Patents Examined by John S Hunter, Jr.
  • Patent number: 10876479
    Abstract: An acoustic liner can include a support layer having a set of partitioned cavities with open faces, a first facing sheet and second facing sheet both having perforations and operably coupled to the support layer such that the facing sheets overlie and close the open faces, and an aerogel layer operably coupled to the second facing sheet.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: December 29, 2020
    Assignee: MRA SYSTEMS, LLC.
    Inventors: Andrew Michael Roach, David Patrick Calder, Graham Frank Howarth
  • Patent number: 10864985
    Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The inner-member includes a boss configured for location to and engagement with a yoke. The boss includes a tapered profile (e.g., conic) portion. A tapered recess region of the yoke includes a profile that is substantially matched to receive and contact the tapered profile of the boss. The CF bearing is configured for attachment to a grip of the rotor assembly. The boss is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: December 15, 2020
    Assignee: Textron Innovations Inc.
    Inventors: John McCullough, Mark Adam Wiinikka, Matthew Curtis Ledbetter
  • Patent number: 10859001
    Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft; and a gearbox support arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: the ? ? torsional ? ? shear ? ? stress ? ? of ? ? the ? ? gearbox ? ? support ? ? at maximum ? ? takeoff ? ? conditions the ? ? torsional ? ? shear ? ? stress ? ? of ? ? the ? ? gearbox ? ? support ? ? at cruise ? ? conditions is less than or equal to 3.20. A method of operating the gas turbine engine is also disclosed.
    Type: Grant
    Filed: March 17, 2020
    Date of Patent: December 8, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10858958
    Abstract: A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure secured to a turbine casing and having two annular flanges, each ring sector having two tabs held between the two annular flanges. The ring support structure includes an annular retention band mounted on the turbine casing, the annular retention band including an annular web forming one of the flanges. The two annular flanges exert stress on the tabs of the ring sectors. One of the flanges is elastically deformable in the axial direction of the turbine ring. The band has a first series of teeth distributed circumferentially on the band and the turbine casing has a second series of teeth distributed circumferentially on the casing, and the teeth of the first series and the teeth of the second series together provide circumferential jaw coupling.
    Type: Grant
    Filed: May 18, 2016
    Date of Patent: December 8, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel
  • Patent number: 10851654
    Abstract: An arrangement for a turbine has a metallic support structure having at least one radial support strut and a multiplicity of plate-shaped, fiber-reinforced ceramic segments which are arranged one on top of the other on the support structure and together define the circumferential contour, the segments being provided with through-openings through which the at least one support strut extends, wherein the at least one support strut has outwardly-extending projections that extend perpendicular to the radial direction and engage in corresponding recesses formed in the segments.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: December 1, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventor: Bernd Burbaum
  • Patent number: 10851791
    Abstract: A device for moving a fluid with magnetic gear includes two first balls each having a shape of sphere, respectively fixed to a rotating first shaft through respective centers of the sphere, each of the first balls having a first magnetic dipole in a direction orthogonal to the first shaft; and a second ball having a shape of sphere attaching a blade structure thereon to move the fluid, fixed to a freely rotatable second shaft through a center of the sphere, and having a second magnetic dipole in a direction orthogonal to the second shaft, wherein the centers of the first and second balls altogether form an isosceles triangle with a vertex angle ? being defined about the center of the second ball, satisfying ? = 2 ? arcsin ? ( 1 3 ) ? 70.53 ? ° .
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: December 1, 2020
    Assignee: Okinawa Institute of Science and Technology School Corporation
    Inventors: Johannes Richard Schoenke, Eliot Martin Fried
  • Patent number: 10844742
    Abstract: A heat shield (100) and method for assembling such is disclosed. The heat shield (100) may comprise an outer wall (122) and an inner wall (124). The outer wall (122) includes a first member (130), a flange (132) extending outward from the first member (130) and a first inner edge (134). The first member (130) extends from the flange (132) to the first inner edge (134). The inner wall (124) includes a second member (140), a rim (142) extending outward from the second member (140) and a second inner edge (144). The second member (140) extends from the rim (142) to the second inner edge (144). The inner wall (124) is spaced apart from the outer wall (122), the first and second edges form an air gap (146) between them, and the inner wall (124) and the outer wall (122) form a cavity (148).
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: November 24, 2020
    Assignee: BorgWarner Inc.
    Inventors: Jonathan Williams, Raj Chandramohanan, Robert Race
  • Patent number: 10836476
    Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The outer-member includes an upper flange extension and a lower flange extension for location to and engagement with a grip. The upper flange extension is disposed over an upper surface portion of the elastic member, and the lower flange extension is disposed under a lower surface portion of the elastic member. The CF bearing is configured for attachment to a grip of the rotor assembly. The outer-member is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.
    Type: Grant
    Filed: August 1, 2017
    Date of Patent: November 17, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Mark Adam Wiinikka, Nathan Patrick Green, John R. McCullough
  • Patent number: 10837370
    Abstract: A gas turbine engine including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft mounting structure that includes supporting bearings connected to the fan shaft; and an epicyclic gearbox that can receive input from the core shaft, and output drive to the fan shaft so as to drive the fan at a lower rotational speed than the core shaft. The gearbox includes a sun gear, planet gears, a ring gear, and a planet carrier for mounting the planet gears. A torsional stiffness of the planet carrier is greater than or equal to 1.6×108 Nm/rad. The fan shaft mounting structure has: a radial bending stiffness greater than or equal to 7.00×108 N/m, and/or a tilt stiffness greater than or equal to 1.50×107 Nm/rad.
