Aerodynamic Resistance Reducing Patents (Class 244/130)
  • 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: 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: 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: 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
  • Patent number: 10315761
    Abstract: In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: June 11, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd
  • Patent number: 10319359
    Abstract: A masking method includes: a step of choosing a generating element which is part of the skin of an aircraft, a first step of measuring a fundamental frequency of a sound signal emitted by the generating element, a step of selecting a masking element which is part of the skin, a second step of measuring a fundamental frequency of another sound signal emitted by the masking element, a step of modification of the structure of the masking element in such a way as to shift the fundamental frequency of the sound signal emitted by the masking element to a frequency lower than the fundamental frequency of the sound signal emitted by the generating element. Such a masking method thus makes it possible to mask the sound signal emitted by the generating element by the sound signal emitted by the masking element.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: June 11, 2019
    Assignee: Airbus Operations S.A.S.
    Inventors: Nicolas Molin, Isabelle Boullet
  • Patent number: 10309311
    Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurized fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: June 4, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Jürgen Beier, Gideon Daniel Venter
  • Patent number: 10259567
    Abstract: A multilayer construction for aerodynamic riblets includes a first layer composed of a material with protuberances, the first layer material exhibiting a first characteristic having long-term durability and a second layer composed of a material, exhibiting a second characteristic with capability for adherence to a surface.
    Type: Grant
    Filed: July 16, 2016
    Date of Patent: April 16, 2019
    Assignee: The Boeing Company
    Inventors: Diane C. Rawlings, Kevin R. Malone
  • Patent number: 10252789
    Abstract: Fluid systems are described. An example fluid system has a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: April 9, 2019
    Assignee: Coflow Jet, LLC
    Inventor: Gecheng Zha
  • Patent number: 10240561
    Abstract: A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: March 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Mark Zsurka
  • Patent number: 10220935
    Abstract: An open-channel stiffener for stiffening a panel has a bonding flange for bonding the stiffener to the panel through a bondline formed between the bonding flange and the panel to form a stiffened panel. The open-channel stiffener has a cross-sectional shape that aligns, or substantially aligns, a shear center of the stiffener with a centroid of the stiffener and aligns the shear center proximate an edge of the bondline, and removes the need for a radius filler noodle. A plurality of perforations may be formed through the bonding flange to permit an adhesive to wick into the perforations and create a mechanical interlock between the bonding flange and the panel.
    Type: Grant
    Filed: September 13, 2016
    Date of Patent: March 5, 2019
    Assignee: The Boeing Company
    Inventors: Lyle R. Deobald, Matthew A. Dilligan, Aaron N. Rinn, Madhavadas Ramnath
  • Patent number: 10173238
    Abstract: An applicator for application onto and embossing microprofiling of a fluidic medium on a substrate, in particular in the aerospace sector, and a corresponding application device having such an applicator. The applicator has a circumferentially moving die that has an embossing profile, a press for the die and a stabilizing device, in particular a hardening device, for the applied medium. In addition, the applicator has a hollow support body, surrounded by the die at a distance forming a gap, the press being arranged in the gap. The application device has, in addition to the applicator, a handling device for a relative movement between the applicator and a workpiece.
    Type: Grant
    Filed: October 7, 2016
    Date of Patent: January 8, 2019
    Assignee: Airbus Operations GmbH
    Inventors: Thomas Sturm, Helmut Huber
  • Patent number: 10150557
    Abstract: A transition piece, which can be mounted in a recess, and which can form a continuous surface from a structural component of an airplane to a control surface, which is connected to the structural component in a pivotable manner is described. The transition piece can be mounted between an edge of the structural component and a lateral edge of the control surface such that the transition piece is fastened in a pivotable manner both to the edge of the structural component and to the lateral edge of the control surface. According to an example, the transition piece has a planar design and can be deformed within said plane, that is, the transition piece can be stretched or compressed within this plane.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: December 11, 2018
    Assignee: Airbus Defence and Space GmbH
    Inventor: Luiz Da Rocha-Schmidt
  • Patent number: 10139209
    Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization and methods of operating the flow control system. Various embodiments of the flow control system of the present invention involve flow sensors, active flow control device or activatable flow effectors and/or logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: November 27, 2018
    Assignee: Orbital Research Inc.
