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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 1459. Отображено 100.
24-05-2012 дата публикации

Electro-switchable polymer film assembly and use thereof

Номер: US20120128960A1
Автор: Evelyn Peiffer, Gerhard Maier, Joachim Wagner, Robert GÄRTNER, Thomas BÜSGEN, Werner Jenninger
Принадлежит: BAYER MATERIALSCIENCE AG

The invention relates to an electro-switchable polymer film assembly having a first and a second surface side, comprising at least one pair of electrodes ( 3, 4 ) and a polymer matrix ( 2 ), wherein structuring particles ( 5 ) can be embedded in the polymer matrix and the polymer matrix or the structuring particles consist of an electro-active polymer, wherein furthermore, the first and/or the second surface sides can be transferred from a plane condition into a structured condition by electric switching of the electro-active polymer.

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Номер записи: 1
13-09-2012 дата публикации

Fluid resistance reducing method and resistance reducing propulsion device

Номер: US20120227819A1
Автор: Lisong Zou
Принадлежит: Individual

A fluid resistance reducing method and a resistance reducing propulsion device are disclosed, wherein vane-shaped devices are inserted in the fluid at a certain interval along a vertical direction to a moving velocity direction of the fluid, and thus the fluid is divided into several limited zones to limit the fluid and solidify moving state; resultantly the fluid is prevented from directly crashing with fixed wall of a surface of an object to be resistance-reduced and thus a moving velocity direction of the vane-shaped device accords with a predetermined direction of a tangent line of the fixed wall and reaction force on the fluid provides a centripetal force for the fluid to turn, so as to force the fluid to gradually change the velocity direction along the fixed wall and manually intervene with parts of the object to force the fluid near a boundary face to moves stratifiedly and orderly.

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Номер записи: 2
31-01-2013 дата публикации

Aerodynamic surface with improved properties

Номер: US20130028744A1
Автор: Göte Strindberg, Pontus Nordin
Принадлежит: SAAB AB

An article including an outer surface that serves as an aerodynamic surface when the article is subjected for an air stream. A resin matrix made of a polymeric composite laminate of at least one ply includes the outer surface. The at least one ply includes a nano structure embedded therein such that nano filaments of the nano structure in the ply essentially have the same angular orientation relative the plane of the outer surface. The outer ply is a ply of a laminate including at least two plies. Each ply includes large fibers having an orientation different from or identical to the orientation of large fibers of an adjacent ply.

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Номер записи: 3
14-02-2013 дата публикации

Vortex-induced vibration suppression device and mating collar system

Номер: US20130039702A1
Автор: Dean Leroy Henning, Donald Wayne Allen, William Andrew West
Принадлежит: VIV SOLUTIONS LLC

A system including a votex-induced vibration (VIV) suppression device dimensioned to suppress a vortex induced vibration of a support structure, the VIV suppression device having a base portion that encircles at least a portion of the support structure and a support member formed along the base portion. The system further including a collar having a body portion defining an annular channel and a flange portion extending outwardly from the annular channel, the flange portion dimensioned to form a receiving channel around the support structure for receiving the support member. The support member is received within the receiving channel to secure the VIV suppression device to the support structure and the VIV suppression device is capable of rotating around the support structure along the receiving channel.

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Номер записи: 4
09-01-2014 дата публикации

STRAKES FOR UTILITY STRUCTURES

Номер: US20140007523A1
Автор: Fairbairn Mark Hugh, Jacobs Edward M., Nahlen David Joseph, Perkins Nathan Paul, Slocum Richard Morgan
Принадлежит: THOMAS & BETTS INTERNATIONAL, INC.

A modular strake for reducing the effects of wind on utility structures is disclosed. The strake is comprised of individual fin sections that may easily be attached to a utility structure, preferably in a triple helix pattern. The modular strakes may be installed on a utility structure after is has been placed into service. 1. An apparatus for reducing vortex-induced vibrations on a utility structure comprising:a. a first fin section configured to partially surround the perimeter of the utility structure, said first fin section comprising a strip of sheet metal that extends outward from said utility structure; and 'wherein said first fin section and said second fin section are attached at a point where said first fin section and said second fin section overlap.', 'b. a second fin section configured to partially surround the perimeter of the utility structure, said second fin section comprising a strip of sheet metal that extends outward from said utility structure;'}2. The apparatus of wherein said first fin section and said second fin section are attached by welding.3. The apparatus of wherein said first fin section includes a protruding tab configured to overlap with said second fin section.4. The apparatus of wherein said second fin section includes a protruding tab configured to overlap with said first fin section.5. The apparatus of further comprising a first clip for attaching said first fin section to said utility structure and said second clip for attaching said second fin structure.6. The apparatus of wherein said first clip and said second clip are each made of metal.7. The apparatus of wherein said first fin section and said second fin section are made of self-weathering steel.8. The apparatus of wherein said first fin section and said second fin section are made of galvanized steel.9. A method for attaching a strake on a utility structure comprising:a. positioning a first clip and a second clip to the perimeter of said utility structure;b. securing said ...

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Номер записи: 5
20-03-2014 дата публикации

SELF ADJUSTING DETURBULATOR ENHANCED FLAP AND WIND DEFLECTOR

Номер: US20140076419A1
Автор: Sinha Sumon K.
Принадлежит: Sinhatech

A self adjusting flap is disclosed. The self adjusting flap comprises a solid body including a hinge. The flap includes a flexible skin stretched across an array of equi-spaced ridges on a convex surface of the hinged solid body, such that lift and drag forces due to fluid flow across it causes the flap to rotate about the hinge and automatically orient itself to minimize flow losses through turbulence while shielding objects downstream from flow induced drag. 1. A self adjusting flap comprising:a solid body including a hinge; anda flexible skin stretched across an array of equi-spaced ridges on the convex surface of a hinged solid body, such that lift and drag forces due to fluid flow across it causes the self adjusting flap to rotate about the hinge and automatically orient itself to minimize flow losses through turbulence while shielding objects downstream from flow induced drag.2. The self adjusting flap of claim 1 , wherein the hinge is a deflectable solid member which provides a restoring moment so as to hold the self adjusting flap at a desired orientation while allowing adjustments with changes in the fluid flow over it.3. The self adjusting flap of claim 1 , wherein the self adjusting flap is part of a wind deflector attached to a vehicle so as to minimize aerodynamic drag of the vehicle by diverting flow away from un-streamlined components while attenuating turbulent losses.4. The self adjusting flap of claim 2 , wherein the self adjusting flap is part of a wind deflector attached to a vehicle so as to minimize aerodynamic drag of the vehicle by diverting flow away from un-streamlined components while attenuating turbulent losses.5. The self adjusting flap of claim 1 , wherein the vehicle comprises any of a car claim 1 , truck or train.6. The self adjusting flap of claim 2 , wherein the vehicle comprises any of a car claim 2 , truck or train.7. The self adjusting flap of claim 1 , wherein the self adjusting flap is attached to an airfoil claim 1 , wing or ...

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Номер записи: 6
02-01-2020 дата публикации

CHORD-WISE VARIABLE VORTEX GENERATOR

Номер: US20200001973A1
Автор: Bushmire Troy Thomas
Принадлежит:

One embodiment is an apparatus including an airfoil-shaped body; and a chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body. In some embodiments, the chordwise variable vortex generation system includes an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body. In certain embodiments, the surface of the airfoil-shaped body is a top surface of the airfoil-shaped body. In some embodiments, the airfoil-shaped body is an aircraft wing. 1. An apparatus comprising:an airfoil-shaped body; anda chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body.2. The apparatus of claim 1 , wherein the chordwise variable vortex generation system comprises an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body.3. The apparatus of claim 1 , wherein the surface of the airfoil-shaped body comprises a top surface of the airfoil-shaped body.4. The apparatus of claim 1 , wherein the airfoil-shaped body comprises an aircraft wing.5. The apparatus of claim 1 , wherein the chordwise variable vortex generation system comprises a track disposed along the surface of the airfoil-shaped body between a leading edge of the airfoil- ...

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Номер записи: 7
07-01-2016 дата публикации

FLUID PROCESSING SYSTEM, AN ENERGY-DISSIPATING DEVICE, AND AN ASSOCIATED METHOD THEREOF

Номер: US20160003255A1
Автор: Corneliussen Jorgen Harald, Friedemann John Daniel
Принадлежит:

An energy-dissipating device and fluid processing system is provided containing a compressor, a motor, a secondary fluid re-circulation loop, a purge line, and a fluid conduit. The compressor is configured to receive a hot fluid including condensable and non-condensable components, and produce therefrom a primary compressed fluid stream and a secondary fluid stream. The motor is configured to drive the compressor and for ingress and egress of the secondary fluid stream. The secondary fluid re-circulation loop is configured to control an operating temperature of the motor. The secondary fluid re-circulation loop includes a first energy-dissipating device configured to remove excess heat from the secondary fluid stream. The purge line separates a first portion of the secondary fluid stream in the fluid re-circulation loop from a second portion of the secondary fluid stream being returned to the motor. The fluid conduit receives the primary compressed fluid stream from the compressor. 1. A fluid processing system comprising:(a) a compressor configured to receive a hot fluid comprising condensable and non-condensable components, and produce therefrom a primary compressed fluid stream and a secondary fluid stream;(b) a motor configured to drive the compressor, the motor being configured for ingress and egress of the secondary fluid stream;(c) a secondary fluid re-circulation loop configured to control an operating temperature of the motor, the secondary fluid re-circulation loop comprising a first energy-dissipating device configured to remove excess heat from the secondary fluid stream;(d) a purge line configured to separate a first portion of the secondary fluid stream in the fluid re-circulation loop from a second portion of the secondary fluid stream being returned to the motor; and(e) a fluid conduit configured to receive the primary compressed fluid stream from the compressor.2. The fluid processing system according to claim 1 , wherein the first energy-dissipating ...

