Aerodynamic Resistance Reducing Patents (Class 244/130)
  • Patent number: 11225909
    Abstract: A combustor and a gas turbine having the same which can improve a degree of mixing of fuel and air and achieve a reduction in combustion vibration are provided. The combustor may include a fuel nozzle disposed on a nozzle tube, a center body disposed at a center of the fuel nozzle and connected to a fuel nozzle base, a plurality of swirlers circumferentially spaced apart from each other between the center body and the fuel nozzle, and a plurality of fuel pegs spaced apart from each other around the center body to inject fuel into air flowing in the fuel nozzle, wherein the plurality of fuel pegs are disposed behind the swirlers on the center body based on a combustion chamber of the combustor.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: January 18, 2022
    Inventor: Dongsik Han
  • Patent number: 11174004
    Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine having a first segment and a second segment. The first segment is fixedly coupled to a nacelle. The second segment is rotatable relative to the first segment about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.
    Type: Grant
    Filed: May 20, 2019
    Date of Patent: November 16, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Thomas K. Dodt, Adam M. Clark
  • Patent number: 11174009
    Abstract: An aircraft landing gear arrangement with an airbag attached inside a landing gear bay is disclosed. The airbag has a deflated configuration and a first inflated configuration, wherein, when the landing gear is in the extended position and when the airbag is in the first inflated configuration, the airbag closes off the landing gear bay. The airbag may substantially close off the landing gear bay. The airbag may comprise an external surface, wherein the external surface of the airbag closes off at least a significant proportion of the landing gear bay and lies substantially flush with an external surface of the aircraft body. An aircraft, methods of operating a landing gear arrangement, and methods of operating an aircraft are disclosed.
    Type: Grant
    Filed: August 14, 2019
    Date of Patent: November 16, 2021
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Henry Edwards, Keith Macgregor
  • Patent number: 11148782
    Abstract: A strake for a turbine engine nacelle may comprise a forward portion coupled to a turbine engine nacelle inlet, and an aft portion coupled to a turbine engine nacelle fan cowl, wherein the aft portion is configured to move between a first position and a second position, and the aft portion engages the forward portion in response to the aft portion moving to the second position to secure the fan cowl with respect to the inlet.
    Type: Grant
    Filed: January 24, 2019
    Date of Patent: October 19, 2021
    Assignee: Rohr, Inc.
    Inventor: Saravanakumar Vijayakumar
  • Patent number: 11085471
    Abstract: Systems and method for active control of stationary vortices for aerodynamic structures are disclosed herein. In one embodiment, a method for active control of vortices over a solid surface includes: generating vortices proximate to the solid surface; sensing locations of vortices by printed skin sensors; and maintaining the vortices in their fixed spanwise positions with respect to the solid surface by actuation of printed skin actuators.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: August 10, 2021
    Assignees: Quest Integrated, LLC, University of Washington
    Inventors: Giovanni Nino, Robert E. Breidenthal, Aline Cotel
  • Patent number: 11072413
    Abstract: A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.
    Type: Grant
    Filed: May 11, 2018
    Date of Patent: July 27, 2021
    Assignee: Rohr, Inc.
    Inventors: Teresa M. Kruckenberg, Vijay V. Pujar, Robert L. Braden
  • Patent number: 11059565
    Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the stowed position to the deployed position in response to an aerodynamic force exerted on a deployment vane of the fence.
    Type: Grant
    Filed: November 21, 2018
    Date of Patent: July 13, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Brian Tillotson, Chris Kettering
  • Patent number: 11040769
    Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).
    Type: Grant
    Filed: July 9, 2018
    Date of Patent: June 22, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Geza Schrauf, Christian Heck
  • Patent number: 11014651
    Abstract: Enhanced high-speed aircraft performance, including increased lift/drag ratio, from localized high-temperature speed of sound increases, and associated systems and methods are disclosed. A representative method for operating a vehicle includes, while a lifting body of the vehicle is immersed in a gas, heating the gas in a target volume sufficiently to increase the speed of sound in the gas relative to the speed of sound in the gas outside the target volume. The target volume can be positioned adjacent to, forward of, and/or along a pressure surface of the lifting body.
    Type: Grant
    Filed: June 30, 2017
    Date of Patent: May 25, 2021
    Assignee: Electric Sky Holdings, Inc.
