By Vortex Control Outside Of Boundary Layer Patents (Class 244/199.1)
  • Patent number: 11745860
    Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a first chine rotatably coupled to a nacelle at a first location about an outer circumference of the nacelle. The first chine is rotatable relative to the nacelle about an axis of rotation. The example apparatus further includes a second chine fixedly coupled to the nacelle at a second location about the outer circumference of the nacelle. The second location is circumferentially offset from the first location.
    Type: Grant
    Filed: May 20, 2019
    Date of Patent: September 5, 2023
    Assignee: The Boeing Company
    Inventor: Christopher Andrew Konings
  • Patent number: 11535362
    Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment oriented along a fore-aft direction. The first segment is translatable relative to the nacelle along the fore-aft direction. The multi-segment chine further includes a second segment oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.
    Type: Grant
    Filed: May 20, 2019
    Date of Patent: December 27, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Christopher Andrew Konings, Miles Anthony Robinson
  • Patent number: 11492097
    Abstract: A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.
    Type: Grant
    Filed: August 27, 2020
    Date of Patent: November 8, 2022
    Assignee: Airbus Operations GmbH
    Inventors: Dort Daandels, Bernhard Schlipf
  • Patent number: 11377204
    Abstract: A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.
    Type: Grant
    Filed: June 10, 2020
    Date of Patent: July 5, 2022
    Assignee: Airbus Operations S.L.
    Inventor: Alberto Arana Hidalgo
  • Patent number: 11247769
    Abstract: An aerodynamic structure for use on an upper surface of an aircraft wing is disclosed. The wing includes a slat operable between a stowed configuration in which the slat is stowed in a slat recess of the wing, and a deployed configuration in which the slat extends out of the slat recess. When the slat is in the deployed configuration, an end face of the slat recess is exposed, the end face intersecting with the upper surface of the wing at a recess edge. The aerodynamic structure, adjacent to the recess edge, has a volume shaped to encourage air flowing over the recess edge onto the upper surface during flight, to remain attached.
    Type: Grant
    Filed: November 4, 2019
    Date of Patent: February 15, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Ching-Yu Hui, Neil John Lyons
  • Patent number: 11194333
    Abstract: Systems, devices, and methods are provided for operating a watercraft vessel. The system can include a communication unit configured to receive a position signal and a velocity signal of the first vessel. The system can include a first sensing unit configured to determine a relative position signal of one or more nearby vessels including the first vessel, a second sensing unit configured to detect and measure a fluid velocity field of a vortex around the watercraft vessel, and a third sensing unit configured to detect and measure an efficiency gain from a lifting force experienced by watercraft vessel operating in an upwash region of the vortex. And the system can include a control unit configured to maneuver the watercraft vessel from a first position to an optimum position.
    Type: Grant
    Filed: November 4, 2020
    Date of Patent: December 7, 2021
    Assignee: Boundary Layer Technologies Inc.
    Inventors: Cameron Flannery, Edward Kearney, Jeremy Osborne, Tim Le Lievre
  • Patent number: 10926865
    Abstract: A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.
    Type: Grant
    Filed: December 11, 2018
    Date of Patent: February 23, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Kevin Tsai, Donald Drew Reinhart
  • Patent number: 10878707
    Abstract: Techniques for updating wake separation distance between aircraft are described. A sensors mesh within a flight path of an aircraft is used to detect when a wake vortex from the aircraft has drifted onto the sensor mesh. A minimum wake separation distance and separation interval for following aircraft are determined based on the various sensor measurements, environmental conditions, and aircraft properties. The minimum wake separation distance and separation interval are used to minimize aircraft separation distances between aircraft that are required due to wake vortex turbulence caused by aircraft during flight.
    Type: Grant
    Filed: July 12, 2019
    Date of Patent: December 29, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Ralf Rene Shu-Zhong Cabos, Jonas Schulze
  • Patent number: 10669024
    Abstract: An unmanned aerial vehicle includes a fuselage, a power device connected to the fuselage, and a control device disposed at the fuselage and electrically connected with the power device. The control device is configured to control the power device to switch an operating mode of the power device to cause the unmanned aerial vehicle to fly in air or navigate on a water surface.