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Номер записи: 8
13-01-2022 дата публикации

Active Lift Control Device and Method

Номер: US20220009618A1
Автор: John A. Cooney, Jr., Neal E. Fine
Принадлежит: Arctura Inc

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes a means to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

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Номер записи: 9
01-01-2015 дата публикации

HIGH VOLUME AERODYNAMIC GOLF CLUB HEAD

Номер: US20150005096A1
Автор: Albertsen Jeffrey J., Burnett Michael Scott, Willett Kraig Alan
Принадлежит:

A high volume aerodynamic golf club head producing reduced aerodynamic drag forces. The club head has a crown section shape that imparts beneficial aerodynamic properties characterized by a particular drop contour area and projected area of a face portion. 1. A high volume aerodynamic golf club head comprising:{'b': 110', '200', '300', '400', '112', '114', '116', '118, 'claim-text': [{'b': '110', 'i) the hollow body () has a bore having a center that defines a shaft axis (SA) which intersects with a horizontal ground plane (GP) to define an origin point; and'}, {'b': '110', 'claim-text': [{'b': 400', '400, '(a) vertically toward the crown section () from the origin point a distance Ycg in a direction orthogonal to the ground plane (GP), and vertically toward the crown section () from a horizontal center face plane (HCFP) a distance Vcg in a direction orthogonal to the horizontal center face plane (HCFP);'}, {'b': '118', '(b) horizontally from the origin point toward the toe () a distance Xcg that is parallel to a vertical plane defined by the shaft axis (SA) and parallel to the ground plane (GP); and'}, {'b': '114', '(c) a distance Zcg from the origin toward the back () in a direction orthogonal to the vertical direction used to measure Ycg and orthogonal to the horizontal direction used to measure Xcg;'}], 'ii) the hollow body () has a center of gravity (CG) located], 'A) a hollow body () having a club head volume of at least 400 cc, a face (), a sole section (), a crown section (), a front (), a back (), a heel (), and a toe (), wherein'}{'b': 200', '210', '220', '210', '100', '220', '100, 'B) the face () having a top edge () and a lower edge (), wherein a top edge height (TEH) is the elevation of the top edge () above the ground plane (GP) when the high volume aerodynamic golf club head () is positioned in a design orientation, and a lower edge height (LEH) is the elevation of the lower edge () above the ground plane (GP) when the high volume aerodynamic golf ...

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Номер записи: 10
12-01-2017 дата публикации

Flow control technique by dielectric materials

Номер: US20170008615A1
Автор: Beverley McKeon, Kaushik Bhattacharya, Paul Mazur
Принадлежит: California Institute of Technology CalTech

A multilayered active surface is presented whose rugosity can be controlled by an applied electrical field. Varying the applied electrical field can control the rugosity of the surface which makes contact with a fluid, and thereby can affect instabilities of the boundary layer. A middle layer of the multilayered active surface can be made of a compliant electroactive material. In some cases, a pre-stretch in the middle layer can predefine a rugosity of the multilayered active surface without an applied electrical field, in which case an applied electrical field can further alter the rugosity in both amplitude and spatial periodicity and ultimately result to a smooth surface for a higher value of the applied electrical field. A top layer and a bottom layer are constructed using conductive material and uses as electrodes coupled to a voltage source to generate the electric field that controls the rugosity of the surface.

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Номер записи: 11
09-01-2020 дата публикации

ACTIVE LAMINAR FLOW CONTROL SYSTEM WITH COMPOSITE PANEL

Номер: US20200010175A1
Автор: Paolini Thomas, Sanz Martinez Pablo T., Schrell Johann S.
Принадлежит:

An assembly is provided for active laminar flow control. This assembly includes a panel, which panel includes an outer skin, an inner skin and a plurality of plenums between the outer skin and the inner skin. Each of the plurality of plenums is fluidly coupled with a respective array of perforations through the outer skin. The panel is constructed from fiber-reinforced composite material. 1. An assembly for active laminar flow control , comprising a panel comprising an outer skin , an inner skin and a plurality of plenums between the outer skin and the inner skin , each of the plurality of plenums fluidly coupled with a respective array of perforations through the outer skin , wherein the panel is constructed from fiber-reinforced composite material.2. The assembly of claim 1 , further comprising a suction system fluidly coupled with one or more of the plurality of plenums.3. The assembly of claim 1 , wherein the panel is configured from the fiber-reinforced composite material as a monolithic body.4. The assembly of claim 1 , wherein the panel further comprises a plurality of corrugations arranged between the outer skin and the inner skin claim 1 , and the plurality of corrugations form sidewalls of the plurality of plenums.5. The assembly of claim 4 , whereina first of the plurality of corrugations comprises a bridge, a first sidewall, a second sidewall, a first flange and a second flange;the bridge extends between the first sidewall and the second sidewall, and is connected to the inner skin;the first sidewall and the second sidewall each extend between the inner skin and the outer skin;the first flange projects out from the first sidewall and is connected to the outer skin; andthe second flange projects out from the second sidewall and is connected to the outer skin.6. The assembly of claim 4 , wherein a first of the plurality of corrugations is bonded to at least one of the outer skin and the inner skin.7. The assembly of claim 4 , whereinthe panel further ...

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Номер записи: 12
14-01-2016 дата публикации

Orthotropic Bimorph for Improved Performance Synthetic Jet

Номер: US20160013395A1
Автор: Griffin Steven, Whelan Edward
Принадлежит:

Piezoelectric actuators for synthetic jets and other devices are disclosed having orthotropic piezoelectric bimorphs with increased out-of-plane displacements for greater responsiveness to applied electric fields. In some embodiments, the piezoelectric actuators may include interdigitated electrodes applied to a surface of a piezoelectric plate to produce greater in-plane strains in the plate and greater out-of-plane displacements of a flexible diaphragm of the synthetic jet. In other embodiments, the actuator includes an orthotropic piezoceramic plate having a greater d coupling coefficient in one in-plane direction and in the other in-plane direction to cause desired diaphragm out-of-plane displacements when an electric field is applied by electrodes. 1. A piezoelectric actuator comprising:a first plate having a planar first plate surface and an oppositely disposed planar second plate surface separated by a first plate thickness;a first electrode disposed on one of the planar first plate surface and the planar second plate surface and having a plurality of first fingers;a second electrode disposed on the same one of the planar first plate surface and the planar second plate surface and having a plurality of second fingers alternated with the plurality of first fingers; anda flexible diaphragm having a first diaphragm surface and an oppositely disposed second diaphragm surface, wherein one of the planar first plate surface and the planar second plate surface of the first plate faces and is rigidly secured to the first diaphragm surface,wherein a first electric field applied through the first electrode and the second electrode causes in-plane tensile stresses to elongate the first plate in a first direction, causes in-plane compressive stresses in a second direction, and causes transverse compressive stresses in a third direction, and wherein a second electric field applied through the first electrode and the second electrode causes compressive stresses to compress ...

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Номер записи: 13
03-02-2022 дата публикации

SELF-ADHERING FILM WITH AERODYNAMIC PERFORMANCE

Номер: US20220033068A1
Автор: Mikami Haruyuki, Okura Ken, Tachihara Takayuki
Принадлежит:

Provided is the film that can reduce aerodynamic drag and enhance aerodynamic performance. The film according to an embodiment is a film () to be attached to a moving body that moves in a predetermined moving direction, extends along a second direction (D) being the moving direction, and includes recesses and protrusions (A) configured to enhance aerodynamic performance of the moving body on a surface of the film. 1. A film to be attached to a moving body that moves in a predetermined moving direction , the film comprises:recesses and protrusions configured to enhance aerodynamic performance of the moving body on a surface of the film.2. The film according to claim 1 , further comprising a hydrophilic coating layer configured to coat the recesses and protrusions.3. The film according to claim 1 , further comprising a hydrophobic coating layer configured to coat the recesses and protrusions.4. The film according to claim 1 , further comprising an adhesive agent layer configured to cause the film to adhere to the moving body.5. The film according to claim 4 , further comprising an intermediate layer that is positioned between the recesses and protrusions and the adhesive agent layer. One aspect of the present disclosure relates to a film.Patent Document 1 describes a method of reducing a resistance force and a resistance-force reduction item. As the resistance-force reduction item, a sheet material is described. The sheet material includes a pattern surface on a front surface, and a cross section of a pattern layer is a serrated cross section having a plurality of mountains and a plurality of valleys. Further, the sheet material including an adhesive layer on a surface opposite to the pattern surface is described. The sheet material reduces a resistance force of an item when the adhesive layer is attached to the surface of the item.Incidentally, a moving body, for example, a vehicle, an airplane, a blade of a wind power plant, or the like exerts a function of ...

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Номер записи: 14
17-01-2019 дата публикации

LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT

Номер: US20190016444A1
Автор: HECK Christian, Schrauf Géza
Принадлежит:

A leading edge structure () for a flow control system of an aircraft, including a double-walled leading edge panel () that surrounds a plenum (), wherein the leading edge panel () includes an inner wall element () facing the plenum () and an outer wall element () in contact with the ambient flow (), wherein between the inner and outer wall elements () the leading edge panel () includes elongate stiffeners () spaced apart from one another, so that between each pair of adjacent stiffeners () a hollow chamber () is formed between the inner and outer wall elements (), wherein the outer wall element () includes micro pores () forming a fluid connection between the hollow chambers () and an ambient flow (), and wherein the inner wall element () includes openings () forming a fluid connection between the hollow chambers () and the plenum (). 1. A leading edge structure for a flow control system of an aircraft , the leading edge structure comprisinga double-walled leading edge panel that surrounds a plenum in a curved manner, the plenum extending in a span direction,wherein the leading edge panel has a first side portion extending from a leading edge point to a first attachment end,wherein the leading edge panel has a second side portion opposite the first side portion, extending from the leading edge point to a second attachment end,wherein the leading edge panel comprises an inner wall element facing the plenum and an outer wall element in contact with the ambient flow,wherein between the inner and outer wall elements, the leading edge panel comprises a plurality of elongate stiffeners spaced apart from one another, so that between each pair of adjacent stiffeners a hollow chamber is formed between the inner and outer wall elements,wherein the outer wall element comprises a plurality of micro pores forming a fluid connection between the hollow chambers and an ambient flow, andwherein the inner wall element comprises openings forming a fluid connection between the hollow ...