    Inventors: Troy S Prince, Richard Kolacinski, Mehul Patel
  • Patent number: 10124840
    Abstract: An air-drag reduction mechanism for a vehicle is provided. The mechanism includes a shell structured to be deployable in a direction away from a vehicle, the shell including a plurality of telescoping shell segments. The shell segments are structured to form a shell having a shape which tapers or narrows in a direction away from the vehicle. The air-drag reduction mechanism may be incorporated into an air-drag reduction system including an actuation mechanism operatively coupled to the telescoping shell and operable to deploy the shell.
    Type: Grant
    Filed: October 20, 2016
    Date of Patent: November 13, 2018
    Assignee: Toyota Motor Engineering & Manufacturing North America, Inc.
    Inventors: Umesh N. Gandhi, Yasuo Uehara, Danil V. Prokhorov
  • Patent number: 10086927
    Abstract: A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: October 2, 2018
    Assignee: The Boeing Company
    Inventors: Arvin Shmilovich, Edward Andrew Whalen
  • Patent number: 10087839
    Abstract: An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.
    Type: Grant
    Filed: February 24, 2016
    Date of Patent: October 2, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Francois Bisson, Mark Cunningham, Michel Desjardins, Guo Rong Yan
  • Patent number: 10077113
    Abstract: An aircraft propulsion engine including a fan case, and a cowl forming part of the nacelle of the engine and being designed to at least partially surround the case leaving a space between the cowl and the case, in which space at least one piece of equipment is mounted and extends along the axis of the engine, is provided. The cowl includes a wall and wall stiffeners fixed to the internal face of the wall. At least a part of the stiffeners of the cowl is arranged to form air guide ducts, the air guide ducts being assembled into an air distribution circuit to ventilate the equipment.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: September 18, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Tewfik Boudebiza, Frederic Eichstadt, Marc Tesniere
  • Patent number: 10035586
    Abstract: An aircraft wing assembly including: a wing having a wing box structure with an upper wing cover and a lower wing cover, and a wing tip device attached to the outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm, a seal assembly aerodynamically seals the gap, wherein the seal assembly includes a bridging component on an interior side of the gap, and a seal which fills the gap and is supported by the bridging component.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: July 31, 2018
    Assignee: Airbus Operations Limited
    Inventors: Huw Davies, Nigel McKenna
  • Patent number: 10005530
    Abstract: The invention relates to a device for reducing the driving power requirement of a watercraft, comprising a flow guiding surface from which at least one first fin projects. A first end of said first fin is fixed to the flow guiding surface, and a second end of the first fin is embodied as a free end.
    Type: Grant
    Filed: March 31, 2014
    Date of Patent: June 26, 2018
    Assignee: becker marine systems GmbH & Co. KG
    Inventors: Dirk Lehmann, Friedrich Mewis
  • Patent number: 9994297
    Abstract: A panel (3) for controlling the aerodynamic phenomena generated by a body (0) to be positioned on a surface of an aircraft (V). The panel (3) can be associated with the base of the body (0) and includes at least one inlet aperture (322) and at least one outlet aperture (322?) placed in communication with each other, through which a portion of a fluid flow (W) in which the body (0) is immersed can selectively pass. The inlet aperture (322) is located upstream of the body (0) and the outlet aperture (322?) is located downstream of the body (0), with respect to the direction of the fluid flow (W).
    Type: Grant
    Filed: August 30, 2013
    Date of Patent: June 12, 2018
    Assignee: ALENIA AERMACCHI S.P.A.
    Inventor: Danilo Marchetti
  • Patent number: 9994301
    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: November 18, 2013
    Date of Patent: June 12, 2018
    Assignee: ROHR, INC.
    Inventors: Teresa M. Kruckenberg, Vijay V. Pujar, Robert L. Braden
  • Patent number: 9975625
    Abstract: A method and apparatus may comprise a first number of layers of a flexible material, a second number of layers of a dielectric material, a first electrode attached to a surface layer in the first number of layers, and a second electrode attached to a second layer in one of the first number of layers and the second number of layers. The first number of layers may be interspersed with the second number of layers. The first electrode may be configured to be exposed to air. The first electrode and the second electrode may be configured to form a plasma in response to a voltage.