    Type: Grant
    Filed: January 2, 2018
    Date of Patent: June 2, 2020
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventor: Mingyu Wang
  • Patent number: 10286996
    Abstract: An airflow modification patch 14 for reducing aeroacoustic noise generated by an aircraft assembly. The patch has a substrate 14a and a plurality of airflow disruption elements 14b.
    Type: Grant
    Filed: September 9, 2013
    Date of Patent: May 14, 2019
    Assignee: SAFRAN LANDING SYSTEMS UK LTD
    Inventors: Stuart Lacy, Geoff Cumner, Peter Michaelides
  • Patent number: 9340281
    Abstract: A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.
    Type: Grant
    Filed: July 31, 2014
    Date of Patent: May 17, 2016
    Assignee: The Boeing Company
    Inventors: Neal A. Harrison, Mark Dehaan, John C. Vassberg, Anthony J. Sclafani
  • Patent number: 8936213
    Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.
    Type: Grant
    Filed: October 27, 2010
    Date of Patent: January 20, 2015
    Assignee: Airbus Operations S.A.S.
    Inventors: Steve Bedoin, Cyril Bonnaud
  • Patent number: 8916795
    Abstract: A plasma-actuated vortex generator arrangement includes a plurality of spaced-apart vortex generators, and a plasma actuator distributed amongst the plurality of vortex generators.
    Type: Grant
    Filed: March 28, 2011
    Date of Patent: December 23, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Paul D. McClure, Dennis B. Finley, Sergey Macheret
  • Patent number: 8910910
    Abstract: A wing of an aircraft has a pressure-side flow surface and a suction-side flow surface relative to an assumed main direction of attack and comprises a flow fence disposed on a flow surface, wherein the flow fence extends in the main wing chordwise direction and between a location of the pressure-side flow surface and a location of the suction side flow surface.
    Type: Grant
    Filed: April 12, 2013
    Date of Patent: December 16, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Rolf Emunds
  • Patent number: 8870124
    Abstract: A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device.
    Type: Grant
    Filed: July 8, 2010
    Date of Patent: October 28, 2014
    Inventor: Peter Ireland
  • Patent number: 8827201
    Abstract: A fairing (1) for a structural element of a rotorcraft, the fairing including a rear portion (2) that is substantially orthogonal to the longitudinal direction (L) of the aircraft, extending between two spaced-apart trailing edges (3, 4) and thus presenting a determined width, said rear portion (2) closing at least part of the internal volume defined by the fairing (1) and generating aerodynamic drag in forward flight. According to the invention, the rear portion presents, at least at the trailing edges (3, 4), a shape that is perturbed on the streamlines (5) of the air-flow.
    Type: Grant
    Filed: November 30, 2011
    Date of Patent: September 9, 2014
    Assignee: Airbus Helicopters
    Inventor: David Alfano
  • Patent number: 8827210
    Abstract: An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·?; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=
    Type: Grant
    Filed: June 16, 2008
    Date of Patent: September 9, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Detlev Schwetzler
  • Publication number: 20140217240
    Abstract: A vortex generating apparatus includes: a member to contact with a flow of a fluid to form a stagnation point and a first and a second separation points on a periphery of a cross section of the member parallel to the flow; a disturbance applying unit to apply a disturbance to an upstream side of the first separation point to cause part of a boundary layer of the flow to adhere; and a controller to temporally control the application of the disturbance to change an adhesion distance from the stagnation point to the first separation point so as to generate a dynamic stall vortex.
    Type: Application
    Filed: January 29, 2014
    Publication date: August 7, 2014
    Applicant: KABUSHIKI KAISHA TOSHIBA
    Inventors: Motofumi TANAKA, Toshiki Osako, Kazunori Shioda, Hisashi Matsuda, Tatsuro Uchida, Naohiko Shimura
  • Patent number: 8740149
    Abstract: The present disclosure relates to flow channels comprising a channel length having a first portion approximately parallel to the maximum waterline thickness location of a body and at least a second portion non-parallel thereto, a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of the surface of the body, and at least a portion of the free edge being arcuate. A method comprises providing the fluid channel attachable to a body, modifying resultant vortices and reducing or minimizing shock formations or separation regions of the freestream.