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Номер записи: 15
16-01-2020 дата публикации

LOW DRAG SURFACE

Номер: US20200018333A1
Автор: WEBB Simon P.
Принадлежит: ROLLS-ROYCE PLC

A low drag surface is provided for a fluid washed object, the low drag surface comprising an aerodynamic surface comprising a cut-out region, and a continuously translatable surface comprising a surface portion. The surface portion is positioned in the cut-out region such that the aerodynamic surface and the surface portion form a fluidwash surface, and the surface portion is translatable relative to the aerodynamic surface. 2. The low drag surface according to claim 1 , wherein the surface portion is substantially flush with the aerodynamic surface.3. The low drag surface according to claim 1 , wherein the continuously translatable surface is the radially outer surface of a sphere.4. The low drag surface according to claim 1 , whereineach axis of rotation is fixed in position relative to the aerodynamic surface.5. The low drag surface according to claim 1 , the low drag surface further comprising an actuator for actuating the continuously translatable surface.6. The low drag surface according to claim 1 , wherein the continuously translatable surface is arrangeable such that a forward gap exists between the aerodynamic surface and a forward edge of the surface portion and/or a rearward gap exists between the aerodynamic surface and a rearward edge of the surface portion claim 1 , and wherein air is forced out of the forward gap and/or air is forced in to the rearward gap.7. The low drag surface according to claim 1 , wherein the low drag surface comprises a plurality of cut-out regions and a plurality of surface portions claim 1 , wherein each surface portion corresponds to and is positioned in a cut-out region claim 1 , and wherein the aerodynamic surface and the plurality of surface portions form a fluidwash surface.8. The low drag surface according to claim 7 , wherein the plurality of cut-out regions are arranged in an array claim 7 , and wherein optionally the number of cut-out regions is greater than 4 claim 7 , 6 claim 7 , 8 claim 7 , 10 or 20.9. A gas ...

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Номер записи: 16
22-01-2015 дата публикации

Aerodynamic Variable Cross-Section Airfoil and Constant Lateral Surface Area Truss

Номер: US20150023797A1
Автор: Egbert Nitin Kitchley
Принадлежит:

The invention provides a mechanism for an airtight airfoil with variable cross section that can lower its average density below that of the medium in which it is used, providing additional bouyancy and reducing the effective weight of any craft to which it may be affixed. The outside of the airfoil is formed by a sheet of material that is impermeable to the medium in which the foil is used. This sheet is affixed to several points on an internal expandable frame. The cross-sectional perimeter of the frame remains constant throughout the expansion of the frame, minimizing wear on the enclosing sheet of material. Because the length of the sheet remains constant through the expansion process, the sheet need not be elastic, and may even be replaced by rigid plates of material. By providing a variable source of buoyancy, this foil enables lower speed and lower power applications than regular foils. By providing a smoothly variable airfoil cross-section, this foil enables higher performance in a wider variety of aerodynamic conditions. 1. An expanding frame , henceforth referred to as simply a “frame ,” whose vertices lie at the vertices of a polygonal prism , the lateral surface area of which does not change during expansion , consisting of a series of parallel planar expanding trusses which maintain a constant perimeter over the range of their expansion. Each planar expanding truss consists of two half-trusses constructed so as to share their expanding side. Each half-truss is constructed as in one of the sub-claims below. Each of the sub-claims corresponds to the corresponding sub-figure in .{'figref': {'@idref': 'DRAWINGS', 'FIG. 5'}, 'I. An expandable strut along the expanding side, a rigid strut that can pivot about a position fixed with respect to one end of the expanding side, and another rigid strut that can pivot about both a position fixed with respect to the other end of the expanding side, and a position fixed with respect to the other rigid strut. This ...

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Номер записи: 17
25-01-2018 дата публикации

FIRE-FIGHTING DEVICE

Номер: US20180021609A1
Автор: BRINK Stephan, JÜRGENS Rolf, VOIGTLÄNDER Benjamin
Принадлежит:

A fire-fighting device can cool a vertical wall where a horizontally-extending profiled element is disposed on the vertical wall. The fire-fighting device may comprise a guide plate that includes a first region arranged above the horizontally-extending profiled element, a second region arranged below the horizontally-extending profiled element, a third region arranged in a plane of the horizontally-extending profiled element and on a side of the horizontally-extending profiled element facing away from the vertical wall, and a fourth region in the second region. The guide plate may have a distance to the wall of mm to mm in the fourth region. 18-. (canceled)9. A fire-fighting device for cooling a vertical wall wherein a horizontally-extending profiled element is disposed on the vertical wall , the fire-fighting device comprising a guide plate that includes a first region disposed above the horizontally-extending profiled element , a second region disposed below the horizontally-extending profiled element , a third region disposed in a plane of the horizontally-extending profiled element and on a side of the horizontally-extending profiled element facing away from the vertical wall , and a fourth region disposed in the second region , wherein in the fourth region the guide plate has a distance to the vertical wall of 1 mm to 20 mm.10. The fire-fighting device of wherein in the fourth region the guide plate has a distance to the vertical wall of 2 mm to 10 mm.11. The fire-fighting device of wherein in the fourth region the guide plate has a distance to the vertical wall of 2.5 mm to 5 mm.12. The fire-fighting device of wherein the guide plate forms a closed area between the first region and the second region.13. The fire-fighting device of wherein the guide plate comprises steel.14. The fire-fighting device of wherein the vertical wall is a bulkhead.15. The fire-fighting device of wherein the horizontally-extending profiled element is at least one of a bead profile or ...

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Номер записи: 18
24-01-2019 дата публикации

RIBLET STRUCTURE AND OBJECT

Номер: US20190023379A1
Автор: Iijima Hidetoshi, Koshioka Yasuhiro, Kurita Mitsuru, Nishizawa Akira, Okabayashi Kie
Принадлежит: JAPAN AEROSPACE EXPLORATION AGENCY

The present invention provides a riblet structure that further reduces drag, which is a sum of turbulent friction drag and pressure drag, and an object including such a riblet structure. An object such as an aircraft, plant, and pipeline includes a wavelike riblet pattern on a surface. The wavelike riblet pattern includes a large number of wavelike riblets. Each of the large number of wave riblets includes a wavelike ridge line, and a height thereof changes cyclically with respect to a fluid flow direction. With such a configuration, drag, which is a sum of turbulent friction drag and pressure drag, can be further reduced. 1. A riblet structure , comprisinga plurality of wavelike riblets,a height of each of the plurality of wavelike riblets being set to become smaller as an angle formed between a ridge line and a fluid flow direction becomes larger.2. The riblet structure according to claim 1 , whereinthe ridge line of each of the plurality of wavelike riblets has a sinusoidal shape of a first wavelength, andthe height of each of the plurality of wavelike riblets increases/decreases in a sinusoidal shape of a second wavelength as a half wavelength of the first wavelength in the fluid flow direction.3. The riblet structure according to claim 2 , wherein {'br': None, 'i': a≤', 'h., '0<0.2'}, 'when a reference height of the wavelike riblets is represented by h, an amplitude a of the second wavelength satisfies'}4. The riblet structure according to claim 1 , whereinthe plurality of wavelike riblets are arranged at constant intervals.5. An object claim 1 , comprisinga wavelike riblet pattern including wavelike ridge lines, a height of the wavelike riblet pattern changing cyclically with respect to a fluid flow direction. The present invention relates to an object including a surface on which fluid flows and a riblet structure applied to such an object.It is known that, by providing a riblet pattern on a surface of an aircraft, a wall surface of a pipeline, and the like, ...

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Номер записи: 19
23-01-2020 дата публикации

SWIRLING JET ACTUATOR FOR CONTROL OF SEPARATED AND MIXING FLOWS

Номер: US20200025225A1
Автор: Alvi Farrukh, Munday Phillip, Taira Kunihiko
Принадлежит:

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. 1. A method of controlling a fluid flow , comprising inputting a swirling flow into the fluid flow.2. The method of claim 1 , wherein the swirling flow is inputted in an orientation such that a central axis claim 1 , about which the swirling flow rotates is normal to a surface of a body over which the fluid flow is passing.3. The method of claim 1 , further including the step of adjusting flow properties of the swirling flow.4. The method of claim 1 , wherein the swirling flow is actively controllable.5. The method of claim 1 , wherein the inputting occurs at a plurality of actuator sites such that each actuator site includes a swirling flow input and each swirling flow input has an initial direction of rotation that is opposite of the initial direction of rotation of the swirling flow input of an adjacently located actuator site.6. The method of claim 1 , wherein the inputting occurs at a plurality of actuator sites such that each actuator site includes a swirling flow input and each swirling flow input has an initial direction of rotation that is in the same initial direction of rotation of the swirling flow input of an adjacently located actuator site.7. The method of claim 1 , further including a step of inputting a momentum flow.8. The method of claim 7 , wherein the momentum flow is inputted in an orientation that is normal to a surface of a body over which the fluid flow is passing.9. The method of claim 7 , wherein the momentum flow is adjustable.10. A method of controlling a fluid flow claim 7 , comprising the step of inputting a swirling flow ...

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Номер записи: 20
01-02-2018 дата публикации

Method and apparatus of plasma flow control for drag reduction

Номер: US20180031013A1
Автор: Flint O. Thomas, Thomas C. Corke
Принадлежит: University of Notre Dame

A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.

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Номер записи: 21
31-01-2019 дата публикации

ADJUSTABLE COMPONENT COOLING DEVICE FOR CONTROLLING DOWNFORCE GENERATED BY A VEHICLE

Номер: US20190031253A1
Автор: Parry-Williams Dan, Slight Arthur
Принадлежит: McLaren Automotive Limited

An automobile comprising a cooling duct that extends to underneath the automobile to channel cooling air to a component of the automobile when the automobile is in motion is provided. A restriction located within the cooling duct that is moveable from a first position, in which airflow to the component is substantially unimpeded, to a second position in which the airflow to the component is substantially impeded, when the automobile is in motion is further provided. The automobile generates more downforce when the restriction is in the second position versus the first position. A control unit configured to select the position of the restriction to control the downforce generated by the automobile if the temperature of the component is below a predetermined level, and to select the first position for the restriction if the temperature of the component is above the predetermined level, is also provided. 1. An automobile comprising a duct arranged to channel air from a region which is at relatively high pressure when the automobile is in motion to a region underneath the automobile which is at relatively low pressure when the automobile is in motion , the duct comprising a resilient elastic restriction arranged to substantially close off the duct , the duct being configured such that motion of the automobile generates a pressure difference across the elastic restriction , the elastic restriction being configured to open when the pressure difference approximately exceeds a predetermined value so as to allow air to flow from the relatively high pressure region to underneath the automobile and reduce the downforce generated by the automobile.2. An automobile as claimed in claim 1 , wherein the region underneath the automobile is in front of a front wheel of the automobile.3. An automobile as claimed in claim 1 , wherein the resilient elastic restriction is arranged to be substantially flush with a surface of the cooling duct when it substantially closes off the third duct ...

