Aerodynamic Resistance Reducing Patents (Class 244/130)
  • Patent number: 11920617
    Abstract: Fluid systems and methods for addressing fluid separation are described. An example fluid system includes a main body and a fluid pressurizer. The main body has a first portion, a second portion, an injection opening, a suction opening, a channel that extends from the suction opening to the injection opening, and a side wall. The first portion has a first axis that extends along the side wall. The second portion has a second axis that extends along the side wall at an angle relative to the first axis such that when fluid flows over the main body flow separation is defined adjacent to the second portion. The injection opening is disposed at a first location relative to said flow separation. The suction opening is disposed at a second location relative to said flow separation. The channel extends from the suction opening to the injection opening.
    Type: Grant
    Filed: July 22, 2020
    Date of Patent: March 5, 2024
    Assignee: COFLOW JET, LLC
    Inventor: Gecheng Zha
  • Patent number: 11913378
    Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.
    Type: Grant
    Filed: October 15, 2020
    Date of Patent: February 27, 2024
    Assignees: INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE, SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Jérôme Jean Tantot, Xavier Carbonneau, Philippe Gérard Chanez, Nicolas Garcia Rosa, Alejandro Martin Pleguezuelo, Nicolas Joseph Sirvin
  • Patent number: 11905983
    Abstract: A fluid control system includes a dielectric-barrier discharge (DBD) device, and processing circuitry. The processing circuitry is configured to obtain a streamwise length scale of a fluid flowing over a surface. The processing circuitry is also configured to obtain a convective time scale of the fluid flowing over the surface. The processing circuitry is also configured to operate the DBD device, based on the streamwise length scale and the convective time scale, to adjust a flow property of the fluid.
    Type: Grant
    Filed: January 21, 2021
    Date of Patent: February 20, 2024
    Assignee: Deep Science, LLC
    Inventors: Brian C. Holloway, David William Wine
  • Patent number: 11891185
    Abstract: A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.
    Type: Grant
    Filed: May 18, 2021
    Date of Patent: February 6, 2024
    Assignee: SAFRAN NACELLES
    Inventors: Patrick André Boileau, Jean-Philippe Joret, Vincent Jean-François Peyron, Gina Ferrier
  • Patent number: 11878808
    Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle. The nacelle includes an inlet structure and a cowl. The inlet structure extends axially in a first direction along a centerline to an inlet structure aft end. The inlet structure includes a clip and a hoist bracket integrated with the clip. The clip is at the inlet structure aft end. The clip includes a locator receptacle. The hoist bracket is configured to provide a structural lift point for the inlet structure during assembly and/or disassembly of the nacelle. The cowl extends axially in a second direction along the centerline to a cowl forward end. The cowl includes a locator at the cowl forward end. The locator includes a protrusion received by the locator receptacle.
    Type: Grant
    Filed: April 5, 2023
    Date of Patent: January 23, 2024
    Assignee: Rohr, Inc.
    Inventor: Pratap Mallampati
  • Patent number: 11840286
    Abstract: An airflow adjusting apparatus to be provided in a vehicle includes a flap and an airflow generator. The vehicle includes a wheel disposed to be partly protruded downward from a vehicle body of the vehicle. The flap is protruded, in front of the wheel, downward from the vehicle body. The airflow generator is configured to generate an airflow, and provided in an underneath of the vehicle body. The airflow generator is configured to generate an airflow. The airflow moves backward and downward of the vehicle and the airflow moves obliquely relative to a horizontal plane.
    Type: Grant
    Filed: June 14, 2021
    Date of Patent: December 12, 2023
    Assignee: SUBARU CORPORATION
    Inventors: Naoto Watanabe, Yusaku Dogahira
  • Patent number: 11780509
    Abstract: A modular aerodynamic system for a vehicle includes multiple nozzles that generate airsheets. The airflow from the nozzles may be controlled separately. Thus, the nozzles collectively enable granular control of the overall air velocity profile around (e.g., behind) the vehicle. The airsheet configuration may allow the system to control the wake behind the vehicle for various purposes, such as drag reduction, stabilization, and/or breaking. The overall air velocity profile may increase the back pressure of the vehicle, reducing energy consumption. The system may also move the center of pressure and changing the dynamic response of the vehicle to other external forces. These changes may be implemented dynamically in response to aerodynamic/dynamic changes.