    Type: Grant
    Filed: June 3, 2013
    Date of Patent: June 3, 2014
    Assignee: The Boeing Company
    Inventor: Gregory G. Thumann
  • Publication number: 20140070056
    Abstract: An aircraft (10) with improved aerodynamic performances is adapted to keep the directional stability and a very good aerodynamic behaviour at medium-high incidence. The aircraft (10) includes a fuselage (12) to which shaped wings (18, 20) are associated, and a nose (52). The aircraft (10) also includes a vortex control device (72) of the extension of the leading edge of the wing at the root (LERX), shaped in order to symmetrize the bursting of the vortices generated by such LERX with a medium-high incidence. Said aircraft comprises removable equipment with at least one dissipation device of incident radar waves, on at least one hot portion of the aircraft.
    Type: Application
    Filed: May 30, 2011
    Publication date: March 13, 2014
    Applicant: ALENIA AERMACCHI SPA
    Inventors: Emanuele Merlo, Massimo Lucchesini
  • Patent number: 8657238
    Abstract: A device and methods for low speed performance improvement of a lifting surface assembly are disclosed. At least one vortex generator is coupled to the lifting surface assembly, and the vortex generator is extended through the lifting surface assembly by drooping a hinged leading coupled to the lifting surface assembly to increase lift. The vortex generator is retracted inside the lifting surface assembly to decrease drag.
    Type: Grant
    Filed: July 5, 2011
    Date of Patent: February 25, 2014
    Assignee: The Boeing Company
    Inventors: Bruce R. Fox, Stephen J. Fox
  • Patent number: 8657236
    Abstract: Aircraft are provided with a perforated blade seal at the lower and/or upper side edges of a control surface contour, such as a flap, with the purpose of acting as a vortex generator, thereby making it difficult for the lower vortex system to move upwards and merge with the upper vortex system. The perforated blade seals are preferably arranged on the inboard and outboard edges of high lift flaps.
    Type: Grant
    Filed: March 27, 2008
    Date of Patent: February 25, 2014
    Assignee: Embraer S.A.
    Inventors: Mário Trichês, Jr., Micael Gianini Valle do Carmo, Bruno Arantes Caldeira da Silva, Marcus Vinicius Franca Barboza, Vinicius Losada Gouveia
  • Patent number: 8656957
    Abstract: Devices for generating streamwise vorticity in a boundary includes various forms of vortex generators. One form of a split-ramp vortex generator includes a first ramp element and a second ramp element with front ends and back ends, ramp surfaces extending between the front ends and the back ends, and vertical surfaces extending between the front ends and the back ends adjacent the ramp surfaces. A flow channel is between the first ramp element and the second ramp element. The back ends of the ramp elements have a height greater than a height of the front ends, and the front ends of the ramp elements have a width greater than a width of the back ends.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: February 25, 2014
    Assignee: The Board of Trustees of the University of Illinois
    Inventors: Holger Babinsky, Eric Loth, Sang Lee
  • Patent number: 8651426
    Abstract: Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: February 18, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Romuald Morvant, Kevin M Britchford
  • Publication number: 20130299643
    Abstract: A vortex generation apparatus including a vortex generator that deploys in response to deployment of a wing leading edge lift augmentation device. The vortex generator deploys into a position to generate vortices over a main wing body upper surface region trailing the vortex generator.
    Type: Application
    Filed: May 8, 2012
    Publication date: November 14, 2013
    Applicant: Lockheed Martin Corporation
    Inventor: Kenneth M. Dorsett
  • Patent number: 8528601
    Abstract: Sub-boundary-layer-scale ramp-like vortex generators that can be mounted on any surface such as the wing of an airplane, the inlet to a propulsion system, the hull of a ship, or any other surface over which a fluid moves, when the objective is to minimize drag, irreversibility losses, or other performance penalties that can occur for reasons such as boundary layer separation or other undesirable boundary layer properties. The disclosed devices acts to passively induce streamwise vortices in the boundary layer, thereby transferring high-momentum fluid toward the surface in such a way as to alter the shape of the velocity profile within the boundary layer and thereby avoid or delay separation or alter other properties of the boundary layer.