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Номер записи: 22
17-02-2022 дата публикации

Switching unit and pneumatic system

Номер: US20220049721A1
Автор: Matthew Oakley, Thomas Reitinger
Принадлежит: Berlin Heart GmbH

A switching unit may be provided for connecting a first pneumatic unit and a second pneumatic unit of a pneumatic system together. The switching unit comprises a main body having: a channel structure which extends through the main body; a first and a second inlet for introducing a pressure into the channel structure; a first and a second outlet for discharging at least some of the pressure from the channel structure; and a first and a second valve; wherein the first inlet can be brought into a pressure-exchange connection to the first outlet via a first channel by setting a first switch position of the first valve or to the second outlet via a second channel by setting a second switch position of the first valve, and wherein the second inlet can be brought into a pressure-exchange connection to the first outlet via a third channel by setting a first switch position of the second valve or to the second outlet via a fourth channel by setting a second switch position of the second valve.

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Номер записи: 23
30-01-2020 дата публикации

STRUCTURALLY ENHANCED PLASTICS WITH FILLER REINFORCEMENTS

Номер: US20200032823A1
Автор: Johnson, SR. WILLIAM L.
Принадлежит:

A composition comprising a fluid, and a material dispersed in the fluid, the material made up of particles having a complex three dimensional surface area such as a sharp blade-like surface, the particles having an aspect ratio larger than 0.7 for promoting kinetic boundary layer mixing in a non-linear-viscosity zone. The composition may further include an additive dispersed in the fluid. The fluid may be a thermopolymer material. A method of extruding the fluid includes feeding the fluid into an extruder, feeding additives into the extruder, feeding a material into the extruder, passing the material through a mixing zone in the extruder to disperse the material within the fluid wherein the material migrates to a boundary layer of the fluid to promote kinetic mixing of the additives within the fluid, the kinetic mixing taking place in a non-linear viscosity zone. 162-. (canceled)63. A composition comprisinga fluid having a boundary layer;particles in said boundary layer of said fluid, said particles having a sharp conchoidal surface and a complex three-dimensional surface area, said particles having a 2.5 Mohs scale hardness or greater and having a size from nano to micron;wherein said particles comprise from 0.5 wt % to 8 wt % of the composition.64. The composition according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , sharp surface.65. The composition according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , sharp claim 63 , blade-like surface.66. The composition according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , curved surface.67. The composition according to wherein said particles comprise a jet milled material.68. The composition according to wherein said particles comprise an impact jet milled material.69. The composition according to wherein said particles comprise a ball milled material.70. The composition according to wherein said ...

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Номер записи: 24
08-02-2018 дата публикации

Motor Vehicle

Номер: US20180038396A1
Автор: Thomas Wagner
Принадлежит: Bayerische Motoren Werke AG

The speed of a motor vehicle causes the production of an air flow which can produce disturbing noises at edges of motor vehicle components. To provide a motor vehicle in which disturbing noises due to the air flow when travelling are avoided, at least one spoiler element is provided, or in that a plurality of spoiler elements are provided. The respectively present number of spoiler elements is formed upstream and/or downstream of at least one existing edge of the particular component acted upon by the air flow. The number of spoiler elements is arranged and/or shaped in such a manner that the air flow striking against the respective spoiler elements is dispersed non-uniformly.

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Номер записи: 25
24-02-2022 дата публикации

Hexagonet

Номер: US20220056935A1
Автор: Sahnoune Fatiha, Scott Philip Andrew
Принадлежит:

An innovative hexagonet provides a unique surface structure to achieve optimal tribological performance of any solid objects. The hexagonet comprises fractal hexagons and each fractal hexagon include regular hexagons in fractal form that can reduce friction and improve interactions of an object with any other objects and environment, thereby increasing the performance and reliability of the object by increasing balance and consistency in motion and at rest. Once integrated to the object, the hexagonet can form a protective surface which is repellent to other matter, thus, providing slippery, anti-fouling and anti-bacterial properties. Additionally, the protective surface creates a tribological effect which significantly reduces heat and disturbance, contamination and wear and tear resulting in reduction of energy consumption of the object. Further, the versatile and effective hexagonet can provide various applications to the object in solid-to-solid, solid-to-liquid, solid-to-air interactions, etc. 1. A hexagonet for providing optimal surface tribology comprising:at least one fractal hexagon;a solid object;each fractal hexagon being exteriorly positioned on the solid object; andeach fractal hexagon comprising a plurality of hexagons.2. The hexagonet for providing optimal surface tribology comprising as claimed in comprising:the plurality of hexagons comprising concentric hexagons.3. The hexagonet for providing optimal surface tribology comprising as claimed in comprising:the plurality of hexagons comprising nonconcentric hexagons.4. The hexagonet for providing optimal surface tribology comprising as claimed in comprising:the each of the plurality of hexagons comprising an outermost hexagon and an innermost hexagon;the outermost hexagon of the plurality of hexagons being positioned flush with exterior surface of the solid object; andthe innermost hexagon of the plurality of hexagons being interiorly positioned in the solid object.5. The hexagonet for providing ...

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Номер записи: 26
16-02-2017 дата публикации

Microelectronic module, module array, and method for influencing a flow

Номер: US20170043863A1
Автор: Emanuel Ermann, Karin Bauer, Ralf Caspari, Robert Weichwald
Принадлежит: Airbus Defence and Space GmbH

A microelectronic module for influencing a flow of a fluid is provided. The module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one active flow-influencing element for influencing the direction and/or the speed of a fluid which is flowing around and/or over the flow-influencing element. At least the voltage converter and the active flow-influencing element are disposed on a thin-film, planar substrate. The influencing of the direction and/or the speed of the fluid is dependent on a hydrodynamic acceleration as a function of the second voltage provided by the voltage converter at the flow-influencing element.

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Номер записи: 27
14-02-2019 дата публикации

VISCOUS DRAG REDUCTION APPARATUS FOR VEHICLES

Номер: US20190047640A1
Автор: AL-AMRI Fahad Ghallab, SIDDIQUI MUHAMMAD UMAR
Принадлежит: Imam Abdulrahman Bin Faisal University

Described herein are a viscous drag reduction apparatus and a method. The apparatus includes a pair of rollers connected to a supporting surface on a roof of the vehicle, a belt having a frictional surface and partially wrapped around the pair of rollers, such that the pair of rollers allow the belt to rotate in response to an air flow generated around the vehicle when the vehicle is in motion, the pair of rollers having a length in an axial direction that is at least as long as a width of the belt, an assembly of the pair of rollers and the belt being at least partially recessed with respect to a top line of the roof, and a reverse flow cover connected to the front end of the roof of the vehicle to block an air back flow generated by the belt when rotating. 1. A viscous drag reduction apparatus for a vehicle comprising:a pair of rollers connected to a supporting surface on a roof of the vehicle;a belt having a frictional surface and partially wrapped around the pair of rollers, such that the pair of rollers allow the belt to rotate in response to an air flow generated around the vehicle when the vehicle is in motion, the pair of rollers having a length in an axial direction that is at least as long as a width of the belt, an assembly of the pair of rollers and the belt being at least partially recessed with respect to a top line of the roof; anda reverse flow cover connected to the supporting surface of the roof of the vehicle and extending to a top of the belt so as to block an air back flow generated by the belt when rotating, the shape of the reverse flow cover being angled at less than 90 degrees with respect to supporting surface and tilting in a backward direction with respect to a moving direction of the vehicle.2. The apparatus according to claim 1 , wherein the supporting surface is an inset portion of the roof of the vehicle claim 1 , the supporting surface being lower than an apex of a leading edge of the roof claim 1 , where the leading edge is at a ...

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Номер записи: 28
14-02-2019 дата публикации

Riblet film for reducing the air resistance of aircraft

Номер: US20190047684A1
Автор: Hegenbart Matthias, Linde Peter
Принадлежит:

A riblet film for reducing the air resistance of aircraft, comprising a suspension with magnetic particles enclosed therein. Depending on the pattern of a magnetic field acting on the riblet film, the magnetic field that is acting can be made visible, at least in certain regions, by changing the orientation of the magnetic particles. The riblet film allows an inspection of the aircraft structure located under the riblet film through the riblet film. 1. A riblet film for reducing air resistance of an aircraft , comprising:a suspension with magnetic particles enclosed therein,wherein, depending on a pattern of a magnetic field acting on the riblet film, the magnetic field that is acting is made visible, at least in certain regions, by changing an orientation of the magnetic particles.2. The riblet film according to claim 1 , wherein the riblet film comprises a layer with a multiplicity of microcapsules claim 1 , wherein the suspension is distributed among the microcapsules and respectively enclosed therein.3. The riblet film according to claim 1 , wherein the magnetic particles comprise colloidal nickel.4. The riblet film according to claim 1 , wherein at least one of the suspension or a layer comprising the microcapsules is applied to a substrate serving as a carrier film.5. The riblet film according to claim 1 , wherein the riblet film comprises a plurality of ribs which are arranged substantially parallel to one another and have tips.6. The riblet film according to claim 1 , wherein the riblet film comprises a plurality of riblets each having a substantially triangular cross section.7. The riblet film according to claim 1 , wherein the riblet film further comprises has an adhesive layer arranged to adhesively attach the riblet film onto an aerodynamic surface.8. An aircraft with a riblet film according to applied to an aerodynamic surface of the aircraft.9. A method for examining an aircraft structure to which a riblet film according to has been applied claim 1 , ...

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Номер записи: 29
25-02-2016 дата публикации

FAIRING

Номер: US20160053554A1
Автор: SKAUGSET Kjetil
Принадлежит:

A fairing device for the reduction of vortex-induced vibrations or motions and the minimization of drag about a substantially cylindrical element immersed in a fluid medium, comprising; a cylindrical element, a fairing rotatably mounted about the cylindrical element, the fairing comprising a shell with a cylindrical cross-sectional shape with an outer diameter (D) following the outer diameter of the cylindrical element from an upward stagnation point of 0 degrees to at least +/−90 degrees, and which at +/−90 degrees continues as two fin-like portions in an aft direction and defining a chord length (C), further comprising that the fin-like portions are convexly curved aft of +/−90 degrees thus tapering towards each other and defining a tail end opening or gap less than the fairing standoff height. 1. A fairing device for the reduction of vortex-induced vibrations or motions and reduction of drag about a substantially cylindrical element immersed in a fluid medium , comprising;a mainly cylindrical element,a fairing rotatably mounted about the mainly cylindrical element, the fairing comprising a shell with a mainly cylindrical cross-sectional shape with an outer diameter (D) following the outer diameter of said cylindrical element from an upward stagnation point of 0 degrees to at least +/−90 degrees, and which at +/−90 degrees continues as two fin-like portions in an aft direction and defining a chord length (C),characterized in thatthe fin-like portions are convexly curved aft of +/−90 degrees thus tapering towards each other and defining a tail end opening less than the fairing standoff height.2. The fairing device of claim 1 , wherein the fin-like portions are convexly curved fore of +/−90 degrees thus tapering towards each other and defining a tail end opening less than the fairing standoff height.3. The fairing device of claim 1 , wherein the tail end opening constitutes more than 80% of the fairing standoff height.4. The fairing device of claim 1 , wherein said ...

