With Lift Modification Patents (Class 244/198)
  • Patent number: 10954916
    Abstract: The invention relates to a wind turbine blade having integrated thermoplastic anchoring sites for attachment of surface mounted devices, a method for producing such blade and a wind turbine equipped with such blade.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: March 23, 2021
    Assignee: LM WP PATENT HOLDING A/S
    Inventor: Michael Drachmann Haag
  • Patent number: 10882606
    Abstract: An aerodynamic device for enhancing lift and reducing drag on a body, comprising a plurality of raised members, each having a symmetric profile and including a central portion having an elongated profile, and first and second outer portions having elongated profiles and arranged substantially parallel to and on opposing sides of the central portion, wherein the plurality of raised members are situated adjacent one another to form a continuous structure on or defining at least a portion of a surface of the body and oriented such that the raised members are substantially aligned with a direction of localized flow on the body. An aerodynamic device for enhancing lift and reducing drag of a flying disc, wherein the plurality of raised members are situated adjacent one another to form a continuous structure and the raised members are oriented in a substantially circumferential direction on the surface of the flying disc.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: January 5, 2021
    Assignees: President and Fellows of Harvard College, University of South Carolina
    Inventors: Katia Bertoldi, August G. Domel, George V. Lauder, Mehdi Saadat, Hossein Haj-Hariri
  • Patent number: 10852111
    Abstract: Pressure relief holes are sized and positioned on each fin of a projectile to allow high pressure from one side of the fin due to canard and fin interaction to bleed to a low pressure area on the opposite side of the fin. The location of the pressure relief holes target pressure differences due to canard roll control downwash while not affecting pressure differences due to projectile attitude. The fin planform area remains small enough to meet packaging and fire requirements for this type of munition and large enough to aerodynamically stabilize the airframe thereby enabling a more robust pitch and yaw autopilot design.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: December 1, 2020
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Thomas Recchia, Yin Chen, Mitchell Stolk, David Hosier, Sarah Hunt
  • Patent number: 10800539
    Abstract: A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.
    Type: Grant
    Filed: August 19, 2016
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Randy M. Vondrell, Brandon Wayne Miller, Patrick Michael Marrinan, Lawrence Chih-hui Cheung, Nikolai N. Pastouchenko
  • Patent number: 10767623
    Abstract: A rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The rotor blade assembly also includes at least one noise reducer secured at the trailing edge. The noise reducer(s) includes at least one serration having a base portion and at least one side edge feature extending from the base portion. Further, the base portion extends along a first plane. The side edge feature(s) extends out of the first plane so as to reduce vortices generated by the serration(s).
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: September 8, 2020
    Assignee: General Electric Company
    Inventors: Guannan Wang, Benoit Philippe Armand Petijean, Roger Drobietz
  • Patent number: 10746156
    Abstract: The invention relates to a method for producing or designing a leading edge of a lifting structure, wherein starting at the midpoint of the base (0,0), a curve is applied to the profile of the structure, the length “L1” of which is according to the maximum thickness of the NACA section in the base of the profile “H0” in the base and is defined by the equation L1=0.0510H02?0.0790H0+15.5790, and the maximum height of which on the “x”-axis is located at point “L1/2” and defined by means of the relationship x=0.0137(L1)1.4944, the shape of said curve being defined by means of the equation: (y?y0)=0.0000000107x6+0.0000016382x5?0.0000794412x4+0.0010194142x3+0.0097205322x2+0.0136993913x, and the rest of the curve being calculated by means of an iterative process according to the above.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: August 18, 2020
    Assignee: FUNDACIÓN AZTI—AZTI FUNDAZIOA
    Inventors: Guzmán Díez Díez, Gorka Gabiña Iribar
  • Patent number: 10726172
    Abstract: Systems and methods for tailoring fluid and energy interaction through surface texturing. The methods comprise: receiving behavior input data specifying known or modeled interactions between a material and pre-solved solution surfaces, discrete input data specifying parameters of a surface to be textured, and continuous input data specifying ranges of values for environmental characteristics that the surface is to be subjected to during use; transforming the behavior input data into a composite response surface comprising a weighted combination of the pre-solved solution surfaces generated based on the discrete input data and the continuous input data; determining an optimized surface texture for the surface based on the composite response surface and desired behavior data specifying a desired interaction between the material and the surface to be textured; and outputting the optimized surface texture (e.g., to a surface texturing machine) so that the optimized surface texture is applied to the surface.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: July 28, 2020
    Assignee: HARRIS CORPORATION
    Inventors: Christopher A. Corey, Erin K. Sharma
  • Patent number: 10480789
    Abstract: Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: November 19, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Osami Yokota, Shohei Numata, Tomomi Koganezawa, Tetsuma Tatsumi
  • Patent number: 10393156
    Abstract: A method of controlling a fluid flow using momentum and/or vorticity injections. Actively controlling an actuator allows for direct, precise, and independent control of the momentum and swirl entering into the fluid system. The perturbations are added to the flow field in a systematic mater providing tunable control input, thereby modifying behavior thereof in a predictable manner to improve the flow characteristics.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: August 27, 2019
    Assignee: The Florida State University Research Foundation, Inc.