    Type: Grant
    Filed: March 29, 2010
    Date of Patent: September 10, 2013
    Assignee: The Regents of The University of Michigan
    Inventors: Werner J. A. Dahm, Andrew P. Lapsa
  • Patent number: 8453974
    Abstract: The present disclosure relates to flow channels comprising a channel length having a first portion approximately parallel to the maximum waterline thickness location of a body and at least a second portion non-parallel thereto, a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of the surface of the body, and at least a portion of the free edge being arcuate. A method comprises providing the fluid channel attachable to a body, modifying resultant vortices and reducing or minimizing shock formations or separation regions of the freestream.
    Type: Grant
    Filed: December 13, 2010
    Date of Patent: June 4, 2013
    Assignee: The Boeing Company
    Inventor: Gregory G. Thumann
  • Patent number: 8444092
    Abstract: Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at least a part of the surface, and wherein the riblet topography is coated with at least one coating sufficiently designed and applied to preserve the riblet topography. In an embodiment, the multiplicity of adjacent permanently rolled longitudinal riblets results in a friction-reducing textured surface. In an embodiment, metal product is used in fabricating at least a portion of an aircraft. In an embodiment, metal product is used in fabricating at least a portion of a rotor blade.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: May 21, 2013
    Assignee: Alcoa Inc.
    Inventors: Ming Li, James M. Marinelli, Jiantao Liu, Paul E. Magnusen, Simon Sheu, Markus B. Heinimann, John Liu, Luis Fanor Vega
  • Patent number: 8382040
    Abstract: A wing assembly has a wing and one or more no-bias laminar flow oval diskettes that are fixed on a support structure along the C/L (center of lift) of an airfoil, of an aircraft wing. The benefit of an oval diskette with laminar flow is that it has no speed limitations and it allows an aircraft to clime at a speed that matches its Ground Effect Lift speed which is a 25% performance increase and a 40% reduction in vortex drag with a increase stability that eliminates inertia coupling of high-speed airfoils.
    Type: Grant
    Filed: February 16, 2011
    Date of Patent: February 26, 2013
    Inventor: Terry Wayne Hamilton
  • Patent number: 8328516
    Abstract: A method of assembling a blade extension assembly for use with a wind turbine. The method includes removing a tip end of a tip portion of a rotor blade and coupling a tip wall to the tip portion. The tip wall extends between a first sidewall and a second sidewall and includes a plurality of slots defined therein. A blade extension assembly is coupled to the tip portion.
    Type: Grant
    Filed: September 29, 2009
    Date of Patent: December 11, 2012
    Assignee: General Electric Company
    Inventors: Pedro Luis Benito Santiago, Eugenio Yegro Segovia
  • Patent number: 8186619
    Abstract: A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.
    Type: Grant
    Filed: March 13, 2009
    Date of Patent: May 29, 2012
    Assignee: Airbus Operations SAS
    Inventors: Cyril Bonnaud, Stephanie Dantin, Marjorie Defos, Thierry Fol
  • Patent number: 8181912
    Abstract: An engine pod for an aircraft has one side which features several fin-shaped vortex generators such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases. The first vortex generator lies within a positioning corridor that is situated between two boundary lines. The origin and end points, respectively, of the first boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and 25 degrees and the longitudinal engine pod coordinate X=L/4 and L·?. The origin and end points, respectively, of the second boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and 55 degrees and the longitudinal engine pod coordinate X=L/4 and L·?.
    Type: Grant
    Filed: May 26, 2009
    Date of Patent: May 22, 2012
    Assignee: Airbus Deutschland GmbH
    Inventor: Detlev Schwetzler
  • Patent number: 8172185
    Abstract: In order to establish laminar flow on the attachment line (18) of an aerofoil body, a duct entrance (27) is provided on the leading edge of the aerofoil body for receiving spanwise boundary layer flow BLt. The exit (23) of the duct is located spanwise downstream of the duct entrance (27). The boundary layer flow BLt enters the duct (23) and is discharged downstream. The height of the duct entrance (27) above the leading edge of the aerofoil body is greater than the depth of the boundary layer BLt and thus a fresh laminar boundary layer is established on the outer surface (20) of the duct which propagates spanwise along the surface to rejoin the leading edge of the aerofoil body.
