Aerodynamic Resistance Reducing Patents (Class 244/130)
  • 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: 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: 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: 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: 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: 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: 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: 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: 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
  • Patent number: 9868543
    Abstract: In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams.
    Type: Grant
    Filed: April 22, 2015
    Date of Patent: January 16, 2018
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Olivier Pautis, Jonathan Blanc
  • Patent number: 9850007
    Abstract: A wing skin, which was secured to a wing structure by a plurality of fasteners extending through the wing skin, is removed from the wing and aligned with a template. Template holes are drilled through the template corresponding to each of the fastener holes of the wing skin. The template is then aligned with a new wing skin, and pilot holes are drilled through the new wing skin corresponding to each of the template holes. The new wing skin is then aligned with the wing structure such that the pilot holes permit access to corresponding fastener holes of the wing structure. A mill bit is then positioned through each pilot hole and aligned with the center of the corresponding consumable bushing in the fastener hole of the wing sub-structure, and the skin pilot holes are milled to form fastener holes in the new wing skin aligned with existing sub-structure.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: December 26, 2017
    Assignee: Kellstrom Defense Aerospace, Inc.
    Inventors: John Burton Kalisz, Joshua Ryan Werner
  • Patent number: 9820369
    Abstract: Embodiments of the invention relate to a method and apparatus for providing high thrust density plasma, and/or high control authority plasma. In specific embodiments, such high thrust density, and/or high control authority, plasma can be at or near atmospheric pressure. Embodiments pertain to a method and apparatus that use electron confinement via one or more magnetic fields, and/or one or more electric fields, in a manner to improve the ionization due to surface plasma actuators. Specific embodiments can improve ionization by several orders of magnitude. This improved ionization can result in a high electric field inside the sheath for the same applied voltage and can result in very high thrust.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: November 14, 2017
    Assignee: University of Florida Research Foundation, Incorporated
    Inventor: Subrata Roy
  • Patent number: 9789956
    Abstract: A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: October 17, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Anat Bordoley, Brian J. Tillotson, Michael Chih-Huan Wang, Dan J. Clingman
  • Patent number: 9777703
    Abstract: A method of retrofitting vortex generators on a wind turbine blade is disclosed, the wind turbine blade being mounted on a wind turbine hub and extending in a longitudinal direction and having a tip end and a root end, the wind turbine blade further comprising a profiled contour including a pressure side and a suction side, as well as a leading edge and a trailing edge with a chord having a chord length extending there between, the profiled contour, when being impacted by an incident airflow, generating a lift. The method comprises identifying a separation line on the suction side of the wind turbine blade, and mounting one or more vortex panels including a first vortex panel comprising at least one vortex generator on the suction side of the wind turbine blade between the separation line and the leading edge of the wind turbine blade.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: October 3, 2017
    Assignee: LM WIND POWER A/S
    Inventor: Jesper Madsen
  • Patent number: 9764823
    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: September 29, 2009
    Date of Patent: September 19, 2017
    Inventor: David Birkenstock
  • Patent number: 9764824
    Abstract: Thermal actuation of riblets is described herein. One disclosed example apparatus includes a riblet defining an aerodynamic surface of a vehicle. The disclosed example apparatus also includes a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: September 19, 2017
    Assignee: The Boeing Company
    Inventor: Weidong Song
  • Patent number: 9765696
    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 pressurised 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: June 10, 2014
    Date of Patent: September 19, 2017
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Jürgen Beier, Gideon Daniel Venter
  • Patent number: 9765700
    Abstract: Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: September 19, 2017
    Assignee: The Boeing Company
    Inventors: Steve G. Mackin, George A. Ludlow
  • Patent number: 9751618
    Abstract: Aerodynamic microstructures having sub-microstructure are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure defining an external surface of a vehicle, and a pattern of sub-microstructures superimposed on the microstructure to convey a representation of an image.
    Type: Grant
    Filed: May 6, 2015
    Date of Patent: September 5, 2017
    Assignee: The Boeing Company
    Inventors: Diane C. Rawlings, Timothy Leroy Williams, James C. McGarvey, James M. Kestner, Alan G. Burg
  • Patent number: 9752559
    Abstract: The present subject matter directed to a rotor blade assembly for a wind turbine having at least one rotatable aerodynamic surface feature configured thereon. The rotor blade assembly includes a body shell including a pressure side surface and a suction side surface extending between a leading edge and a trailing edge. The aerodynamic surface feature is disposed adjacent to the pressure side surface, the suction side surface, and/or both. In addition, the surface feature may have a generally airfoil-shaped cross section. As such, an actuator can be configured at least partially within an internal volume of the surface feature, the actuator being configured to rotate the surface feature relative to the body shell.