    Inventors: Kunihiko Taira, Farrukh Alvi, Phillip Munday
  • Patent number: 10358931
    Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Chaitanya Paruchuri, Philip Joseph, Jae-Wook Kim
  • Patent number: 10330077
    Abstract: A vortex generator for a wind turbine blade to be mounted to a wind turbine blade includes: a platform portion to be mounted to a surface of the wind turbine blade; and at least one fin disposed upright on the platform portion. The platform portion has a cross section having a curved convex shape, at least along a blade spanwise direction of the wind turbine blade.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: June 25, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Koji Fukami
  • Patent number: 10259566
    Abstract: An aircraft includes an elongated wing having a leading edge extending to a trailing edge, an upper surface extending from the leading edge to the trailing edge, and a lower surface extending from the leading edge to the trailing edge; an air passage forming an entrance opening at the leading edge and configured to extend to an exit opening positioned at the upper surface; and an airflow stop configured to control airflow movement through the air passage.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: April 16, 2019
    Inventor: James Randolph Lawrence
  • Patent number: 10240576
    Abstract: A wind turbine blade includes a trailing edge including a radially inboard portion and a radially outboard portion opposite the radially inboard portion. The trailing edge further includes at least one serrated portion extending at least partially between the radially inboard portion and the radially outboard portion. The serrated portion includes at least one substantially acoustically absorbent material.
    Type: Grant
    Filed: November 25, 2015
    Date of Patent: March 26, 2019
    Assignee: General Electric Company
    Inventors: Lorenz Edwin Drack, Thierry Pascal Maeder, Roger Drobietz
  • Patent number: 10227128
    Abstract: The invention provides an aircraft wing, comprising a fixed wing and a wing tip device at the tip. The wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device in the locked flight configuration. A rotatable locking member is associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other. The rotatable locking member comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin is urged toward the rotation axis of the rotatable locking member by a camming action of the guide surface on the locking pin, thereby preloading the locking mechanism.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: March 12, 2019
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Chetan Korya, Anthony Bryant, Matt Harding, David Brakes
  • Patent number: 10151325
    Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: December 11, 2018
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, Manjunath Bangalore Chengappa, Pradeep Patel
  • Patent number: 10137978
    Abstract: The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: November 27, 2018
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Matt Harding
  • Patent number: 10138868
    Abstract: A method for calculating a trailing edge that is to be produced for a rotor blade of an aerodynamic rotor of a wind power installation, wherein the rotor blade has radial positions with respect to the rotor, the rotor blade has a local blade profile that is a function of the radial positions with respect to the rotor and the trailing edge has a jagged profile having a plurality of spikes, wherein each spike has a spike height and a spike width, and the spike height and/or the spike width is calculated as a function of the radial position thereof and/or as a function of the local blade profile of the radial position thereof.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: November 27, 2018
    Assignee: Wobben Properties GmbH
    Inventors: Andree Altmikus, Mohammad Kamruzzaman
  • Patent number: 10106251
    Abstract: A rotor blade system includes a rotor blade having an outboard section and an inboard section, a hinge joint rigidly attached to the outboard section, and an adhedral tip engaged with the hinge joint. A method includes pivotally attaching an adhedral tip to the rotor blade and pivoting the adhedral tip during flight to change the flight performance characteristics of the blade during flight.