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Номер записи: 30
15-05-2014 дата публикации

Flow Guider and Devices with the Same

Номер: US20140130923A1
Автор: Hu Chen-Chuan
Принадлежит:

A flow guider has a guiding body, a blade edge and two tips. The guiding body has two guiding surfaces configured symmetrically with each other. Each guiding surface is convex. The blade edge is curved, is formed between and connects the guiding surfaces and has two opposite ends. The tips are formed respectively at the ends of the blade edge and each tip merges the guiding surfaces and one end of the blade edge. The flow guider divides and guides oncoming airflow or waterflow to smoothly pass across the flow guider with reduced turbulence so that vehicles or bridge piers mounted with the flow guiders suffer less vibration, shaking and damage when encountering airflow or waterflow. 1. A flow guider comprising: two opposite guiding surfaces configured symmetrically with each other, and each guiding surface being convex;', 'a blade edge being curved, formed between and connecting the guiding surfaces and having two opposite ends; and', 'two tips formed respectively at the ends of the blade edge and each tip merging the guiding surfaces and one end of the blade edge., 'a guiding body having'}2. The flow guider as claimed in claim 1 , whereinthe guiding body is fin-shaped when observed from a left or right side view and is leaf-shaped when observed from a top view; andwhen the guiding body is observed from the left or right side view, the blade edge is hill-like with an intermediate raised section and two outer sloping sections extending from the intermediating raised section.3. The flow guider as claimed in further comprising a mounting plate attached to the guiding body and having multiple assembling holes defined through the mounting plate.4. A land vehicle comprising:a sheet metal; and two opposite guiding surfaces configured symmetrically with each other, and each guiding surface being convex;', 'a blade edge being curved, formed between and connecting the guiding surfaces and having two opposite ends; and, 'multiple flow guiders mounted on the sheet metal and each ...

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Номер записи: 31
20-02-2020 дата публикации

HYDROPHOBIC XEROGEL FILM AND METHOD OF USE THEREOF FOR REDUCING DRAG

Номер: US20200056113A1
Автор: MARION Olivier, WHIPP Gary
Принадлежит: Mirapakon Inc.

The present disclosure generally relates to drag reducing hydrophobic xerogel films. More particularly, the invention relates to hydrophobic ORMOSIL (organically modified silica) drag reducing film. 1. A method for reducing the drag of an object having an interfacial interaction with a fluid , comprising providing a xerogel film , on at least a portion of a surface of said object.2. The method of claim 1 , wherein said step of providing a xerogel film is comprising coating a composition comprising a sol-gel matrix on said at least a portion of a surface of said object.3. The method of claim 2 , wherein said sol-gel matrix is comprising partially hydrolyzed and/or condensed silanes.4. The method of claim 3 , wherein said silanes are alkoxysilanes.5. The method of claim 4 , wherein said alkoxysilanes are comprising long-chain alkyltrialkoxysilanes claim 4 , short-chain alkyltrialkoxysilanes claim 4 , aminoalkyltrialkoxysilanes claim 4 , alkylaminoalkyltrialkoxysilanes claim 4 , dialkylaminoalkyltrialkoxysilanes claim 4 , perfluororalkyltrialkoxysilanes or a combination thereof; and a tetraalkoxysilane.6. The method of claim 2 , wherein said sol-gel matrix comprises two claim 2 , three or four partially hydrolyzed and/or condensed alkoxysilanes.7. The method of claim 2 , wherein said sol-gel matrix comprises a first and second partially hydrolyzed and/or condensed silane claim 2 , wherein said first silane is a short-chain alkyltrialkoxysilane claim 2 , and said second silane is a tetraalkoxysilane.8. The method of claim 2 , wherein said sol-gel matrix comprises a first claim 2 , second and third partially hydrolyzed and/or condensed silane claim 2 , wherein said first silane is a long-chain alkyltrialkoxysilane claim 2 , said second silane is a short-chain alkyltrialkoxysilane claim 2 , and said third silane is a tetraalkoxysilane.9. The method of claim 2 , wherein said sol-gel matrix comprises a first claim 2 , second claim 2 , third and fourth partially hydrolyzed ...

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Номер записи: 32
20-02-2020 дата публикации

VORTEX-SHEDDING-ARRANGEMENT

Номер: US20200056593A1
Автор: Jensen Anders Hoejris
Принадлежит:

A Vortex-shedding-arrangement, which is prepared to be arranged on a tower of a wind turbine, is provided. Embodiments of the invention even relate to a tower, which is equipped with the Vortex-shedding-arrangement and to a method to equip the tower with the Vortex-shedding-arrangement. 1. A vortex-shedding-arrangement , wherein:the vortex-shedding-arrangement is arranged and prepared to be connected to a surface of a tower,the vortex-shedding-arrangement is prepared to reduce vortex-induced-vibrations, acting on the tower and its structure, wherein the vortex shedding arrangement comprises vortex shedding elements and at least one shrink foil,wherein the vortex shedding elements are connected with the shrink foil, andwherein the shrink foil is prepared to fix and to position the vortex shedding elements at specific positions at the tower surface by heat applied to the shrink foil.2. The arrangement according to claim 1 ,wherein the vortex shedding arrangement comprises vortex shedding elements and two shrink foils,wherein the vortex shedding elements are arranged and positioned between the two shrink foils, which are welded together thus the vortex shedding elements are enveloped by the shrink foilswherein the shrink foils are prepared to fix and to position the vortex shedding elements at specific positions at the tower surface by heat applied to the shrink foils.3. The arrangement according to claim 1 , wherein the vortex shedding elements have a triangular shaped cross-section.4. The arrangement according to claim 1 , wherein the angle of inclination of the longitudinal axis of the vortex shedding element in respect to the longitudinal axis of the tower is in a range between 10° and 80°.5. The arrangement according to claim 1 , wherein the vortex shedding elements are made of polyethylene or wherein the vortex shedding elements are made of foam.6. A tower with a vortex-shedding-arrangement according to claim 1 ,wherein the vortex-shedding-arrangement is ...

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Номер записи: 33
27-02-2020 дата публикации

Controlled Turbulence System

Номер: US20200063765A1
Автор: Dalmas, II Elario Dino, Leathers Brett James, Shoenberger Douglas Charles
Принадлежит: Quest Engines, LLC

A controlled turbulence system is disclosed to have a surface and means configured to induce a first wave form in a working fluid along the surface. Some embodiments of the invention may include a second means configured to induce a second wave form in the working fluid, wherein the first wave form and the second wave form have different frequencies. The first and/or second means may be provided as fields of pockets formed in the surface or wave-based generators. 1. A controlled turbulence system comprising:a surface configured to be provided adjacent to a working fluid;a first means configured to induce a first wave form in the working fluid along the surface adjacent to the working fluid;a second means configured to induce a second wave form in the working fluid along the surface adjacent to the working fluid,wherein the first wave form and the second wave form have different frequencies, andwherein the first wave form and the second wave form cooperate in the working fluid to create a turbulence boundary layer in the working fluid along the surface.2. The system of wherein the first means comprises a plurality of laterally spaced pockets arranged in plurality of rows to form a field of pockets on or through the surface.3. The system of wherein the second means comprises a plurality of laterally spaced pockets arranged in a plurality of rows to form a field of pockets on or through the surface claim 2 , andwherein the plurality of laterally spaced pockets comprising the second means have one or more dimensions that are different from one or more corresponding dimensions of the laterally spaced pockets comprising the first means.4. The system of wherein the second means comprises a transducer.5. The system of wherein the plurality of laterally spaced pockets comprising the first means have one or more dimensions claim 2 , andwherein said system further comprises an apparatus configured to vary the one or more dimensions.6. The system of further comprising a closed- ...

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Номер записи: 34
27-02-2020 дата публикации

ADJUSTABLE PASSIVE CHOKES

Номер: US20200063766A1
Автор: ALJUBORI Ahmed, STASIUK Ryan, STEPHENS Evan
Принадлежит: Secure Energy (Drilling Services) Inc.

Adjustable passive choke devices, systems, and methods for controlling fluid flow rate, pressure, or both, are provided. The adjustable passive choke devices may comprise a fluid conduit having a first end, a second end, and an intervening portion therebetween, the intervening portion comprising a flow resistance element for reducing a flow rate of a fluid when the fluid is passed through the fluid conduit from the first end to the second end. The devices may further comprise a selectable bypass line connected upstream and downstream of the flow resistance element, or a portion thereof, operable to provide a fluid flow bypass path bypassing all, or a portion, of the flow resistance element when activated. 124.-. (canceled)25. An adjustable passive choke device for controlling fluid flow rate , pressure , or both , said device comprising:a fluid conduit having a first end, a second end, and an intervening portion therebetween, the intervening portion comprising a flow resistance element for reducing a flow rate of a fluid when the fluid is passed through the fluid conduit from the first end to the second end; anda selectable bypass line connected upstream and downstream of the flow resistance element, or a portion thereof, operable to provide a fluid flow bypass path bypassing all, or a portion, of the flow resistance element when activated;whereby activation of the selectable bypass line configures the adjustable passive choke device for increased flow rate by at least partially opening the fluid flow bypass path, and deactivation of the selectable bypass line configures the adjustable passive choke device for decreased flow rate by at least partially closing the fluid flow bypass path.26. The device of claim 25 , further comprising a flow meter downstream of the flow resistance element for determining a fluid flow rate claim 25 , a pressure gauge or pressure sensor for determining a pressure downstream of the flow resistance element claim 25 , or both.27. The ...