    Inventor: Jeffrey Greason
  • Patent number: 10995780
    Abstract: An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: May 4, 2021
    Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbH
    Inventors: Ralf Caspari, Robert Weichwald, Emanuel Ermann, Gerd Heller, Detlev Konigorski, Stefan Schnäubelt, Nicole Jordan
  • Patent number: 10986883
    Abstract: A low drag garment is made from a fabric having a textured region with a texture height H, wherein the texture height H increases substantially continuously with the surface angle ? in said textured region. Optionally, the substantially continuous increase in texture height H comprises a plurality of incremental increases in texture height, and wherein each incremental increase in texture height is less than 200 ?m.
    Type: Grant
    Filed: April 19, 2016
    Date of Patent: April 27, 2021
    Inventor: Simon Smart
  • Patent number: 10967979
    Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: April 6, 2021
    Assignee: Airbus Operations S.L.
    Inventor: Jose Luis Martinez Munoz
  • Patent number: 10960978
    Abstract: An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: March 30, 2021
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Carlos Alexander Fenny, Rohn Lee Olson, Andrew James Zahasky
  • Patent number: 10946559
    Abstract: Multilayer riblet applique and methods of producing the same are described herein. One disclosed example method includes applying a first high elongation polymer material to a web tool, where the web tool is to be provided from a first roll, and heating, via a first heating process, the first high elongation polymer material. The disclosed example method also includes applying a second high elongation polymer material to the first high elongation polymer material, and heating, via a second heating process, the second high elongation polymer material. The disclosed example method also includes applying, via a laminating roller, a support layer to the second high elongation polymer material.
    Type: Grant
    Filed: October 1, 2018
    Date of Patent: March 16, 2021
    Assignee: The Boeing Company
    Inventors: Diane C. Rawlings, Bruce K. Keough, Larry K. Olli, Alan G. Burg, James M. Kestner, George Michael Granger, James Charles McGarvey
  • Patent number: 10934995
    Abstract: A blade for use in a wind turbine comprises a pressure side and suction side meeting at a trailing edge and leading edge. The pressure side and suction side provide lift to the turbine blade upon the flow of air from the leading edge to the trailing edge and over the pressure side and suction side. The blade includes one or more openings at the suction side, in some cases between the leading edge and the trailing edge. The one or more openings are configured to provide a pressurized fluid towards the leading edge of the blade, in some cases at an angle between about 0° and 70° with respect to an axis oriented from a centerline of the blade toward the leading edge.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: March 2, 2021
    Assignee: KOHANA TECHNOLOGIES INC.
    Inventors: Michael D. Zuteck, Leigh Zalusky, Paul Lees
  • Patent number: 10919618
    Abstract: A device for influencing the wake flow of an aircraft wing having a high pressure side and a lower pressure side, the device including a body adapted for attachment in the region of the tip of the aircraft wing and having a through-duct with a first opening at a first end of the duct being located on the high pressure side of the wing and a second opening at a second end of the duct being located on the low pressure side of the wing, the duct being configured to permit a fluid flow through the duct so as to inhibit the flow of the fluid around the outboard extremity of the wing and to direct the fluid flow through the duct into a pair of opposing rotating flows of substantially equal magnitude externally of the duct.
    Type: Grant
    Filed: July 18, 2016
    Date of Patent: February 16, 2021
    Assignee: Fourth Dimensional Aerospace Technology Limited
    Inventor: John Jaycott Smith
  • Patent number: 10900509
    Abstract: A member may have a first major surface and a second major surface. The first major surface may define a plurality of riblets that may extend in the direction of a primary flow. The member may form an array of conduits that extend from an entrance port at the second major surface to an exit port at the first major surface. Each of the exit ports may intersect two or more riblets. Each of the exit ports may intersect a riblet that intersect another of the exit ports.
    Type: Grant
    Filed: January 7, 2019
    Date of Patent: January 26, 2021
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: James Loebig
  • Patent number: 10889370
    Abstract: One embodiment is an apparatus including an airfoil-shaped body; and a chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body. In some embodiments, the chordwise variable vortex generation system includes an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body. In certain embodiments, the surface of the airfoil-shaped body is a top surface of the airfoil-shaped body. In some embodiments, the airfoil-shaped body is an aircraft wing.
