Patents Examined by Dwayne J. White
  • 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
    Inventors: Hiroyuki Miyata, Shinichiro Tokuyama
  • Patent number: 10138738
    Abstract: A composite vane body formed of a composite material of a thermosetting resin or a thermoplastic resin, and reinforced fibers, and a metal sheath that is bonded to a leading edge section of the composite vane body via a soft adhesive to cover the leading edge section are included, and an adhesive filling section in which the soft adhesive is filled, a plurality of leading edge side contact sections that come into contact with a curved section corresponding to a leading edge of the metal sheath, and a plurality of protrusions that come into contact with a planar section corresponding to a vane surface of the metal sheath, with at least a same height as a thickness of a layer of a requisite amount of the soft adhesive filled in the adhesive filling section are formed in the leading edge section of the composite vane body. Attachment of the metal sheath to the leading edge section can be performed easily with high precision.
    Type: Grant
    Filed: February 17, 2016
    Date of Patent: November 27, 2018
    Assignee: IHI Corporation
    Inventors: Kenro Obuchi, Hiroyuki Yagi
  • Patent number: 10132323
    Abstract: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: November 20, 2018
    Inventors: Swati Saxena, Andrew Breeze-Stringfellow, Rajkeshar Vijayraj Singh, Tsuguji Nakano
  • Patent number: 10132172
    Abstract: It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.
    Type: Grant
    Filed: December 9, 2015
    Date of Patent: November 20, 2018
    Inventors: Carl Berger, Marco Lamminger, Christoph Didion, Cyrille Bricaud, Philippe Thomas Lott, Igor Tsypkaykin
  • 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: 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
    Inventors: Gary D. Roberge, Andrew P. Berryann, Scott A. Carr
  • 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
    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: 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: 10119476
    Abstract: A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter.
    Type: Grant
    Filed: September 16, 2011
    Date of Patent: November 6, 2018
    Assignee: United Technologies Corporation
    Inventor: Joseph T. Caprario
  • 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
    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
    Inventors: Jörg Kleber, Andreas Wilhelm
  • Patent number: 10106955
    Abstract: A turning control apparatus includes a turning body and a hydraulic motor to turn the turning body. A high-pressure relief circuit relieves hydraulic pressure of a first hydraulic line at a first relief pressure, the first hydraulic line supplying an operating oil to drive the hydraulic motor. A hunting reduction circuit relieves a hydraulic pressure of a second hydraulic line at a pressure lower than the first relief pressure, the second hydraulic line being connected to a deceleration-side hydraulic port from which the operating oil is discharged when the hydraulic motor is being driven. The hunting reduction circuit connected to the deceleration-side hydraulic port is caused to open before an operation lever to operate turning of the turning body returns to a neutral position.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: October 23, 2018
    Inventors: Ryuji Shiratani, Hideto Magaki, Minoru Okuyama, Masaaki Yamamoto
  • Patent number: 10100744
    Abstract: Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.
    Type: Grant
    Filed: June 19, 2015
    Date of Patent: October 16, 2018
    Assignee: The Boeing Company
    Inventors: Steve G. Mackin, David W. Foutch, Eric G. Landre
  • 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
    Inventors: Liang-Hua Xu, Te-Chung Wang
  • 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: 10082080
    Abstract: A forward fan rotor is disclosed with a hub of axis of rotation (X) and a cone mounted on the hub of the fan. The cone comprises an air bleed orifice which opens into an air duct of which a forward end portion passes through the fan rotor, said forward end portion comprising mechanical air entrainment means. The air bleed orifice has an annular shape and in that the cone is divided by said orifice into a front vertex portion and a rear frustoconical portion. A turbomachine forward axial spool equipped with such a fan rotor is also disclosed.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: September 25, 2018
    Inventors: Christian Vessot, Matthieu Leyko
  • Patent number: 10082152
    Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: September 25, 2018
    Inventors: Jiping Zhang, Barton M. Pepperman