    Type: Grant
    Filed: September 15, 2014
    Date of Patent: October 23, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Christopher Foskey, Frank B. Stamps
  • Patent number: 10093411
    Abstract: An apparatus and method using an interference body to shape a sonic boom signature is provided herein. The interference body can be installed on various control surfaces, including a vertical control surface. The interference body can be sized and positioned to create a desired amount of interference with expansion wave s generated by one or more components of an aircraft. In one configuration, the interference body can be operative to reduce the sonic boom formed by an aircraft operating at or above supersonic speeds.
    Type: Grant
    Filed: March 18, 2014
    Date of Patent: October 9, 2018
    Assignee: The Boeing Company
    Inventors: Eric E. Adamson, David A. Treiber
  • Patent number: 10087912
    Abstract: Universal vortex generators for wind turbine rotor blades and methods of manufacturing same are disclosed. The vortex generator includes a base portion configured for attachment to at least one of a suction side surface or a pressure side surface of the rotor blade and at least one airflow modifying element extending from the base portion. In addition, the airflow modifying element includes one or more discontinuities configured therein so as to increase flexibility of the vortex generator.
    Type: Grant
    Filed: January 30, 2015
    Date of Patent: October 2, 2018
    Assignee: General Electric Company
    Inventors: James Robert Tobin, Stefan Herr, Scott Gabell Riddell, Michael Christopher Booth
  • Patent number: 10072511
    Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: September 11, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Roy D. Fulayter, Crawford F. Smith
  • Patent number: 10011346
    Abstract: Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 3, 2018
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Gur Kimchi, Allan Ko
  • Patent number: 9995166
    Abstract: A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion.
    Type: Grant
    Filed: November 21, 2014
    Date of Patent: June 12, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Thomas William Vandeputte
  • Patent number: 9989078
    Abstract: The present invention includes a method of controlling a fluid flow using momentum and/or vorticity injections. Actively controlling an actuator allows for direct, precise, and independent control of the momentum and swirl entering into the fluid system. The perturbations are added to the flow field in a systematic mater providing tunable control input, thereby modifying behavior thereof in a predictable manner to improve the flow characteristics.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: June 5, 2018
    Assignee: The Florida State University Research Foundation, Inc.
    Inventors: Kunihiko Taira, Farrukh Alvi, Phillip Munday
  • Patent number: 9943731
    Abstract: A flying toy for throwing and/or catching includes an elongated body forming a fuselage. The body extends along a longitudinal axis from a front end to a rear end. A lift-generating wing is non-movably attached in relation to the body. A horizontal stabilizer is disposed at or near the rear end of the body, where the horizontal stabilizer disposed behind the lift-generating wing. A vertical stabilizer is disposed at or near the rear end of the body, where the vertical stabilizer is disposed behind the lift-generating wing. A push surface is attached to the body and extends perpendicular in relation to the longitudinal axis. The push surface faces towards the rear end of the body. The push surface allows a user to push the flying toy forward when thrown.
    Type: Grant
    Filed: September 5, 2017
    Date of Patent: April 17, 2018
    Inventor: Marc Gregory Martino
  • Patent number: 9896193
    Abstract: An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.
    Type: Grant
    Filed: February 17, 2009
    Date of Patent: February 20, 2018
    Assignee: Airbus Operations Limited
    Inventor: Norman Wood
  • Patent number: 9890764
    Abstract: A trailing edge protective cap for a rotor blade of a wind turbine and method of manufacturing same is disclosed. The method includes infusing a first material onto a first mold so as to form a first part having a length. While the first part is still in the first mold, the method may also include placing a second mold onto the first part. The method may then include infusing a second material onto the second mold and at least a portion of the first part so as to form a second part having a length. The first and second parts may then be joined or infused together along a portion their respective lengths so as to form the protective cap, wherein the protective cap includes a joined section and an open section.
    Type: Grant
    Filed: March 26, 2014
    Date of Patent: February 13, 2018
    Assignee: General Electric Company
    Inventors: Sujan Kumar Pal, Wilfred A. A. W.
  • Patent number: 9890792
    Abstract: The invention relates to a vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).