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: January 12, 2021
    Assignee: TEXTRON INNOVATIONS INC.
    Inventor: Troy Thomas Bushmire
  • Patent number: 10882605
    Abstract: The present invention provides a riblet structure that further reduces drag, which is a sum of turbulent friction drag and pressure drag, and an object including such a riblet structure. An object such as an aircraft, plant, and pipeline includes a wavelike riblet pattern on a surface. The wavelike riblet pattern includes a large number of wavelike riblets. Each of the large number of wave riblets includes a wavelike ridge line, and a height thereof changes cyclically with respect to a fluid flow direction. With such a configuration, drag, which is a sum of turbulent friction drag and pressure drag, can be further reduced.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: January 5, 2021
    Assignee: JAPAN AEROSPACE EXPLORATION AGENCY
    Inventors: Kie Okabayashi, Yasuhiro Koshioka, Akira Nishizawa, Mitsuru Kurita, Hidetoshi Iijima
  • Patent number: 10871232
    Abstract: An aircraft assembly including: first and second external skin panels having opposing edge faces separated by a gap, the gap having a width in a first direction extending between the opposing edge faces and a depth in a second direction generally orthogonal to the first direction; and a gap seal arranged in the gap to at least partially fill the gap, wherein the gap seal is formed of a material configured such that compression of the gap seal in the first direction results in substantially no expansion of the gap seal in the second direction.
    Type: Grant
    Filed: November 15, 2017
    Date of Patent: December 22, 2020
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Julien Laverne, Philip Jaggard, Matt Harding
  • Patent number: 10858089
    Abstract: A chine spoiler system enhances aircraft wing stall recovery characteristics while optimizing a maximum lift coefficient (CLMAX) of an aft-swept wing on an aircraft having an engine nacelle mounted below the wing. The system includes a chine located on a surface of the nacelle; the chine is configured to generate a vortex at high angles of attack. The vortex passes over an upper surface of the wing, favorably influencing inboard wing aerodynamics to delay airflow separation from the wing, in advance of a stall. The vortex increases CLMAX, but also creates a nose-up pitching moment on an aft-swept wing, which degrades stall recovery. A chine spoiler system module is configured to render the chine ineffective at predetermined wing flap configurations and angles of attack (typically post CLMAX) to balance the objectives of achieving high pre-stall CLMAX, while providing a nose-down pitching moment increment for improved stall recovery.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: December 8, 2020
    Assignee: The Boeing Company
    Inventor: C. Byram Bays-Muchmore
  • Patent number: 10851817
    Abstract: Body provided with a superficial area adapted to reduce drag when the body is moving relative to a gaseous or watery medium, comprising depressions in said superficial area, wherein the depressions have a greater length than width and are provided in the superficial area so as to collectively shape a curvature provided in a length direction of said depressions in the superficial area, and/or said depressions themselves are provided with a curvature in their length direction. The depressions are thus adapted to provide that a turbulent boundary layer of the gaseous or watery medium adjacent to the superficial area of the body is exposed to lateral excitation with reference to a movement direction of the body in the gaseous or watery medium or with reference to a flow direction of said turbulent boundary layer along said superficial area of the body. Said lateral excitation results in a reduction of drag.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: December 1, 2020
    Assignee: DIMPLE IP B.V.
    Inventors: Michiel Van Nesselrooij, Olaf Van Campenhout, Leonardus Louis Maria Veldhuis
  • Patent number: 10844837
    Abstract: An apparatus and system for compensating for various load situations in a turbine includes the use of one or more deployable devices configured to extend an air deflector outwardly from a surface of a rotor blade. The air deflector may subsequently be retracted into the rotor blade once the load falls below a certain threshold. Mechanisms for extending and retracting the air deflector may include pneumatic, hydraulic and/or electromechanical devices. Air deflectors are generally configured to modify the air flow around the rotor blade to increase or decrease power generation, or reduce loads so that the risk of potential damage to components of the wind turbine is minimized. Deflectors may be positioned at various chordwise stations including leading-edge, mid-chord, and trailing-edge locations on the upper and lower surfaces at spanwise positions. Accordingly, a plurality of devices can be actuated to aerodynamically control rotor performance and loads based on wind conditions.