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Номер записи: 35
05-03-2020 дата публикации

METHODS AND APPARATUS FOR CONTROLLING FLOW FIELDS

Номер: US20200072259A1
Автор: Amitay Michael, Gildersleeve Samantha
Принадлежит: RENSSELAER POLYTECHNIC INSTITUTE

Methods and systems for controlling a fluid flow field near a surface are disclosed. In some embodiments, the system includes an array of oscillating bodies disposed on the surface to provide physical modification to the flow field. Fluid jets are also emitted from an outlet in the oscillating body to provide virtual modification of the flow field through momentum addition. Fluid jet sources, including synthetic jet generators such as piezoelectric drivers and sources of compressed fluids such as air or water, are positioned to be in fluid communication with the outlet at intervals during the oscillation of the oscillating body. Controlling the oscillation amplitude and frequency of the body, as well as the location of oscillating body outlets and frequency of fluid jet emission, have advantageous effects for the surface such as improved heat transfer properties and reduction in structural vibration and noise. 1. A method of manipulating a flow field over a surface comprising:providing a body having a fluid jet outlet;oscillating said body in said flow field; andemitting a fluid jet from said fluid jet outlet into said flow field.2. The method of manipulating a flow field according to claim 1 , wherein said fluid jet is generated from a compressed fluid source claim 1 , a synthetic jet generator claim 1 , an external flow stream claim 1 , or a combination thereof.3. The method of manipulating a flow field according to claim 1 , wherein providing a body having a fluid jet outlet further comprises:providing an array of bodies including a first body and at least one adjacent second body; andoscillating said first body at a first amplitude, frequency, and phase; and oscillating said adjacent second body at a second amplitude, frequency, and phase.4. An actuator assembly for controlling a flow field over a surface comprising:a body extending at least partially through said surface, wherein the body is configured to oscillate at least one of vertically, horizontally, and ...

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Номер записи: 36
26-03-2015 дата публикации

REDUCED FLUID DRAG ACROSS A SOLID SURFACE WITH A TEXTURED COATING

Номер: US20150083227A1
Автор: BAHADUR Vaibhav, Bidkar Rahul Anil, Kulkarni Ambarish Jayant, LEBLANC Luc Stephane
Принадлежит: GENERAL ELECTRIC COMPANY

An article includes a substrate with a coating having asperities such that an average spacing between the asperities is between about 0.01 and about 1.5 micron. An average surface roughness of the coating is up to about 2 microns, and an average porosity of the coating is in the range from about 35% to about 70%. A material to reduce surface energy is disposed on the coating. A method for making such an article and a method for decreasing fluid drag across such an article are also provided. 1. An article comprising:a substrate;a coating disposed on the substrate, the coating comprising a plurality of asperities, wherein the coating has an average spacing between asperities in the range from about 0.01 micron to about 1.5 micron, an average surface roughness of up to about 2 microns, and an average porosity in the range from about 35% to about 70%; and a material to reduce surface energy is disposed on the coating.2. The article of claim 1 , wherein the coating comprises a ceramic claim 1 , a metal claim 1 , a polymer claim 1 , or a combination thereof.3. The article of claim 2 , wherein the ceramic comprises yttria-stabilized zirconia (YSZ) claim 2 , yttrium aluminum garnet (YAlOor YAG) claim 2 , ytterbium oxide (YbO) claim 2 , or a combination thereof.4. The article of claim 1 , wherein the material to reduce surface energy is a low surface energy material.5. The article of claim 4 , wherein the low surface energy material comprises an inorganic material claim 4 , a fluorinated material claim 4 , a polymer claim 4 , or a combination thereof.6. The article of claim 5 , wherein the fluorinated material comprises a fluorosilane claim 5 , a fluoroalkylsilane claim 5 , a fluoropolymer claim 5 , or a combination thereof.7. The article of claim 1 , wherein the average surface roughness of the coating is up to about 1.5 microns.8. The article of claim 2 , wherein the substrate is an inner surface of a pipe claim 2 , or a surface of a vessel hull.9. A method for making an ...

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Номер записи: 37
26-03-2015 дата публикации

CLADDING

Номер: US20150086276A1
Автор: Chadwick Joshua T., Harbison Austin
Принадлежит: Trelleborg Offshore U.K. Limited

A cladding section () for mounting upon an elongate member to be deployed underwater is shaped to suppress vortex induced vibration of the elongate member when it is subject to a fluid flow, the cladding section comprising at least one cylindrical or part-cylindrical portion () to seat upon the elongate member and at least one strake ( ) upstanding from the part-cylindrical portion, the cladding section being characterised in that the strake is resilient, enabling it to be deformed when subject to load and to reform following removal of the load. The cladding section may be prepared by methods involving thermoforming or moulding. 1. A cladding section for mounting upon an elongate member to be deployed underwater , the cladding section being shaped to suppress vortex induced vibration of the elongate member when it is subject to a fluid flow , the cladding section comprising at least one cylindrical or part-cylindrical portion to seat upon the elongate member and at least one stake upstanding from the part-cylindrical portion , the cladding section being characterised in that the stake is resilient , enabling it to be deformed when subject to load and to reform following removal of the load.2. A cladding section as claimed in which is a unitary thermoformed component.3. A cladding section as claimed in or in which the strake is hollow.4. A cladding section as claimed in any preceding claim in which the strake is filled with a resilient material.5. A cladding section claim 4 , as claimed in in which the stake is filled with a moulded material.6. A cladding section as claimed in or in which the strake is filled with a polyurethane material.7. A cladding section as claimed in any preceding claim which comprises a plurality of part-cylindrical portions joined by hinges claim 4 , enabling it to be reconfigured from a quasi-flat state in which the part-cylindrical portions lie side-by-side and a state in which it forms a tube for receiving the elongate member.8. A ...

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Номер записи: 38
12-03-2020 дата публикации

Fluidic Actuator For Airfoil

Номер: US20200079499A1
Автор: Shmilovich Arvin
Принадлежит: The Boeing Company

A fluidic actuator is configured to be mounted to an airfoil surface. The actuator includes a rotor supported within a housing. The rotor contains at least one generally radially extending nozzle that converges from an entry at an interior circumference of the rotor to an exit at an exterior circumference thereof, the converging shape of the nozzle assuring high velocity airflow at the nozzle exit. In one form, each nozzle also includes a curved path by which high-pressure air is enabled to induce spinning of the rotor. The fluidic actuator further includes a diffuser through which high-pressure air from the nozzles is cyclically ejected from those of the nozzles instantaneously exposed to the diffuser. In one form, the rotor spins at 300 revolutions per second and provides nozzle ejections effective to avoid boundary layer separation; i.e. to maintain an attached boundary layer flow over the airfoil. 1. A fluidic actuator for an airfoil , the fluidic actuator comprising:a housing configured for being fixed to an airfoil surface;a rotor contained within the housing, the rotor defined by an interior circumference and an exterior circumference, the rotor including at least one nozzle extending generally radially through the rotor from the interior circumference to the exterior circumference;wherein the at least one nozzle is configured to receive high-pressure air to induce spinning of the rotor within the housing; andwherein the fluidic actuator further includes a diffuser through which high-pressure air from the at least one nozzle is cyclically ejected during movement of the rotor.2. The fluidic actuator of claim 1 , wherein the housing includes a circular cavity sized to sealingly engage the exterior circumference of the rotor.3. The fluidic actuator of claim 1 , wherein the at least one nozzle is curved from an entry opening at the interior circumference to an exit opening at the exterior circumference.4. The fluidic actuator of claim 3 , wherein the entry ...

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Номер записи: 39
30-03-2017 дата публикации

WAKE CONVERGENCE DEVICE FOR A VEHICLE

Номер: US20170088196A1
Автор: Camosy Michael W.
Принадлежит:

A wake convergence device for a vehicle is provided, wherein the vehicle has a vehicle top and first and second vehicle sides each extending from the vehicle top. The vehicle includes a vehicle leading edge, a vehicle trailing edge, and a vehicle longitudinal axis. The wake convergence device includes a first side panel positioned beside and spaced from the first vehicle side and including a first side panel leading edge that transitions from forward of the vehicle trailing edge to aft of the vehicle trailing edge. The wake convergence device also includes a second side panel positioned beside and spaced from the second vehicle side and including a first side panel leading edge that transitions from forward of the vehicle trailing edge to aft of the vehicle trailing edge. 1. A wake convergence device for a vehicle having a vehicle top and first and second vehicle sides each extending from the vehicle top , the vehicle including a vehicle leading edge , a vehicle trailing edge , and a vehicle longitudinal axis , the wake convergence device comprising:a first side panel positioned beside and spaced from the first vehicle side and including a first side panel leading edge that transitions from forward of the vehicle trailing edge to aft of the vehicle trailing edge; anda second side panel positioned beside and spaced from the second vehicle side and including a first side panel leading edge that transitions from forward of the vehicle trailing edge to aft of the vehicle trailing edge.2. The wake convergence device of claim 1 , wherein the first side panel includes a first side panel leading edge center point at a center of the first side panel leading edge claim 1 , the first side panel further comprising at least one first side panel end that extends forward from the first side panel leading edge center point.3. The wake convergence device of claim 2 , wherein the at least one first side panel end extends forward substantially linearly from the first side panel ...

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Номер записи: 40
25-03-2021 дата публикации

ANTENNA HOUSING AND STRUCTURE FOR ANTENNA HOUSING

Номер: US20210091449A1
Автор: Stuible Eckart, Weber Stefan
Принадлежит:

An antenna housing includes, in at least one region which, after the antenna housing is mounted, is exposed to an incident flow from an air stream, a structure formed such that it transfers the incident air stream and the air stream present at the housing into a turbulent flow at a transfer region defined by the structure A corresponding structure is also disclosed. 112-. (canceled)13. An antenna housing in the form of a blunt body , wherein the antenna housing has a structure on at least one region which is exposed to an incident flow by an air stream after mounting of the antenna housing , wherein the structure is formed in such a way that it converts the impinging air stream and air stream present at the housing , from a substantially laminar flow into a turbulent flow at a transition region defined by the structure ,wherein:the structure is formed as a turbulator or as a microturbulator or a combination thereof,the following structures or a combination thereof are used as a turbulator: a zigzag band, a knob band, a step, a step with knob band on top, individually mounted knobs, individually mounted elevations, one or more adjacent abrupt and sharp-edged elevations with associated edges, wherein the edges point in one direction or in several directions at an angle to each other, and whereinthe antenna housing substantially has a shape of a cuboid with front, first and second side walls, rear, lid and bottom and edges therebetween with a predetermined edge radius, and the structure is arranged adjacent to or on an edge between two sides.14. The antenna housing according to claim 13 , wherein the structure is formed such that a reduction of the wind load by at least 2% is measurable at least at a predetermined reference value of a speed of an impinging air stream.15. The antenna housing according to claim 13 , wherein the structure is arranged at an area on the antenna housing where the present air stream is slightly before stalling.16. The antenna housing ...