    Type: Grant
    Filed: March 25, 2014
    Date of Patent: February 13, 2018
    Assignee: TURBOMECA
    Inventors: Laurent Tarnowski, Nicolas Pascal Bulot
  • Patent number: 9816537
    Abstract: A rotary actuator includes a housing, a rotor assembly rotatably journaled in said housing and including a rotary output shaft, a central actuation assembly including a central mounting point formed in an external surface of the rotary output shaft, said central mounting point proximal to the longitudinal midpoint of the rotary output shaft, a mounting assembly adapted for attachment to an external mounting connector of a mounting surface of an aircraft structural member, and an actuation arm removably attached at a proximal end to the central mounting point, said actuation arm adapted at a distal end for attachment to an external mounting feature of an aircraft assembly to be actuated.
    Type: Grant
    Filed: June 19, 2013
    Date of Patent: November 14, 2017
    Assignee: Woodward, Inc.
    Inventors: Joseph H. Kim, Robert P. O'Hara, Shahbaz H. Hydari, Pawel A. Sobolewski
  • Patent number: 9782636
    Abstract: A throwing or catching toy includes a generally elongated spheroidal body defined as having a longitudinal axis, where a length of the body along the longitudinal axis between a front end to a back end of the body is longer than an equatorial diameter. A support is attached to the body and extends beyond the back end of the body and does not extend beyond the front end of the body. A lift-generating wing is non-movably attached to the support. A push surface is disposed near the back end of the body, where the push surface is generally perpendicular to the longitudinal axis. A horizontal stabilizer is attached to the support and disposed behind the lift-generating wing. An impact transfer surface is attached directly to the support, where the impact transfer surface is disposed within the body and fixed between the front end of the body and the support.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: October 10, 2017
    Inventor: Marc Gregory Martino
  • Patent number: 9719466
    Abstract: A system and method for providing reverse thrust is disclosed. The system can include one or more cascade elements. The one or more cascade elements can each include a plurality of vanes to redirect engine thrust in a forward direction relative to travel. Some, or all, of the vanes can include raised geometric patterns configured to increase the mixing of the airstreams between the reversed engine thrust and the airstream over the vehicle to reduce noise and improve reverse thrust. The angle, curvature, and geometric pattern of the vanes can be optimized for a particular cascade element, engine, location on the engine, row, or can be optimized individually to maximize reverse thrust and minimize noise.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: August 1, 2017
    Assignee: The Boeing Company
    Inventor: Omid B. Nakhjavani
  • Patent number: 9719488
    Abstract: An arrangement to reduce noise of a wind turbine rotor blade is provided, including a wind turbine rotor blade and a noise reduction device. The noise reduction device includes a serrated extension for at least reducing noise generated from the wind turbine rotor blade, the noise reduction device attached to the trailing edge section. The serrated extension has a number of first and second teeth. The designs of the first and second teeth are differently compared to each other such that suction side noise and pressure side noise are both reduced by the teeth of the serrated extension. Advantageously, the first teeth and the second teeth are arranged in an alternating, periodic pattern and differ from each other by an angle of inclination with regard to a trailing edge streamline and or by its planform shape. Furthermore, a method to reduce noise of a wind turbine rotor blade is provided.
    Type: Grant
    Filed: August 11, 2014
    Date of Patent: August 1, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventor: Stefan Oerlemans
  • Patent number: 9638164
    Abstract: In one aspect, a rotor blade assembly for a wind turbine may generally include a rotor blade extending lengthwise between a root and a tip. The rotor blade may include a pressure side and a suction side extending between a leading edge and a trailing edge. Additionally, the rotor blade assembly may include a chord extender having an attachment portion coupled to at least of the pressure side or the suction side and an extension portion extending outwardly from the attachment portion beyond the trailing edge. The extension portion may extend chordwise between a first end disposed adjacent to the trailing edge and a second end disposed opposite the first end. The extension portion may include a surface defined between the first and second ends. The extension portion may further include at least one stiffening rib projecting outwardly from the surface.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: May 2, 2017
    Assignee: General Electric Company
    Inventors: Ramesh Vedula, Kunal Upendra Sakekar, Jonathan Glenn Luedke, Stefan Herr, Scott Gabell Riddell, Michael Christopher Booth
  • Patent number: 9605649
    Abstract: A wind turbine rotor blade has a longitudinal axis, a blade root, a blade tip, a pressure side, a suction side and an aerodynamic profile which, in a longitudinal section of the rotor blade, has a profile chord and a thick trailing edge. The rotor blade includes a multiplicity of flow deflection elements which are arranged on the thick trailing edge and have respective inflow surfaces which are shaped and arranged such that a radial flow running in the direction from the blade root toward the blade tip is diverted by the inflow surface in the direction of the profile chord.