    Type: Grant
    Filed: April 19, 2010
    Date of Patent: May 22, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Joseph Steven Silkey, David James Suiter, Bradley Alan Osborne
  • Patent number: 9975623
    Abstract: An elastomeric transition for spanning a gap between first and second surfaces on an aircraft includes an elastomeric skin. A first skin edge is configured for attachment to the first surface and a second skin edge is configured for attachment to the second surface. The elastomeric skin has a longitudinal dimension, coincident with the gap, which is significantly longer than a distance between laterally corresponding points on the first and second skin edges. At least one continuous rod is coupled at one end to a selected first point on the first surface and at another end to a selected second point, spaced apart from the first point, on the second surface. The at least one continuous rod is configured in the elastomeric transition to run along the gap such that the rod extends at an acute angle in relation to both the first and second skin edges.
    Type: Grant
    Filed: March 8, 2016
    Date of Patent: May 22, 2018
    Assignee: Northrop Grumman Systems Corporation
    Inventor: Allen A. Arata
  • Patent number: 9950803
    Abstract: Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: April 24, 2018
    Assignees: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE, COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD.
    Inventors: Zhehui Yu, Miao Zhang, Meihong Zhang, Fei Xue, Tiejun Liu, Dongyun Zhang, Junhong Wang, Pan Cheng, Yong Lu, Xiaoyan Liu
  • Patent number: 9920740
    Abstract: A wind turbine rotor blade element includes a first portion and a second portion connected to each other is described. The first portion includes a rear surface for facing a surface of a wind turbine rotor blade and the second portion includes a top surface which includes an angle between 90° and 180° with the rear surface of the first portion.
    Type: Grant
    Filed: January 18, 2012
    Date of Patent: March 20, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Peder Bay Enevoldsen, Jens Jørgen Østergaard Kristensen, Jason Stege, Carsten Thrue
  • Patent number: 9914525
    Abstract: A rotorcraft provided on top with a waterdrop-shaped fairing arranged below the rotary wing of a main rotor of the rotorcraft and overlying a cover covering a power plant of the rotorcraft. The trailing edge(s) of the fairing is/are provided with a respective movable member guiding a first stream of air flowing along the fairing and escaping from the trailing edge towards the rear of the rotorcraft in flight. By way of example, the movable member is arranged as a flap or as a bladed roller that may potentially be motor-driven as a function of the effects of the first stream of air on the behavior of the rotorcraft in flight.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: March 13, 2018
    Assignee: AIRBUS HELICOPTERS
    Inventor: David Alfano
  • Patent number: 9908631
    Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: March 6, 2018
    Assignee: EMBRAER S.A.
    Inventors: Luis Gustavo Trapp, Israel Da Silva, Murilo Mestriner, Murilo Pinto Ribeiro
  • Patent number: 9890765
    Abstract: Various air deflector shapes, sizes and configurations for use in a load compensating device on an airfoil are provided. The air deflector arrangements are configured to alter the airflow around the air deflector in order to affect sound or acoustics associated with the air deflector when deployed during operation. Some example configurations that may alter the air flow around the air deflector include air deflectors having a plurality of apertures, air deflectors including a scalloped edge, and/or air deflectors including a plurality of protrusions extending from a portion of the air deflector.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: February 13, 2018
    Assignee: GE Infrastructure Technology, LLC
    Inventors: Qing Tian, Jehan Z. Khan, Jonathon P. Baker
  • Patent number: 9884677
    Abstract: A natural-laminar-flow swept transonic wing fitted with a wing tip pod for controlling the location of a wing shock in the wing tip region, such that the shock extends outboard substantially up to the wing tip without substantially sweeping forward toward the wing tip leading edge.
    Type: Grant
    Filed: March 20, 2012
    Date of Patent: February 6, 2018
    Assignee: Airbus Operations Limited
    Inventors: Robert Northam, Neil Lyons
  • Patent number: 9873467
    Abstract: The fairing assembly uses inflatable wall panels that automatically deploy and retract at certain speeds to provide sturdy, light-weight aerodynamic fairings, which cover and enclose the space between the tractor truck and connected trailers to improve the aerodynamics of the tractor-trailers. The fairing assembly uses a module design and includes two or more panel units, a blower/vacuum and an electronic controller. Each panel unit includes a panel housing and an inflatable wall panel, which inflates and deflates to deploy and retract from its housing. The controller actuates the blower/vacuum to provide a continuous flow of air to the inflatable wall panels during deployment and to draw an air flow from the inflatable wall panels when retracting the panels back into the panel housings.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: January 23, 2018
    Assignee: Wall Global, LLC.
    Inventor: Billy Russell Wall, II