    Type: Grant
    Filed: June 5, 2012
    Date of Patent: November 24, 2020
    Assignee: GE Infrastructure Technology, LLC
    Inventors: Jonathon P. Baker, Kevin Lee Jackson, Edward A. Mayda, Cornelis P. van Dam
  • Patent number: 10821486
    Abstract: A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: November 3, 2020
    Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbH
    Inventors: Ralf Caspari, Robert Weichwald, Emanuel Ermann, Gerd Heller
  • Patent number: 10823207
    Abstract: Pressure oscillations or acoustic loads over an open type cavity having a front face an upper edge of which constitutes a leading edge and having a rear face an upper edge of which constitutes a trailing edge are reduced by applying curvature to the rear face so as to present a convex curved surface internal to the cavity. In one embodiment, a cross-section through a longitudinal axis of the convex curved surface describes part of an ellipse.
    Type: Grant
    Filed: February 2, 2017
    Date of Patent: November 3, 2020
    Inventors: Jacob Cohen, Sudip Das
  • Patent number: 10815974
    Abstract: A method of repairing or reinforcing, or attaching an accessory part to a wind turbine blade includes: determining a criterion to be satisfied by a repair member including a reinforcing fiber and a UV curable resin, the criterion being an adhesion strength of the repair member relative to a base member of the wind turbine blade; determining a work condition including: dimensions of the repair member, the number of the layers of the reinforcing fiber in the repair member, and/or a fiber extension direction of the reinforcing fiber, based on a damage condition of a repair target portion of the wind turbine blade; placing the reinforcing fiber and UV curable resin on the repair target portion based on the determined work condition; and obtaining the repair member by curing the UV curable resin so that the adhesion strength of the repair member relative to the base member satisfies the criterion.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: October 27, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naota Watanabe, Hirokazu Yamasaki, Yoshihiko Hayashi, Eiji Kato
  • Patent number: 10814990
    Abstract: There is provided a propulsion system for an aircraft, the system having a low-fan-pressure-ratio engine configured to be mounted, in a forward over-wing-flow installation, to a wing of the aircraft. The engine has a core, a variable pitch fan, and a nacelle having a nacelle trailing edge with a top-most portion positioned above a wing leading edge. The engine has an L/D ratio of the nacelle in a range of from 0.6 to 1.0, and a fan-pressure-ratio in a range of from 1.10 to 1.30. The forward over-wing-flow installation enables, during all flight phases of the aircraft, a fan flow exhaust to flow behind the nacelle, and to be bifurcated by the wing leading edge, so the fan flow exhaust flows both over the wing and under the wing. During a cruise flight phase of the aircraft, the engine minimizes scrubbing drag of the fan flow exhaust to the wing.
    Type: Grant
    Filed: June 28, 2018
    Date of Patent: October 27, 2020
    Assignee: The Boeing Company
    Inventors: John C. Vassberg, Mark Dehaan, Tony J. Sclafani
  • Patent number: 10808540
    Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Curtis L. Memory, Jin Hu, Thomas J. Praisner
  • Patent number: 10766601
    Abstract: Aircraft wing flaps having aerodynamic restoration doors are described. An example apparatus includes a door to be rotatably coupled to a closure rib of a flap of an aircraft wing. The door is to be moveable between a deployed position and a retracted position. The flap has a leading edge and a cutout formed in the leading edge. The door is to fill a portion of the cutout when the door is in the deployed position.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: September 8, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Eric Milligan, Bryan Jacob Gruner
  • Patent number: 10760600
    Abstract: This disclosure relates to a method and resulting apparatus of applying a riblet sheet comprising a riblet film layer and a riblet liner layer on an airfoil surface. The method comprises applying the riblet film layer of the riblet sheet over the airfoil surface, peeling back at least a portion of the riblet liner layer from the riblet film layer to expose a portion of the riblet film layer, applying a attaching hardware or a non-textured surface film over at least a portion the riblet film layer portion; and applying the peeled back portion of the riblet liner layer over a portion of the attaching hardware.
    Type: Grant
    Filed: October 27, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Sarah Colleen Watson, Elzbieta Kryj-Kos
  • Patent number: 10752343
    Abstract: An electric propulsion system includes a mast defining an axis of rotation. At least one yoke is rotatably mounted to the mast. A fairing assembly surrounds the at least one yoke. An electric motor includes a stator assembly associated with the fairing assembly and a rotor assembly associated with the yoke.