    Type: Grant
    Filed: June 28, 2013
    Date of Patent: March 28, 2017
    Assignee: Nordex Energy GmbH
    Inventor: Doosttalab Mehdi
  • Patent number: 9586677
    Abstract: For establishment of a laminar attachment line flow, an aircraft wing includes a leading edge including an attachment line, where air impinging on the region flows in a boundary layer spanwise along the leading edge. The leading edge and the attachment line are at least partially formed at first and second slats. The second slat is located adjacent to the first slat in the downstream direction of the attachment line flow, so that the leading edge includes a slat-to-slat junction, where a slat cavity is formed. A duct has a duct entrance at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing. The duct entrance extends around the leading edge and over the range of positions of the attachment line at the slat-to-slat junction.
    Type: Grant
    Filed: August 6, 2013
    Date of Patent: March 7, 2017
    Assignee: AIRBUSGROUP LIMITED
    Inventor: Stephen Rolston
  • Patent number: 9588011
    Abstract: Exemplary practice of the present invention provides and implements a superior small-scale test model of a full-scale vessel hull describing a smooth axisymmetric body. The boundary layer of a smooth axisymmetric body moving in water is characterized, in succession from front axial-longitudinal end to back axial-longitudinal end, by a laminar region, an unstable region, an intermittent region, and a turbulent region. The smooth axisymmetric body's intermittent region is characterized by generation of turbulent spots, which bring about the turbulent region. According to exemplary inventive practice, a “turbulent spot inducer” (ring-shaped structure or structural arrangement) is strategically sized and placed to increase generation of turbulent spots, thereby reducing (axially-longitudinally shortening) the intermittent region and enlarging (axially-longitudinally lengthening) the turbulent region.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: March 7, 2017
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Young T. Shen, Michael J. Hughes
  • Patent number: 9581133
    Abstract: The present disclosure relates to a wind turbine blade, in particular a wind turbine blade having devices or structures for reducing noise generated by the wind turbine blade during use and related method. The wind turbine blade comprises at least a first longitudinal section having a cross section perpendicularly to a longitudinal direction, the cross section having a plurality of flow modulating devices including a first primary flow modulating device and a secondary flow modulating device for modulating noise spectra, wherein the first primary flow modulating device and the first secondary flow modulating device are spaced perpendicularly to the longitudinal direction. Also disclosed is a method of retrofitting a wind turbine blade.
    Type: Grant
    Filed: May 14, 2012
    Date of Patent: February 28, 2017
    Assignee: LM WINDPOWER A/S
    Inventor: Qingshan Yao
  • Patent number: 9574544
    Abstract: Methods of manufacturing rotor blade components for a wind turbine and rotor blade components produced in accordance with such methods are disclosed. In one embodiment, the method generally includes providing a mold of the rotor blade component; coating at least a portion of an interior surface of the mold with an elastomeric material; inserting a foam material within the mold; and, removing the rotor blade component from the mold, wherein the elastomeric material forms a cover skin around at least a portion of the rotor blade component. In an alternative embodiment, the method includes providing at least one support member defining a profile for the rotor blade component on a mold surface; coating at least a portion of the support member with an elastomeric material; and, allowing the elastomeric material to cure on the mold surface so as to form the rotor blade component.
    Type: Grant
    Filed: December 16, 2013
    Date of Patent: February 21, 2017
    Assignee: General Electric Company
    Inventors: James Robert Tobin, William Max Gobeli, Christopher Daniel Caruso
  • Patent number: 9567980
    Abstract: An arrangement for reducing noise which is generated by a wind turbine blade is provided. The wind turbine blade has a first panel and a second panel. The first and the second panel are arranged at a trailing edge of the wind turbine blade, wherein the first panel is adjacent to the second panel. The first panel includes a first transition zone and the second panel includes a second transition zone. The first transition zone and the second transition zone are engaged in a way that whistle tones produced by a gap of the wind turbine blade, the gap being located between the first panel and the second panel, is reduced or even avoided.