    Type: Grant
    Filed: December 20, 2007
    Date of Patent: May 8, 2012
    Assignee: Gaster Consultants Ltd
    Inventor: Micheal Gaster
  • Patent number: 8118265
    Abstract: Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.
    Type: Grant
    Filed: February 6, 2009
    Date of Patent: February 21, 2012
    Assignee: Embraer S.A.
    Inventor: Marcello do Areal Souto Ferrari
  • Patent number: 8118263
    Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.
    Type: Grant
    Filed: January 10, 2011
    Date of Patent: February 21, 2012
    Assignee: Airbus Operations GmbH
    Inventors: Florent Laporte, Heinz Hansen
  • Patent number: 8087617
    Abstract: A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.
    Type: Grant
    Filed: August 15, 2008
    Date of Patent: January 3, 2012
    Assignee: The Boeing Company
    Inventors: Anthony J. Sclafani, Christopher A. Konings
  • Publication number: 20110272529
    Abstract: A wing assembly has a wing and one or more no-bias laminar flow oval diskettes that are fixed on a support structure along the C/L (center of lift) of an airfoil, of an aircraft wing. The benefit of an oval diskette with laminar flow is that it has no speed limitations and it allows an aircraft to clime at a speed that matches its Ground Effect Lift speed which is a 25% performance increase and a 40% reduction in vortex drag with a increase stability that eliminates inertia coupling of high-speed airfoils.
    Type: Application
    Filed: February 16, 2011
    Publication date: November 10, 2011
    Inventor: Terry Wayne Hamilton
  • Patent number: 8047233
    Abstract: An apparatus for generating vortexes in fluid flow generally adjacent to a surface includes: (a) at least one vortex generating element; and (b) a piezoelectric motor element coupled with the at least one vortex generating element. The piezoelectric motor element responds to a varying voltage signal to move the at least one vortex generating element between a first position extending into the fluid flow an operating distance from the surface and a second position generally flush with the surface.
    Type: Grant
    Filed: November 14, 2007
    Date of Patent: November 1, 2011
    Assignee: The Boeing Company
    Inventor: Dan J. Clingman
  • Patent number: 7997528
    Abstract: Runway length requirement for take-off and landing of an aircraft is reduced by taking advantage of dynamic lift overshoot, and in some cases, dynamic stall. In take-off and landing, the angle of attack is rapidly increased so that the lift coefficient exceeds the maximum predicted by the steady flow lift curve. By increasing the angle of attack at an appropriate rate, the increased lift coefficient can be maintained, without loss of control, until the aircraft touches down in the case of a landing, or until the aircraft can begin a normal climb, in the case of take-off. A low aspect ratio lifting body is preferred because of its more gradual stall behavior, and the potential to use dynamic stall for further deceleration before touchdown. Vortex fences can be oscillated to delay the onset of stall, and, in cruise, to energize the boundary-layer and reduce drag and/or control roll and/or yaw.
    Type: Grant
    Filed: January 16, 2007
    Date of Patent: August 16, 2011
    Assignee: Aereon Corporation
    Inventor: James D. Lang
  • Patent number: 7988092
    Abstract: A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A portion of the support mast of an aircraft engine is located near a hot gas flow being discharged from the engine. The vortex-generating device is positioned on a surface of the support mast. The device generates a vortex which crosses the hot gases and prevents the hot gas flow from reaching a heat sensitive portion of the support mast. This device is adaptable to the operating conditions of an already-built aircraft without any notable increased weight.
    Type: Grant
    Filed: July 10, 2007
    Date of Patent: August 2, 2011
    Assignee: Airbus Operations SAS
    Inventors: Cyril Bonnaud, Arnaud Hormiere
  • Patent number: 7988099
    Abstract: A winglet for an aircraft wing is provided. The winglet has an airflow control arrangement, for example in the form of a trailing edge flap (20) by means of which lift generated by the winglet can be varied. The control arrangement desirably forms part of a manoeuvre load alleviation system (22) for the aircraft.