    Type: Grant
    Filed: October 18, 2016
    Date of Patent: August 25, 2020
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Timothy Fred Lauder
  • Patent number: 10745112
    Abstract: A method and system delay the laminar-to-turbulent transition of a supersonic or hypersonic boundary layer flow moving in a flow direction over a surface. For supersonic boundary layer flow, oblique first-mode instability waves present in the boundary layer and propagating at an oblique angle relative to the flow direction cause a laminar-to-turbulent transition in the boundary layer flow. These instability waves have a wavelength associated therewith in a direction perpendicular to the flow direction. Flow disruptors are used to generate modulations within the boundary layer flow wherein a wavelength of the modulations along the direction perpendicular to the flow direction is less than one-half of the wavelength of the instability waves.
    Type: Grant
    Filed: October 16, 2017
    Date of Patent: August 18, 2020
    Assignee: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINSTRATOR OF NASA
    Inventors: Pedro Paredes Gonzalez, Meelan M. Choudhari, Fei Li
  • Patent number: 10730611
    Abstract: An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: August 4, 2020
    Inventor: Larry Utt
  • Patent number: 10734622
    Abstract: According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.
    Type: Grant
    Filed: April 24, 2017
    Date of Patent: August 4, 2020
    Assignee: The Boeing Company
    Inventors: Julie K. Plessner, Douglas D. Maben, Daniel F. Lewinski, George A. McEachen, Mark E. Smith, Michael L. Trent, Richard K. Johnson
  • Patent number: 10723445
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle exterior skin and a strake. The strake is configured with a base and an airfoil that projects out from the base. The base is recessed into and connected to the nacelle exterior skin.
    Type: Grant
    Filed: May 16, 2017
    Date of Patent: July 28, 2020
    Assignee: Rohr, Inc.
    Inventor: Alan J. Binks
  • Patent number: 10723470
    Abstract: A boundary layer ingestion engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan mechanically linked to the turbine via at least one shaft. The linkage is configured such that rotation of the turbine is translated to the fan. The boundary layer ingestion engine further includes an exhaust duct fluidly connected to an outlet of the turbine. The exhaust duct is positioned radially inward of the fan.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: July 28, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord
  • Patent number: 10716340
    Abstract: A vortex generator might be attached to various types of articles to reduce the drag. For example, vortex generators might be attached to a garment or to adhesive tape. In addition, vortex generators might be attached to various types of athletic equipment. A mapping can suggest placement of a vortex-generator arrangement on an article, as well as prescribe particular vortex-generator arrangements for regions of a person.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: July 21, 2020
    Assignee: NIKE, INC.
    Inventors: Yuki Aihara, Leonard W. Brownlie, Jorge E. Carbo, Jr., Edward L. Harber, Ryan P. Henry, Irena Ilcheva, Susan L. Sokolowski
  • Patent number: 10696401
    Abstract: A dispenser for storing and launching countermeasures from an aircraft, comprising an elongate body provided with at least one launch opening adapted for storing the countermeasures in cartridges, where the dispenser comprises a manoeuvrable spoiler arranged in front of the launch opening, where the spoiler is adapted to be fully retracted before a countermeasure has been launched, and that the spoiler is adapted to extend outwards in a predefined manner when a countermeasure has been launched. The advantage of the invention is that a spoiler will reduce induced noise from the open cartridges by extending a spoiler outwards depending on the number of launched countermeasures. This allows for a simple, reliable and cost-effective solution.
    Type: Grant
    Filed: May 5, 2017
    Date of Patent: June 30, 2020
    Assignee: SAAB AB
    Inventor: Christer Zaetterqvist
  • Patent number: 10677790
    Abstract: An optochemical detector and a method for fabricating an optochemical detector includes a light generation unit arranged to emit a light signal; a probe cell unit arranged to alter at least one physical characteristic of the light signal in response to an interaction with a target substance; and a light detection unit arranged to receive the light signal altered by the probe cell unit; wherein a detection of the target substance is characterized by a change in the at least one physical characteristic altered by the probe cell unit.
