Patents Examined by Ninh H. Nguyen
  • Patent number: 10927676
    Abstract: A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Ho, Jamal Zeinalov
  • Patent number: 10927819
    Abstract: A method of monitoring a blade pitch bearing of a rotor blade of a wind turbine is provided, the method including: pitching the rotor blade; measuring an amount of a vibration of the blade pitch bearing during the pitching; estimating a condition of the blade pitch bearing based on the measured amount of vibration. Also disclosed is an arrangement for monitoring a blade pitch bearing, a rotor blade bearing and a wind turbine.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: February 23, 2021
    Inventors: Soeren Forbech Elmose, Troels Kildemoes Moeller
  • Patent number: 10920793
    Abstract: A centrifugal gas compressor with rotating hollow housing and an independently rotating, turbine compresses gas bubbles in capillary tubes and recovers energy from the liquid drain (sometimes a liquid recycler). The housing rotatably retains an internal spool having the turbine. Gas-liquid emulsion fed to the capillaries generates compressed gas-liquid emulsion at a radially distal annular region in an annular lake within the spool. Compressed gas leaves the lake and is ported away. A turbine blade edge in spilt over liquid drives the turbine, converting angular velocity/momentum into shaft torque as recovered energy. Blade captured liquid is recycled to capillary inputs.
    Type: Grant
    Filed: May 21, 2019
    Date of Patent: February 16, 2021
    Assignee: CARNOT COMPRESSION INC.
    Inventors: Mark A. Cherry, Robert A. Alderman, Danil Hans Shillinger
  • Patent number: 10920619
    Abstract: A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.
    Type: Grant
    Filed: June 19, 2019
    Date of Patent: February 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Etienne Gerard Joseph Canelle, Jacques Marcel Arthur Bunel, Faouzi Aliouat
  • Patent number: 10920788
    Abstract: In order to reduce erosion of an impeller due to liquid droplets in an incoming flow of gas, the impeller comprises converging-diverging bottlenecks; the incoming flow passes through the bottlenecks so that the speed of the gas at the inlet of the impeller first suddenly and substantially increases and then suddenly and substantially decreases; furthermore, the impeller is configured so that, internally after its inlet, the incoming flow is deviated gradually in the meridional plane.
    Type: Grant
    Filed: September 11, 2014
    Date of Patent: February 16, 2021
    Assignee: NUOVO PIGNONE SRL
    Inventors: Alberto Scotti Del Greco, Andrea Arnone, Matteo Checcucci, Filippo Rubechini
  • Patent number: 10920593
    Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: February 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vincent Francois Georges Millier, Francois Pierre Michel Comte, Fabien Stephane Garnier, Alain Dominique Gendraud, Arnaud Lasantha Genilier
  • Patent number: 10920612
    Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.
    Type: Grant
    Filed: July 13, 2016
    Date of Patent: February 16, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott, John Pietrobon
  • Patent number: 10914195
    Abstract: A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Joshua Tyler Mook, Bugra Han Ertas
  • Patent number: 10914194
    Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 10914190
    Abstract: A variable nozzle unit includes a variable nozzle vane which is disposed between a hub wall surface and a shroud wall surface and is rotatable around a rotation axis parallel to a rotation axis of a turbine impeller inside a gas flow passage. The variable nozzle vane includes a leading edge, a trailing edge, a hub end surface facing a hub wall surface, and a shroud end surface facing a shroud wall surface. The variable nozzle vane is twisted around a twist center located between the trailing edge and the rotation axis so that the hub end surface protrudes to a radial outside of a rotation axis in relation to the shroud end surface at the leading edge side and the hub end surface protrudes to a radial inside of the rotation axis in relation to the shroud end surface at the trailing edge side.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: February 9, 2021
    Assignee: IHI Corporation
    Inventor: Natsuko Motoda
  • Patent number: 10914209
    Abstract: An oil tank filling system for filling the oil tank of a gas turbine engine that includes an aft core cowl. The system includes: an oil tank that is located within a core of the engine; an oil access port located on the aft core cowl; an oil tank filling pipe that connects the oil access port to a tank filling port on the oil tank; and a hydraulic lock that prevents oil entering the oil tank once the oil tank contains a predetermined volume of oil. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.
    Type: Grant
    Filed: April 18, 2019
    Date of Patent: February 9, 2021
    Assignee: Rolls-Royce plc
    Inventors: David A. Edwards, Clare L. Bewick
  • Patent number: 10914193
    Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spokes are used as air feed pipe to provide cooling to different engine systems, such as an oil scupper line and a disc cavity of an adjacent turbine disc.