    Type: Grant
    Filed: June 12, 2002
    Date of Patent: August 2, 2011
    Assignee: Airbus Operations Limited
    Inventor: Robert M Bray
  • Publication number: 20110101168
    Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.
    Type: Application
    Filed: January 10, 2011
    Publication date: May 5, 2011
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Florent LAPORTE, Heinz HANSEN
  • Patent number: 7934686
    Abstract: A vortex ring generator adapted to be associated with a body subjected to fluid flow, the vortex ring generator being adapted to produce a fluid flow in the form of a vortex ring with the fluid flow moving over the body from the vortex ring generator.
    Type: Grant
    Filed: August 2, 2010
    Date of Patent: May 3, 2011
    Assignee: Caitin, Inc.
    Inventor: Jayden David Harman
  • Patent number: 7874523
    Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.
    Type: Grant
    Filed: July 14, 2006
    Date of Patent: January 25, 2011
    Assignee: Airbus Deutschland GmbH
    Inventors: Florent Laporte, Heinz Hansen
  • Patent number: 7866608
    Abstract: A device for controlling a vortex trail generated by an oblong element of an aircraft bearing surface includes a control component arranged on a fixing element of the oblong element and on a bearing surface such that a base of the control component contacts the leading edge of the bearing surface. The control component has a triangular shape, on a plane perpendicular to the longitudinal axis thereof, whose two adjacent sides form flanks interconnected by a rounded edge.
    Type: Grant
    Filed: September 13, 2006
    Date of Patent: January 11, 2011
    Assignee: Airbus France
    Inventor: Olivier Atinault
  • Publication number: 20100294890
    Abstract: A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space.
    Type: Application
    Filed: October 16, 2008
    Publication date: November 25, 2010
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventor: Jerome Journade
  • Patent number: 7815150
    Abstract: Systems and methods are described for controlling flow disturbances emanating from a protrusion, such as a beam propagating device. In one embodiment, a method includes positioning a flow control element at least partially around a base portion of a protrusion, wherein the flow control element includes at least one flow expanding feature. A reduced pressure zone is generated proximate an aft portion of the protrusion by expanding at least a portion of a flowfield. One or more flow disturbances emanating downstream from the protrusion are deflected using the at least one reduced pressure zone.
    Type: Grant
    Filed: August 20, 2007
    Date of Patent: October 19, 2010
    Assignee: The Boeing Company
    Inventors: John C. Vassberg, David T. Yeh, Mark A. DeHaan, Neal A. Harrison, Alan Z. Ullman, Michael W. Traffenstedt
  • Patent number: 7766279
    Abstract: A vortex ring generator adapted to be associated with a body subjected to fluid flow, the vortex ring generator being adapted to produce a fluid flow in the form of a vortex ring with the fluid flow moving over the body from the vortex ring generator.
    Type: Grant
    Filed: October 29, 2007
    Date of Patent: August 3, 2010
    Assignee: NewPax, Inc.
    Inventor: Jayden David Harman
  • Publication number: 20100187366
    Abstract: An airfoil includes a plasma actuation surface integrated onto the airfoil surface. On the airfoil, the plasma actuation surface is configured to provide high-frequency plasma actuation along the plasma actuation surface such that excitation of the vortex flow or shear flow mitigates the vortex flow or the shear flow associated with the airfoil.
    Type: Application
    Filed: January 23, 2009
    Publication date: July 29, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Anurag Gupta, Seyed Gholamali Saddoughi
  • Patent number: RE44548
    Abstract: An open roof construction for a vehicle comprising a roof opening that can be closed by a panel of which at least the rear edge can be pivoted upward and downward. A three-dimensional body is provided on the underside of said panel to influence the air flow, near the rear edge of the panel. The three-dimensional body generates swirls in the air flow over the panel.
    Type: Grant
    Filed: April 4, 2012
    Date of Patent: October 22, 2013
    Assignee: Inalfa Roof Systems Group B.V.
    Inventor: Petrus Gerardus Marie Reivers