    Type: Grant
    Filed: January 17, 2014
    Date of Patent: September 5, 2017
    Assignee: General Electric Company
    Inventors: Stefan Herr, James Robert Tobin
  • Patent number: 9738375
    Abstract: A method and apparatus for forming a winglet formed as a one-piece composite for an aircraft is presented. The winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the winglet. The root region is configured to receive an attachment system for attaching the winglet to a wing of the aircraft.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: August 22, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Philipp Witte, Stanley Warren Stawski, Fedor A. Kleshchev, Joshua William Zarfos, Parth R. Naidu
  • Patent number: 9725156
    Abstract: A fairing for a rotor, the fairing comprising a movable top half-shell, the fairing including a mover device provided with a slideway, the slideway being provided with a stationary portion secured to the head of the rotor, the slideway being provided with a movable portion secured to the top half-shell, the movable portion sliding in elevation along the stationary portion along an axis in elevation, the mover device including a driver device co-operating with the movable portion to move the movable portion in translation relative to the stationary portion from a closed extreme position to an open extreme position, and vice versa.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: August 8, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventor: Robin Moret
  • Patent number: 9709032
    Abstract: An airflow generation device of an embodiment has a main body and a voltage application unit. The main body has a base formed of an insulating material and provided with a first electrode and a second electrode. The voltage application unit generates an airflow by applying voltage between the first electrode and the second electrode. Here, the main body is formed to include a portion which gradually decreases in thickness from a center portion to an end portion.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: July 18, 2017
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Hisashi Matsuda, Kenichi Yamazaki, Motofumi Tanaka, Naohiko Shimura, Masahiro Asayama, Toshiki Osako
  • Patent number: 9695799
    Abstract: A blade comprises a first blade surface, a second blade surface forming the reverse surface of the first blade surface, a primary wind receptor protruding from the front end of the first blade surface in a direction away from the second blade surface and with the back surface formed in a curved shape concave toward the front side in a forward direction, a front edge connected to the front end of the primary wind receptor and the front end of the second blade surface and formed in a curved shape convex toward the forward direction, and a back edge connected to the back end of the first blade surface and the back end of the second blade surface and formed in an acute angle facing the back side of the forward direction.
    Type: Grant
    Filed: July 29, 2013
    Date of Patent: July 4, 2017
    Assignee: GLOBAL TECHNOLOGY INSTITUTE. CO., LTD.
    Inventors: Kunihiko Aihara, Junko Aihara
  • Patent number: 9682735
    Abstract: An aerodynamic unit is attached onto a roof of a road vehicle so that air passes over the unit during forward movement of the road vehicle. The unit has a first end for positioning distal to a rear end of a vehicle roof and a second end for positioning proximal a rear end of a vehicle roof. The unit includes an inclined guide portion which decreases in height in a direction towards the trailing end of the unit. The unit also includes a flow director, which directs air flow to the guide portion, disposed at or near the leading end of the aerodynamic unit. The flow director has a height increasing in a direction from the leading end towards the trailing end. The unit may include vortex generators protruding from the guide portion. A fin may extend along each side of the unit in a direction between the trailing end and the leading end.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: June 20, 2017
    Inventor: Andrew Bacon
  • Patent number: 9677409
    Abstract: The invention provides a fan cowl (11) of an aircraft engine made of a composite material having an optimized structure for withstanding the expected loads and for being able to be manufactured as a monolithic ensemble. The structure comprise a skin (13), frames (15) of a closed cross-section arranged in a transverse direction to the longitudinal axis of the aircraft and longitudinal beams (17, 19) comprising first parts (21) of a closed cross-section to be superimposed to the transverse frames (15) in their crossing zones and second parts (23) of an open cross-section in zones not crossing transverse frames (15) having their webs (41) arranged in a same plane. The invention also refers to a manufacturing method of said fan cowl (11).
    Type: Grant
    Filed: March 4, 2014
    Date of Patent: June 13, 2017
    Assignee: Eads Construcciones Aeronauticas S.A.
    Inventors: Álvaro Ortiz Del Cerro, Joaquín Gallego Pleite, Luis Rubio García, Sofía Ponce Borrero
  • Patent number: 9670901
    Abstract: A wind turbine blade airfoil trailing edge (TE) with a first waveform profile (44B, 44C, 44E) as seen from behind, formed by ruffles or alternating ridges (21) and valleys (22) formed on the airfoil (20) and ending at the trailing edge. The trailing edge may further include a second waveform profile (48B, 48C, 48E) as seen from above, resulting from serrations formed by an oblique termination plane (32B) of the trailing edge or by other geometry. The ridges and/or serrations may be asymmetric (44E, 48E) to increase a stall fence effect of the ridges on the suction side (SS) of the trailing edge. The first and second waveforms may have the same period (44B, 48B) or different periods (44C, 48C).
    Type: Grant
    Filed: March 21, 2014
    Date of Patent: June 6, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: John M. Obrecht, Arni T. Steingrimsson
  • Patent number: 9656761
    Abstract: A lipskin for a nacelle includes a generally annular first lipskin segment that extends generally upstream from a first lipskin edge to a forward edge. The forward edge is proximate to a hilite of the nacelle. The lipskin also includes a generally annular second lipskin segment that extends generally downstream from the forward edge to a second lipskin edge. The second lipskin segment is oriented generally concentrically about the first lipskin segment. The first lipskin segment and the second lipskin segment are coupled together at the forward edge.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: May 23, 2017
    Assignee: The Boeing Company
    Inventors: Alex C. Lumbab, Bradley Scott Leisten