    Type: Grant
    Filed: September 16, 2020
    Date of Patent: October 10, 2023
    Assignee: Aeromutable Corporation
    Inventor: David Esteban Manosalvas-Kjono
  • Patent number: 11718386
    Abstract: A cupola fairing (250) for reducing drag and increasing lift on an aircraft fuselage (210) and wings (220). The fairing includes a housing length extending along a longitudinal axis, and a variable width extending normal to the longitudinal axis. The housing width is variable and defined by a plurality of cross-sectional areas of the cupola fairing. The fairing has a substantially smooth exterior surface that is curved along the length and the variable width of the housing. The housing surface has its longitudinal and transverse curvatures being defined by metrics corresponding to a reference wing root chord of the aircraft (200), a cross-sectional area of the fuselage, a percentage of the cross-sectional area to be covered by the fairing, and positioning of the cupola fairing on the crown portion of the fuselage (210). The housing has a lower surface configured to conform to a shape of the crown at which the cupola fairing (250) is positioned.
    Type: Grant
    Filed: September 20, 2018
    Date of Patent: August 8, 2023
    Assignee: Aero Design Labs LLC
    Inventor: Eric A. Ahlstrom
  • Patent number: 11691679
    Abstract: An airflow adjusting apparatus to be provided in a vehicle includes a flap and an airflow generator. The vehicle includes a wheel disposed to be partly protruded downward from a vehicle body of the vehicle. The flap is protruded, in front of the wheel, downward from the vehicle body. The airflow generator is provided in an underneath of the vehicle body and vehicle-widthwise inwardly from the wheel. The airflow generator is configured to generate an airflow vehicle-widthwise inward, and backward of the vehicle. The airflow moves obliquely relative to a vehicle longitudinal direction when the vehicle travels forward.
    Type: Grant
    Filed: June 14, 2021
    Date of Patent: July 4, 2023
    Assignee: SUBARU CORPORATION
    Inventors: Naoto Watanabe, Yusaku Dogahira
  • Patent number: 11679870
    Abstract: A fairing assembly is provided about a duct outlet port, which is not parallel to an exterior surface of a vehicle, so as to turn fluid flow exiting the duct outlet port in a direction of surface fluid flow. The fairing assembly includes an upstream vane fairing to orient the surface flow with the angled duct flow, a downstream Coanda fairing to turn transverse duct flow in the direction of the surface flow, and a pair of vortex generators each of which is positioned at an opposing lateral side of the Coanda fairing and angled towards each other to organize the combined fluid flow downstream of the duct outlet port to thereby minimize recirculation. This fairing assembly about the duct outlet port enhances organized mixing of the duct and surface flows, and thereby reduces duct and surface recirculation, duct restriction, and overall vehicle drag.
    Type: Grant
    Filed: December 13, 2018
    Date of Patent: June 20, 2023
    Assignee: Aero Design Labs LLC
    Inventors: Eric A. Ahlstrom, Lee Sanders
  • Patent number: 11673617
    Abstract: Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.
    Type: Grant
    Filed: June 16, 2022
    Date of Patent: June 13, 2023
    Assignee: ESS 2 TECH, LLC
    Inventors: Michael Suk, David A. Shoffler
  • Patent number: 11603214
    Abstract: A method for calibrating a target gas sensor inside a drone comprises receiving air flow at the target sensor due to least one of diverted propeller air flow or diverted air flow caused by drone flight, measuring a concentration of the target gas, receiving equivalent air flow at a sensor of at least one reference gas having known atmospheric concentration positioned in or on the drone, measuring a concentration of the at least one reference gas, and calibrating the measured concentration of the target gas based on the measured concentration of the at least one reference gas.
