around an axis, the rotor hub comprising one or more mounting surfaces, the counterweight system comprising: The system comprises a beam comprising a connection element adapted to be attached to the mounting surfaces, the beam being provided with a first steering mechanism adapted to control an orientation of the beam with respect to the connection element. Furthermore, the system comprises a counterweight mass coupled to the beam. Moreover, methods for installing blades to a rotor hub of a wind turbine are also provided.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: August 21, 2018
    Assignee: GE Renewable Technologies Wind B.V.
    Inventors: Isaac Gil Mollà, Elsa Rondeleux
  • Patent number: 10054131
    Abstract: A fan assembly comprises a hub and fan blades. The hub includes a plurality of sockets configured to receive complementary mounting blocks of the fan blades. The mounting blocks each include at least one tapered shoulder portion. The mounting blocks are each tapered along three dimensions. Each mounting block comprises a rear face seated against a complementary rear face of the corresponding socket and a front face that is exposed relative to the hub. A cap secures the fan blades to the hub. The fan assembly may also include one or more shrouds positioned about the fan blades. The one or more shrouds may be substantially straight cylinders, may be flared or bell-shaped, may comprise a cage, may have any other suitable configuration, or may be omitted altogether.
    Type: Grant
    Filed: March 24, 2010
    Date of Patent: August 21, 2018
    Assignee: DELTA T, LLC
    Inventors: Richard M. Aynsley, Richard A. Oleson
  • Patent number: 10054052
    Abstract: A gas turbine engine is provided having a nacelle and a compressor section constructed and arranged to generate hot air. An anti-icing system is constructed and arranged to discharge the hot air from the compressor section to the nacelle. An anti-icing valve is positioned in the anti-icing system and constructed and arranged to control a flow of the hot air from the compressor section to the nacelle. The anti-icing valve includes a partially open position to constrict a flow of the hot air from the compressor section to the nacelle.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: August 21, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Zhijun Zheng, Michael D. Greenberg