    Type: Grant
    Filed: July 13, 2016
    Date of Patent: February 9, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Remy Synnott
  • Patent number: 10907619
    Abstract: A rotor blade of a wind turbine, the rotor blade including a winglet and a lightning protection system with at least one lightning receptor is provided. The lightning receptor is located at the tip section of the rotor blade. Additionally, the rotor blade includes at least one lightning diverter containing an electrically conductive material, wherein the lightning diverter terminates at the lightning receptor and is located at least partially on the surface of the winglet.
    Type: Grant
    Filed: October 17, 2017
    Date of Patent: February 2, 2021
    Assignee: SIEMENS GAMESA RENEWABLE ENERGY A/S
    Inventor: Thomas Lehrmann Christiansen
  • Patent number: 10907504
    Abstract: A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: February 2, 2021
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: Ludovic Bovyn, Eric Englebert, Maxime Peeters
  • Patent number: 10907654
    Abstract: A rotor disk for an exhaust turbocharger is mounted in a housing of the exhaust turbocharger able to rotate about an axis of rotation. The rotor disk has a disk hub comprising a disk back and a disk front remote from the disk back. A plurality of rotor disk blades are formed on the disk hub in a manner extending between the disk back and the disk front. A balancing mark is arranged in a blade channel formed between a first blade of the plurality of rotor disk blades and a second blade, arranged adjacent to the first blade, of the plurality of rotor disk blades. A width of the balancing mark is less than a length of the balancing mark. The disclosure also relates to an exhaust turbocharger comprising such a rotor disk and to a method for balancing a rotor assembly for such an exhaust turbocharger.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: February 2, 2021
    Assignees: IHI Charging Systems International GmbH, IHI Charging Systems International Germany GmbH
    Inventors: Diana Feustel, Ingo Zähringer, Torsten Gramsch, Martin Kreschel
  • Patent number: 10907499
    Abstract: A rotor-blade-side sealing apparatus is configured to seal leakage of working fluid between rotor blade rings connected to distal end portions of rotor blade main bodies attached so as to extend in a radial direction from a rotor main body configured to rotate about an axis in a casing, and an inner circumferential surface of the casing. The rotor-blade-side sealing apparatus includes a sealing fin protruding in the radial direction from a side of the inner circumferential surface of the casing toward one of the rotor blade rings and extending in a circumferential direction. The sealing fin includes: a first sealing-fin main body portion and a second sealing-fin main body portion separated from each other in the circumferential direction across a gap portion that is a discontinuity along the circumferential direction; and an extending portion extending toward an upstream side in an axial direction of the rotor main body.
    Type: Grant
    Filed: February 22, 2019
    Date of Patent: February 2, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Makoto Iwasaki, Rimpei Kawashita, Yasunori Tokimasa
  • Patent number: 10907648
    Abstract: A fan blade for a gas turbine engine includes an airfoil that has a first chord line that extends from a leading edge to a trailing edge. The first chord line is at 0% at the leading edge and at 100% at the trailing edge. The airfoil has a first local maximum thickness defined between about 85% of a span to a tip, a second local maximum thickness defined between about 40% to about 85% of the span and a third local maximum thickness defined between a root to about 40% of the span. The second local maximum thickness is positioned at about 10% to about 30% of the first chord line so as to be offset from the first local maximum thickness in the chordwise direction toward the leading edge. Each of the first, second and third local maximum thicknesses are different.
    Type: Grant
    Filed: August 8, 2017
    Date of Patent: February 2, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Constantinos Vogiatzis
  • Patent number: 10899432
    Abstract: Fan module with variable-pitch blades for a propulsion system that includes: a rotor supporting the blades, and including an internal shaft and an external shroud, defining between them a space; a pitch control device (22) of the blades that includes a load transfer bearing; a feathering device of the blades; said feathering device includes at least one lever that is articulated around a fixed axis (A) in relation to the rotor, where said lever features a first end located outside said space and a second end located inside said space, and where a flyweight is fastened to the first end and the second end is coupled to said bearing.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: January 26, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Gilles Alain Marie Charier, Kevin Morgane Lemarchand
  • Patent number: 10900366
    Abstract: A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.
    Type: Grant
    Filed: January 28, 2019
    Date of Patent: January 26, 2021
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: Rémy Princivalle, Enrique Penalver Castro, Matthieu Janssens
  • Patent number: 10900359
    Abstract: Provided is a turbocharger, including: a compressor impeller (impeller) having a through hole; a shaft inserted through the through hole; and a fastening member caulked to a distal end portion of the shaft projecting from the through hole.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: January 26, 2021
    Assignee: IHI Corporation
    Inventor: Yoshimitsu Matsuyama