    Type: Grant
    Filed: June 4, 2020
    Date of Patent: March 14, 2023
    Assignee: SAUDI ARABIAN OIL COMPANY
    Inventors: Brian Parrott, Fadl Abdellatif
  • Patent number: 11603145
    Abstract: An active drag-reduction system has first 22 and second 24 fluid outlets located on a vehicle 10 adjacent to a low pressure (drag) region 12, wherein fluid ejected from the second fluid outlet 24 is at a higher pressure/ejection velocity than from the first fluid outlet 22. Turbulent and/or low pressure regions adjacent to vehicles are not uniform, but rather have a varying intensity. For instance, the centre of a region may have a lower pressure and/or more turbulent nature than the periphery of the region. The system injects relatively higher pressure air or relatively higher speed air into the relatively lower pressure/more turbulent part of the low pressure/turbulent region, and relatively lower pressure air or relatively lower speed air into the relatively higher pressure/less turbulent part of the low pressure/turbulent region, compared to each other.
    Type: Grant
    Filed: January 13, 2021
    Date of Patent: March 14, 2023
    Assignee: OGAB LTD.
    Inventors: Osama Elogab, Hatem Elogab
  • Patent number: 11535360
    Abstract: Some variations provide a leading-edge heat pipe comprising: (a) an envelope fabricated from a shell material, wherein the envelope includes at least one edge with a radius of curvature of less than 3 mm, and wherein the envelope includes, or is in thermal communication with, at least one heat-rejection surface; (b) a porous wick fabricated from a ceramic or metallic wick material, wherein the porous wick is configured within a first portion of the interior cavity, wherein at least a portion of the porous wick is adjacent to the inner surface, and wherein the porous wick has a bimodal pore distribution comprising an average capillary-pore size from 0.2 microns to 200 microns and an average high-flow pore size from 100 microns to 2 millimeters (the average high-flow pore size is greater than the average capillary-pore size); and (c) a phase-change heat-transfer material contained within the porous wick.
    Type: Grant
    Filed: May 17, 2020
    Date of Patent: December 27, 2022
    Assignee: HRL Laboratories, LLC
    Inventors: Christopher S. Roper, Mark R. O'Masta, Tobias A. Schaedler, Jacob M. Hundley, Tiffany Stewart
  • Patent number: 11525365
    Abstract: A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: December 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
  • Patent number: 11518499
    Abstract: An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.
    Type: Grant
    Filed: August 7, 2020
    Date of Patent: December 6, 2022
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Trevor Howard Wood
  • Patent number: 11466709
    Abstract: Systems and methods are described herein to implement transverse momentum injection at low frequencies to directly modify large-scale eddies in a turbulent boundary layer on a surface of an object. A set of transverse momentum injection actuators may be positioned on the surface of the object to affect large-scale eddies in the turbulent boundary layer. The system may include a controller to selectively actuate the transverse momentum injection actuators with an actuation pattern to affect the large-scale eddies to modify the drag of the fluid flow on the surface. In various embodiments, the transverse momentum injection actuators may be operated at frequencies less than 10,000 Hertz.
    Type: Grant
    Filed: February 16, 2022
    Date of Patent: October 11, 2022
    Assignee: Deep Science, LLC
    Inventors: Alexander J. Smits, Ivan Marusic, David Wine, Brian Holloway
  • Patent number: 11447238
    Abstract: A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: September 20, 2022
    Assignee: AMERICAN HONDA MOTOR CO., INC.