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Номер записи: 41
19-03-2020 дата публикации

Flow restricting fluid component

Номер: US20200088555A1
Автор: Andrew CREQUE, Bryan S. Reiger, David J. Hasak, Michael D. Bestic
Принадлежит: Swagelok Co

A fluid component includes a cross-shaped body having laterally extending first and second flow ports and axially extending first and second access ports. The first flow port connected in fluid communication with the first access port by a first branch port. The second flow port connected in fluid communication with the second access port by a second branch port. The first and second access ports are connected in fluid communication by a convoluted flow restricting passage extending generally axially from the first access port to the second access port.

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Номер записи: 42
01-04-2021 дата публикации

AIRFLOW ADJUSTING APPARATUS

Номер: US20210094631A1
Автор: Dogahira Yusaku, WATANABE Naoto
Принадлежит: SUBARU CORPORATION

An airflow adjusting apparatus to be installed in a vehicle includes an airflow generator and a controller. The airflow generator is provided on an inner surface of a wheel house or on a wheel. The wheel house provides a wheel containing section of a vehicle body. The wheel is contained in the wheel containing section. The airflow generator is configured to generate an airflow that flows from the wheel containing section toward outer side in a vehicle widthwise direction. The controller is configured to control the airflow generator. 1. An airflow adjusting apparatus to be installed in a vehicle , the apparatus comprising:an airflow generator that is provided on an inner surface of a wheel house or on a wheel, the wheel house providing a wheel containing section of a vehicle body, the wheel being contained in the wheel containing section, the airflow generator being configured to generate an airflow that flows from the wheel containing section toward outer side in a vehicle widthwise direction; anda controller configured to control the airflow generator.2. The airflow adjusting apparatus according to claim 1 , wherein the airflow generator comprises a first airflow generator claim 1 , the first airflow generator being provided at least on: a surface portion claim 1 , of the inner surface of the wheel house claim 1 , on front side of the wheel; or a surface portion claim 1 , of the inner surface of the wheel house claim 1 , on rear side of the wheel; the first airflow generator being configured to generate an airflow along the surface portion on which the first airflow generator is provided.3. The airflow adjusting apparatus according to claim 1 , further comprisinga turning state detector configured to detect a turning state of a vehicle, whereinthe airflow generator comprises two or more airflow generators, andthe controller is configured to cause, when the vehicle is turning, a flow velocity of an airflow generated by the airflow generator provided on turning ...

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Номер записи: 43
28-03-2019 дата публикации

VEHICLE ASSEMBLY AND METHOD TO REDUCE BUFFETING AND GENERATE DOWNFORCE

Номер: US20190092144A1
Автор: Cunningham Andrew Thomas, Titus Matthew Arthur, Weston Keith
Принадлежит:

An exemplary vehicle flow influencing assembly includes, among other things, a downforce generator extending laterally outward from an area of a vehicle that is forward a side window. The downforce generator is configured to influence flow to reduce buffeting. A vehicle flow influencing method includes, among other things, lowering a side window to provide an opening to a passenger compartment of a vehicle, and influencing flow over the opening using a downforce generator that extends laterally outward from an area of a vehicle that is forward the side window. The influencing reducing buffeting. 1. A vehicle flow influencing assembly , comprising:a downforce generator extending laterally outward from an area of a vehicle that is forward a side window, the downforce generator configured to influence flow to reduce buffeting.2. The vehicle flow influencing assembly of claim 1 , wherein the downforce generator includes an airfoil.3. The vehicle flow influencing assembly of claim 1 , wherein the downforce generator includes a dive plane.4. The vehicle flow influencing assembly of claim 1 , wherein the area is a window sail.5. The vehicle flow influencing assembly of claim 1 , wherein the area is vertically above a beltline of the vehicle and the side window is a front side window.6. The vehicle flow influencing assembly of claim 1 , wherein the downforce generator is laterally between a side mirror and a side window opening of the vehicle.7. The vehicle flow influencing assembly of claim 1 , further comprising a gurney flap and a base of the downforce generator claim 1 , the gurney flap extending vertically from the base.8. The vehicle flow influencing assembly of claim 7 , wherein gurney flap is at a lateral side of the base.9. The vehicle flow influencing assembly of claim 7 , wherein the gurney flap is at a rear of the base relative to an orientation of the vehicle.10. The vehicle flow influencing assembly of claim 7 , wherein the gurney flap comprises both a side ...

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Номер записи: 44
28-03-2019 дата публикации

APPARATUS AND METHOD FOR REDUCING AERODYNAMIC DRAG ON TRACTOR-TRAILERS

Номер: US20190092401A1
Автор: Conlisk Albert Terrence, Prakash Shaurya, Rangharajan Kaushik Krishna, West Joseph D., Zezinka Zachary
Принадлежит:

An apparatus for reducing aerodynamic drag on a tractor-trailer includes a panel configured to extend along a length of the trailer, the panel having first and second ends and being contoured along a lengthwise direction of the panel from the first end to the second end. Another apparatus includes a panel including a base and an array of rib-like protrusions extending outwardly from the base. Another apparatus includes a panel including an inner portion and an outer portion coupled to each other along first and second seams to define a cavity and including an air inlet for allowing air influx into the cavity from free-stream air flow during transit of the tractor-trailer to transition the panel from a retracted state to a deployed state. When in the deployed state, the panel is configured to alter an external topography of the tractor-trailer. 1. An apparatus for reducing aerodynamic drag on a tractor-trailer comprising:a panel configured to extend along a length of the trailer, the panel having first and second ends and being contoured along a lengthwise direction of the panel from the first end to the second end.2. The apparatus of claim 1 , wherein the a profile of the panel is defined by a shape of partial circumference of a circle of constant radius of curvature3. The apparatus of claim 2 , wherein the radius of curvature is between approximately 83 m and approximately 84 m.4. A trailer including the apparatus of .5. An apparatus for reducing aerodynamic drag on a tractor-trailer comprising:a panel configured to extend along a length of the trailer, the panel including a base extending between first and second ends and further including an array of rib-like protrusions extending outwardly from the base.6. The apparatus of claim 5 , wherein the panel includes approximately 25 rows of the protrusions.7. The apparatus of claim 5 , wherein the protrusions each have a length claim 5 , a width claim 5 , and a height claim 5 , and wherein the lengths of the ...

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Номер записи: 45
28-03-2019 дата публикации

DOWNFORCE FEEDBACK SYSTEMS AND CONTROL LOGIC FOR ACTIVE AERODYNAMIC DEVICES OF MOTOR VEHICLES

Номер: US20190092403A1
Автор: Auden Joshua R., Bray Samantha J., Demetrio Timothy D., Fahland Jason D., Lundberg Philip C.
Принадлежит: GM GLOBAL TECHNOLOGY OPERATIONS LLC

Disclosed are downforce feedback systems for active aerodynamic devices, methods for making/using such systems, and vehicles equipped with a closed-loop downforce feedback system to govern operation of the vehicle's active aero device(s). A feedback control system for operating an active aerodynamic device of a motor vehicle includes one or more pressure sensors for detecting fluid pressures in one or more pneumatic or hydraulic actuators for moving the active aero device. A vehicle controller receives fluid pressure signals from these sensor(s), and calculates an actual downforce value from these signal(s). The controller retrieves a calibrated downforce value from mapped vehicle downforce data stored in memory, and determines if the actual downforce value differs from the calibrated value. If so, the controller determines a target position for a target downforce value for a current vehicle operating condition, and commands the actuator(s) to move the active aero device to the target position. 1. A feedback control system for operating an active aerodynamic device of a motor vehicle , the motor vehicle including a vehicle body with the active aerodynamic device movably mounted on the vehicle body , and a pneumatic or hydraulic actuator selectively operable to move the active aerodynamic device , the feedback control system comprising:a pressure sensor configured to mount to the vehicle body and fluidly connect to the pneumatic or hydraulic actuator, the pressure sensor being operable to detect fluid pressures in the pneumatic or hydraulic actuator and generate fluid pressure signals indicative thereof;a memory device storing mapped vehicle downforce data calibrated to the motor vehicle; and receive a fluid pressure signal from the pressure sensor;', 'calculate an actual downforce value from the received fluid pressure signal;', 'determine if the calculated actual downforce value differs from a calibrated downforce value retrieved from the mapped vehicle downforce ...

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Номер записи: 46
14-04-2016 дата публикации

Fairing and method

Номер: US20160102783A1
Автор: Kjetil Skaugset
Принадлежит: Statoil Petroleum ASA

A fairing device for the reduction of vortex-induced vibrations or motions, and for minimizing the drag about a substantially cylindrical element immersed in a fluid medium, comprising; a fairing rotatably mounted about the cylindrical element, the fairing comprising a shell with a mainly cylindrical cross-sectional shape with an outer diameter (D) following the outer diameter of the cylindrical element from an upward stagnation point of 0 degrees to at least +/−90 degrees, and which at +/−90 degrees continues as two fin-like portions in an aft direction, whereby the fin-like portions are convexly curved aft of +/−90 degrees thus tapering towards each other and are defining a tail end opening or gap less than the fairing standoff height. A method for mounting, storage, and deployment of the fairing device is also disclosed.