    Type: Grant
    Filed: February 7, 2013
    Date of Patent: February 14, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Jens Jørgen Østergaard Kristensen
  • Patent number: 9555874
    Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.
    Type: Grant
    Filed: May 15, 2015
    Date of Patent: January 31, 2017
    Assignees: Airbus Operations GmbH, Airbus Operations Ltd.
    Inventors: Gerd Heller, Alexander Buescher, Frank Theurich, Tom Gibson, Michael Karwin, Stephen Powell
  • Patent number: 9463870
    Abstract: An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock (9) so as to reduce its angle of sweep.
    Type: Grant
    Filed: February 17, 2009
    Date of Patent: October 11, 2016
    Assignee: Airbus Operations Limited
    Inventor: Norman Wood
  • Patent number: 9440737
    Abstract: Apparatus to adjust airfoils of rotor blades are disclosed. An example apparatus includes a first surface to be attached to a trailing edge of a rotor blade; a forward edge having a first thickness; an aft edge having a second thickness; and a middle portion between the forward edge and the aft edge having a third thickness greater than the first and second thicknesses.
    Type: Grant
    Filed: May 11, 2012
    Date of Patent: September 13, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Matthew H. Cawthorne, Robert P. Narducci, Perry Ray Ziegenbein
  • Patent number: 9377005
    Abstract: In one aspect, a rotor blade for a wind turbine is disclosed. The rotor blade may include a body extending between a blade root and a blade tip. The body may define a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the body may define a chord line extending between the leading and trailing edges. The rotor blade may also include an airfoil modifier coupled to at least one of the pressure side or the suction side of the body. The airfoil modifier may define an end surface disposed adjacent to the trailing edge. At least a portion of the end surface may extend at a non-perpendicular angle relative to the chord.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: June 28, 2016
    Assignee: General Electric Company
    Inventors: Aaron A. Yarbrough, Stefan Herr, Christian A. Carroll
  • Patent number: 9334045
    Abstract: An aerodynamic structure comprising a series of shock bumps (3) extending from its surface. The shock bumps are distributed across the structure with a non-uniform spacing (d1, d2) between the centers and/or edges of adjacent bumps. The non-uniform spacing between the bumps can be arranged to give maximum wave drag alleviation for the minimum number of bumps as a function of the shock strength across the span, leading to minimum wing weight penalties for a given amount of wave drag alleviation.
    Type: Grant
    Filed: February 17, 2009
    Date of Patent: May 10, 2016
    Assignee: Airbus Operations Limited
    Inventor: Norman Wood
  • Patent number: 9302761
    Abstract: A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: April 5, 2016
    Assignees: THE SOCIETY OF JAPANESE AEROSPACE COMPANIES, KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Kazuhide Isotani, Kenji Hayama
  • Patent number: 9090326
    Abstract: Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft.
    Type: Grant
    Filed: October 13, 2010
    Date of Patent: July 28, 2015
    Assignee: The Boeing Company
    Inventors: Edward A. Whalen, Mark I. Goldhammer
  • Patent number: 9016638
    Abstract: An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventors: Bruce A. Dahl, Gene A. Quandt
  • Patent number: 8925869
    Abstract: An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction.
    Type: Grant
    Filed: January 25, 2013
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Hendrik Friedel, Bodo Zapf
  • 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: 8844879
    Abstract: A flexible tip for integration in a wing trailing edge employs a wing structure rear spar. A flexible upper skin is attached at a forward boundary to the spar and a rigid lower skin is interconnected to the flexible upper skin at a rigid tail piece. At least one actuation link is attached to the rigid tail piece and has a hinge at a forward edge of the rigid lower skin. At least one positioning slider is attached to the hinge which is movable from a neutral position to a first extended position urging the hinge aft for rotation of the rigid lower skin upward and flexing of the flexible upper skin in an upward camber and to a second retracted position urging the hinge forward for rotation of the rigid lower skin downward and flexing of the flexible upper skin in a downward camber.
    Type: Grant
    Filed: December 12, 2011
    Date of Patent: September 30, 2014
    Assignee: The Boeing Company
    Inventor: Gregory M. Santini