    Inventors: Scott Rewerts, Yuichi Kawamura, Kui Ou, Michimasa Fujino, Kazuhisa Mahiko
  • Patent number: 11427303
    Abstract: Noise-abatement systems provide noise abatement to a wing assembly provided with a forward edge slat and include an elongate shield element which is unconnected but positionable adjacent to a lower trailing edge of the edge slat along a lengthwise extent thereof, and a support web having a distal end fixed to the shield element and a proximal end capable of fixation to an interior cove surface of the edge slat adjacent an upper trailing edge thereof. The support web will therefore allow movement of the shield element towards and away from the lower trailing edge of the edge slat between an operative position wherein the shield element is positioned adjacent to the lower trailing edge of the edge slat along the lengthwise extent thereof and an inoperative position wherein the edge slat is spaced from the trailing edge of the edge slat and positioned in the cove region thereof, respectively.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: August 30, 2022
    Assignees: EMBRAER S.A., USP—UNIVERSIDADE DE SÃO PAULO
    Inventors: Danillo Cafaldo Dos Reis, Leandro Guilherme Crenite Simões, Micael Gianini Valle Do Carmo, Eduardo Lobão Capucho Coelho, Leandro Souza De Moura Lima, Fernando Martini Catalano, Cecil Wagner Skaleski, Francisco Keller Klug, Marcus Felipe Hori Ochi
  • Patent number: 11427346
    Abstract: Cable retainer apparatuses for retaining a cable, and aircraft and methods including such apparatuses are provided. In one example, a cable retainer for retaining a cable proximate a surface of an aircraft includes a cable retainer. The cable retainer is configured to retain the cable. A fairing is disposed about the cable retainer and is configured to couple to the aircraft to support the cable retainer adjacent to the surface of the aircraft.
    Type: Grant
    Filed: September 18, 2019
    Date of Patent: August 30, 2022
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Michael Berceli, Paul Bradford, Aaron Willson, Patrick King, Robert Norris, Patrick Carver, David Bryk
  • Patent number: 11396367
    Abstract: Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.
    Type: Grant
    Filed: May 8, 2019
    Date of Patent: July 26, 2022
    Assignee: THE BOEING COMPANY
    Inventor: Eric W. Walliser
  • Patent number: 11305862
    Abstract: A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes.
    Type: Grant
    Filed: December 20, 2019
    Date of Patent: April 19, 2022
    Assignee: The Boeing Company
    Inventors: Mark R. McLaughlin, Jenny Young, Drew-Daniel T. Keefe, Charles B. Lockin, David H. Leibov
  • Patent number: 11300097
    Abstract: A wind turbine blade apparatus at least includes a wind turbine blade body, wherein a serration portion is disposed on at least on a part of a trailing edge of the wind turbine blade body, the serration portion having a saw-teeth shape where a mountain portion and a valley portion are arranged alternately in a blade longitudinal direction, and wherein a chord-directional cross section of the wind turbine blade body along a chord direction is formed to have an airfoil shape at any position in a region from the mountain portion to the valley portion.
    Type: Grant
    Filed: February 4, 2020
    Date of Patent: April 12, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Shoeji Nakaye, Kentaro Hayashi, Atsushi Yuge, Kai Karikomi, Shinsuke Nishimura
  • Patent number: 11279468
    Abstract: An aircraft surface cover is provided. The aircraft surface cover includes a cover member that is configured to be removably secured to an aircraft structure. The cover member includes an exterior surface that has a microtextured surface including microtexture ribs that are configured to improve aerodynamic performance of the aircraft structure.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: March 22, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Michelle Crivella, Matthew Berden
  • Patent number: 11254411
    Abstract: An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a
    Type: Grant
    Filed: March 16, 2018
    Date of Patent: February 22, 2022
    Assignee: FOKKER AEROSTRUCTURES B.V.
    Inventor: Adrianus Marinus Franciscus Bastiaansen
  • Patent number: 11235855
    Abstract: An aerodynamic structure comprising an aerodynamic surface. The aerodynamic surface is formed by a first part of the aerodynamic structure; a second part of the aerodynamic structure; and a sealed gap between the first part and the second part. The sealed gap contains a sealant material and a support material.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: February 1, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: David Liversage, Darren Crew
  • 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: 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: 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: 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: 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