    Type: Grant
    Filed: March 17, 2020
    Date of Patent: November 17, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10837368
    Abstract: An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the open faces. A set of aerogel fillings can be provided within at least some of the set of cells.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: November 17, 2020
    Assignee: MRA SYSTEMS, LLC
    Inventors: Graham Frank Howarth, David Patrick Calder, Andrew Michael Roach
  • Patent number: 10830154
    Abstract: A gas turbine engine includes: an engine core with a turbine, compressor, and core shaft; a fan upstream the engine core; a gearbox that can receive an input from the core shaft and output drive to a fan shaft to drive the fan at a lower rotational speed than the core shaft. A fan-gearbox axial distance is greater than or equal to 0.35 m. The fan shaft has: (i) a radial bending stiffness ratio of a radial bending stiffness of the fan shaft at the fan input to a radial bending stiffness of the fan shaft at the gearbox output that is greater than or equal to 6.0×10?3; and/or (ii) a tilt stiffness ratio of a tilt stiffness of the fan shaft at the fan input to a tilt stiffness of the fan shaft at the gearbox output that is greater than or equal to 2.5×10?2.
    Type: Grant
    Filed: March 3, 2020
    Date of Patent: November 10, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10823057
    Abstract: An outlet tube arrangement for an aircraft nacelle may comprise a vent tube defining a vent tube outlet, the vent tube outlet configured to be flush with an outer surface of the aircraft nacelle, and an inner tube disposed within the vent tube, the inner tube configured to increase momentum of fluid flowing through the inner tube to urge the fluid to separate from the inner tube without wetting the aircraft nacelle upon exiting from the vent tube, wherein the inner tube comprises an inner tube inlet comprising an inlet cross-sectional area and an inner tube outlet comprising an outlet cross-sectional area, the inlet cross-sectional area being less than a cross-sectional area of the vent tube at the inner tube inlet, the inlet cross-sectional area being greater than the outlet cross-sectional area, and the inner tube outlet being flush with the vent tube outlet.
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: November 3, 2020
    Assignee: Rohr, Inc.
    Inventors: Lubomir A. Ribarov, Joel H. Frank
  • Patent number: 10823084
    Abstract: An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft so as to drive the fan at a lower rotational speed than the core shaft, the gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support arranged to mount the gearbox within the engine. The fan shaft, core shaft, gearbox and the gearbox support together may form a transmission.
    Type: Grant
    Filed: March 3, 2020
    Date of Patent: November 3, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10822981
    Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Alexander Martin Sener, Brian David Keith, David Alan Frey, Jamil Darnell Grant
  • Patent number: 10815963
    Abstract: A trailing edge for a rotor blade tip of an aerodynamic rotor of a wind turbine. The trailing edge comprises a trailing edge delimiting line, which replicates the contour of the trailing edge, and multiple serrations to improve flow behavior at the trailing edge. The serrations are provided at the trailing edge in dependence on the trailing edge delimiting line, and consequently on geometrical and operating parameters.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: October 27, 2020
    Assignee: Wobben Properties GmbH
    Inventors: Mohammad Kamruzzaman, Andree Altmikus
  • Patent number: 10815901
    Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.
    Type: Grant
    Filed: March 3, 2020
    Date of Patent: October 27, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10801352
    Abstract: The invention concerns a turbine for a gas turbine comprising a blade, a vane and an abradable lip attached to the blade or to the vane, wherein the blade and the vane are separated by a gap and the abradable lip extends part of the distance across the gap. Embodiments include the addition of an abrasive layer attached on the other side of the gap from the abradable lip. A method of manufacturing is also described.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: October 13, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Guillaume Wagner, Herbert Brandl, Emanuele Facchinetti, Matthias Hoebel, Carlos Simon-Delgado
  • Patent number: 10801339
    Abstract: A variable pitch fan assembly includes variable pitch fan blades circumscribed about engine centerline axis coupled to a drive shaft centered about the engine centerline axis. Each blade pivotable about pitch axis perpendicular to centerline axis and having blade turning lever connected thereto. One or more linear actuators non-rotatably mounted parallel to engine centerline axis and operably linked to fan blades for pivoting fan blades and connected to spider ring through thrust bearings for transmission of axial displacement of non-rotatable actuator rods of actuators while the fan blades are rotating. Spider arms extending away from spider ring towards blade roots and each spider arm connected to one of the turning levers. Turning levers may be connected and caromed to spider arms by pin and slot joint. Each spider arm may include joint pin disposed through joint slot of turning lever. Joint slot may be angled or curved.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Aldo Daniel Lopez Guzman, Alberto del Angel Duran, Daniela Martinez Arteaga, Carla Garcia Lopez de Llergo, Ileana Prisabel Corona Acosta
  • Patent number: 10801406
    Abstract: An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Valery Ivanovich Ponyavin, Bradly Aaron Kippel, Laxmikant Merchant, Hua Zhang, Naveen Parmeshwar
  • Patent number: 10774840
    Abstract: A fan blade capable of cooling an enclosed space is disclosed, comprising: a leading edge; a trailing edge; a top side; a bottom side; and a plurality of passageways wherein each of the passageways narrows within the fan blade. The plurality of passageways may narrow at any point within the interior of the fan blade and may be shaped in any way to ensure that a narrowing occurs. The plurality of passageways may also be in thermal communication with the rest of the fan blade. The fan blades may be used as part of a fan having a hub and a plurality of fan blades. Also disclosed, is a method of cooling a room comprising rotating a fan, the fan comprising: a plurality of fan blades, each fan blade having a plurality of passageways, wherein each of the passageways narrows within the fan blade.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: September 15, 2020
    Assignee: COOL-AIR LLC.
    Inventor: Lance B. Young