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: June 9, 2020
    Assignee: City University of Hong Kong
    Inventors: Siu Pang Ng, Chi-man Lawrence Wu, Guang-yu Qiu, Hui Lun Anton Law
  • Patent number: 10612514
    Abstract: In an embodiment, a molding apparatus for a turbine blade includes first and second mold compartments defining a mold cavity when in a closed position, at least one of the first and second mold compartments including a micro-structured surface facing an interior of the mold cavity. The micro-structured surface includes an array of V-shaped channels, and the V-shaped channels have a maximum height of 200 micrometers. A turbine blade including integral micro-structured riblets and method for making the turbine blade is also provided.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: April 7, 2020
    Assignee: 10X TECHNOLOGY LLC
    Inventors: Robert M. Pricone, John C. Nelson
  • Patent number: 10569365
    Abstract: A system and method for preparing a fluid flow surface may include the steps of: (1) producing a laser beam, (2) moving the laser beam across a surface of a work piece, and (3) machining a riblet in the surface by removing material from the surface, wherein the riblet includes a pair of ridges, wherein the pair of ridges is approximately parallel to each other, and each one of the ridges includes opposed sides, and a groove formed between facing ones of the sides and separating the ridges.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: February 25, 2020
    Assignee: The Boeing Company
    Inventor: Weidong Song
  • Patent number: 10556699
    Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.
    Type: Grant
    Filed: April 25, 2017
    Date of Patent: February 11, 2020
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Olivier Pautis, Jerome Colmagro, David Ewens
  • Patent number: 10556702
    Abstract: An aircraft is provided including a propulsor having a plurality of fan blades. The aircraft additionally includes a fuselage, with the propulsor attached to the fuselage at an aft end of the fuselage. A stabilizer extends away from the fuselage proximate the aft end, the stabilizer including a portion positioned upstream of the plurality of fan blades. The aircraft additionally includes an airflow duct extending between an inlet and an outlet. The inlet is positioned to receive an airflow from a location outside the fuselage of the aircraft. The outlet is positioned to exhaust the airflow to at least partially offset a wake upstream of the plurality of fan blades, the wake generated by the stabilizer during operation of the aircraft.
    Type: Grant
    Filed: July 13, 2016
    Date of Patent: February 11, 2020
    Assignee: General Electric Company
    Inventors: Nikolai N. Pastouchenko, Jixian Yao
  • Patent number: 10556671
    Abstract: A tile assembly (22) which, in use, is fitted to a base structure to form at least part of a fluid washed surface. The tile assembly comprises a housing (42) with at least one plenum (45) being provided within the housing (42). A wall (44) of the housing (42) is provided with a plurality of flow passages (46) which extend from the plenum side of the wall (44) to an outer surface (48) of the wall. Flow passage closures (50) are provided which are operable to open and close at least some of the flow passages (46).
    Type: Grant
    Filed: December 22, 2014
    Date of Patent: February 11, 2020
    Assignee: BAE Systems plc
    Inventors: Clyde Warsop, Nisar Ahmed Mirza
  • Patent number: 10487679
    Abstract: A system and method for aerodynamically sealing rotating and fixed components of a gas turbine engine. The system includes a gas turbine engine having a casing and a rotating portion, a plasma actuator having a first and a second electrodes, the first electrode including at least one section of substantially flat conductive material encased in a dielectric material forming at least a portion of a cylinder disposed circumferentially on the casing. The system also includes the rotating portion operably configured as the second electrode, and an excitation source operably connected between the first electrode and the second electrode, the excitation source generating an excitation signal and applying it to the first and second electrodes to cause the actuator to form a plasma between the first and second electrodes, the plasma inducing an airflow between the casing and the rotating portion.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: November 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Guthrie Bagdonis
  • Patent number: 10442534
    Abstract: An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removeably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.
    Type: Grant
    Filed: December 26, 2017
    Date of Patent: October 15, 2019
    Assignee: MBDA UK Limited
    Inventors: Nigel John Taylor, Benjamin James Newby
  • Patent number: 10377471
    Abstract: An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.
    Type: Grant
    Filed: August 14, 2017
    Date of Patent: August 13, 2019
    Inventor: David Birkenstock
  • Patent number: 10337407
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed.
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: July 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Bruce L. Morin, David A. Topol
  • Patent number: 10329917
    Abstract: A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 ?m and a depth of 25-50 ?m.
    Type: Grant
    Filed: February 26, 2014
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventor: John Quitter
  • Patent number: 10330047
    Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined therebetween. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Wesley K. Lord, Robert E. Malecki