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Номер записи: 47
13-04-2017 дата публикации

DEVICES FOR CONTROLLING THE DOWNFORCE GENERATED BY A VEHICLE DURING CORNERING

Номер: US20170101139A1
Автор: Parry-Williams Dan, Slight Arthur
Принадлежит: McLaren Automative Limited

An automobile comprising first and second flaps provided on either side of a centreline on the underside of the automobile is provided. Each flap is deployable from first positions that extend minimally into the flow to respective second positions where each flap extends maximally into the flow of air when the automobile is in motion to reduce the downforce generated by the automobile. A control unit adapted to receive inputs that indicate the dynamic state of the automobile is further provided. The control unit select positions of the first and second flaps depending on the dynamic state to control the downforce generated by the automobile. If the inputs indicate that the automobile is cornering, the positions of the first and second flaps are selected so as to counter roll of the automobile. 1. An automobile comprising:a first and a second flap provided on the underside of the automobile, the first and second flaps being positioned on either side of a centreline of the automobile, wherein each flap is deployable from a respective first position in which, when the automobile is in motion, each flap extends minimally into the flow of air beneath the automobile, up to a respective second position in which, when the automobile is in motion, each flap extends maximally into the flow of air beneath the automobile so as to reduce the downforce generated by the automobile; anda control unit adapted to receive one or more inputs that indicate the dynamic state of the automobile and select positions of the first and second flaps between their respective first and second positions, the positions of the first and second flaps being chosen in dependence on the said dynamic state so as to control the downforce generated by the automobile, wherein if the inputs indicate that the automobile is cornering, the positions of the first and second flaps are selected so as to counter roll of the automobile.2. An automobile as claimed in claim 1 , wherein the control unit is configured ...

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Номер записи: 48
23-04-2015 дата публикации

ACTIVE AND PASSIVE BOUNDARY LAYER CONTROL FOR VEHICLE DRAG REDUCTION

Номер: US20150108787A1
Автор: Schmidt Peter
Принадлежит:

An active and passive boundary layer control system and method for reducing boundary layer separation and the resulting form drag from ground vehicles. Tubings with multiple venturis connected in series are attached to the side and/or roof of the ground vehicle. A flow of compressed air is created by an engine auxiliary, e.g., a turbocharger or a supercharger, or by a designated blower and injected into the tubings. Suction created by the venturis actively removes decelerated fluid from the boundary layer and keeps the boundary layer flow attached. Optionally, the system exhausts the air in concentrated free jets along the vehicle body to a series of passive boundary layer control devices, such as vortex generators. 1. A device for reducing aerodynamic drag of a ground vehicle , the device comprising:a tubing having an intake port, an exit port, and a plurality of venturis; and,a compressed air source being fluidly connected to the intake port;wherein the plurality of venturis is disposed between the intake port and the exit port;wherein each venturi from among the plurality of venturis has a throat and a venturi opening on an outer periphery of the venturi to remove a portion of a fluid from a boundary layer of the ground vehicle; and,wherein a venturi from among the plurality of venturis being disposed closer to the intake port has at least one of a larger throat cross-section and a larger venturi opening diameter than a venturi being disposed closer to the exit port.2. The device according to claim 1 , wherein the compressed air source is selected from the group consisting of an engine auxiliary and a dedicated blower.3. The device according to claim 1 , wherein the compressed air source is controlled by an engine control unit to inject compressed air into the intake port only when the ground vehicle is travelling at a predetermined speed or faster.4. The device according to claim 1 , wherein the plurality of venturis is connected in series.5. The device ...

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Номер записи: 49
21-04-2016 дата публикации

Perforated surface for suction-type laminar flow control

Номер: US20160107746A1
Автор: Luby Weaver, Sean Tiwari
Принадлежит: Rohr Inc

An apparatus is provided for promoting laminar flow. The apparatus includes a panel extending between an interior surface and an exterior air flow surface. The panel includes a plurality of macro apertures and a plurality of micro apertures. A first one of the macro apertures extends into the panel from the interior surface. A first one of the micro apertures extends into the panel from the exterior air flow surface and is fluidly coupled with the first one of the macro apertures.

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Номер записи: 50
04-04-2019 дата публикации

TURBULENCE GENERATION SYSTEM

Номер: US20190101143A1
Автор: McKillen James T., Metka Matthew L.
Принадлежит:

A turbulence generation system includes a vane assembly to direct airflow from a nozzle. The vane assembly includes at least two vertically oriented nozzle contraction vanes, a pair of vertically oriented nozzle exit vanes, and at least one horizontally oriented vane. The nozzle contraction vanes are located within the nozzle upstream of a nozzle air outlet. Each nozzle contraction vane rotationally moves independent of the other nozzle contraction vane to generate airflow pressure loss, turbulence and/or flow vectoring. The nozzle exit vanes are downstream of the air outlet and rotationally move to generate higher angles of dynamic yaw or a quick yaw input. The nozzle exit vanes are positioned laterally inward from first and second sidewalls of the nozzle. The horizontally oriented vane is positioned downstream of nozzle contraction vanes and upstream of the nozzle exit vanes and rotationally moves to generate up-wash or downwash. 1. A turbulence generation system for use in aerodynamic and acoustic testing of a vehicle comprising:a contraction section including a nozzle having an air inlet and an air outlet; and at least two vertically oriented nozzle contraction vanes located within the nozzle upstream of the air outlet, each nozzle contraction vane is configured to rotationally move independent of the other nozzle contraction vane to generate airflow pressure loss, turbulence and/or flow vectoring,', 'a pair of vertically oriented nozzle exit vanes downstream of the air outlet and configured to rotationally move to generate dynamic yaw, one of the nozzle exit vanes positioned laterally inward from a first sidewall of the nozzle and the other nozzle exit vane positioned laterally inward from a second sidewall of the nozzle which is laterally spaced from the first sidewall, and', 'at least one horizontally oriented vane positioned downstream of nozzle contraction vanes and upstream of the nozzle exit vanes and configured to rotationally move to generate up-wash or ...

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Номер записи: 51
03-07-2014 дата публикации

Switchable Vortex Generator and Array Formed Therewith, and Uses of the Same

Номер: US20140186180A1
Автор: Christian Bolzmacher, Karin Bauer, Klaus-Peter Neitzke, Winfried Kupke
Принадлежит: AIRBUS OPERATIONS GMBH

A vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests.

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Номер записи: 52
20-04-2017 дата публикации

TOTAL ISOLATION DIVERTER VALVE

Номер: US20170108020A1
Автор: ANDREIS Diego, BUTERA Francesco
Принадлежит:

The invention describes a total isolation diverter valve comprising a valve body whereon a main inlet conduit for inletting a fluid, a first outlet conduit for outletting the fluid and at least one second outlet conduit for outletting the fluid are obtained. The first outlet conduit for outletting the fluid is provided with a first fluid adhesion inner surface and the second fluid outlet conduit is provided with a second fluid adhesion inner surface. Between the main fluid inlet conduit and the two fluid outlet conduits a connection channel is interposed. On the connection channel at least one device for perturbing at least one of the first fluid adhesion inner surface and the second fluid adhesion inner surface is provided. The perturbation device is configured so as to cause a deviation of the fluid flow from the first fluid outlet conduit to the second fluid outlet conduit or vice-versa by exploiting a physical effect called Coand{hacek over (a)} effect. The perturbation device comprises at least one perturbation orifice, which faces the first fluid adhesion inner surface, and at least one opening/closing element, configured for opening and sealingly closing a respective perturbation orifice. 110121416142016221214162420221416. Total isolation diverter valve comprising a valve body () whereon a main fluid inlet conduit () for inletting a fluid , a first fluid outlet conduit () for outletting the fluid and at least one second fluid outlet conduit () for outletting the fluid are obtained , wherein the first fluid outlet conduit () is provided with a first fluid adhesion inner surface () and the second fluid outlet conduit () is provided with a second fluid adhesion inner surface () , between the main fluid inlet conduit () and said first () and second () fluid outlet conduits a connection channel () being interposed on which at least one device for perturbing at least one of said first fluid adhesion inner surface () and said second fluid adhesion inner surface () ...

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Номер записи: 53
02-04-2020 дата публикации

Flow Guide Body For An Aircraft

Номер: US20200102066A1
Автор: Bruno Stefes, Jakob Lohse, Matthias BAUER
Принадлежит: AIRBUS OPERATIONS GMBH, Navasto GmbH

A flow guide body for an aircraft includes a main body having an outer aerodynamic surface having a plurality of outlet openings, and flow control devices, each having an inlet, an interaction chamber, a first outlet and a second outlet. A first control inlet is connected to the interaction chamber at the first side of the chamber axis. The outlets are each connected to outlet openings in the aerodynamic surface. Each outlet has a control outlet. A second flow control device is arranged such that one outlet is connected with the inlet of the first flow control device. One of the control outlets of the first flow control device is connected to the first control inlet of the first flow control device, and the other of the control outlets of the first flow control device is connected to the first control inlet of the second flow control device.

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Номер записи: 54
09-06-2022 дата публикации

PIVOTING CAB FAIRING

Номер: US20220177056A1
Автор: POLZIN Jon David, Schuh Steven J.
Принадлежит:

The present disclosure is directed to a rotatable fairing panel at a rear end of a sleeper cab. The rotatable fairing panel covers an opening between a trailer attached to a vehicle and the sleeper cab of the vehicle. The rotatable fairing panel has a closed position and an opened position. At least one locking assembly locks the rotatable fairing panel in place when in the closed position. The at least one locking assembly is configured to be unlocked by a user such that the rotatable fairing panel may be rotated from the closed position to the opened position such that a user may access the opening between the trailer attached to the vehicle and the sleeper cab of the vehicle. The at least one locking assembly automatically locks when the user rotates the rotatable fairing panel into the closed position. 1. A vehicle , comprising:a sleeper cab including a front end and a rear end opposite to the front end;a first fairing portion protruding from the rear end of the sleeper cab, the first fairing portion including a first external surface and a first internal surface opposite to the first external surface; a first position in which the first outer surface and the first external surface define a first aerodynamic surface; and', 'a second position in which the first outer surface is at an angle of 90-degrees or less to the first external surface., 'a first fairing panel hingedly coupled to the first fairing portion, the first fairing panel having a first outer surface and a first inner surface opposite to the first outer surface, the first fairing panel moveable between2. The vehicle of claim 1 , further comprising a first locking assembly including:a first male component on the internal surface of the first fairing portion;a first female component on the inner surface of the first fairing panel, the first female component configured to receive the first male component to lock the first locking assembly; anda pull component in mechanical cooperation with the female ...

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Номер записи: 55
09-06-2022 дата публикации

SYSTEM FOR A TOWER SEGMENT OF A TOWER, A RESPECTIVE TOWER SEGMENT, AND A WIND TURBINE HAVING A TOWER SEGMENT

Номер: US20220178391A1
Автор: Voss Stefan Bernhard
Принадлежит:

A system for a tower segment of a tower is presented, wherein the tower segment is configured for forming at least partially a part of a tower for carrying a structure, in particular for supporting a nacelle of a horizontal-axis wind turbine or a machine house of a vertical-axis wind turbine. The system is configured to be attached, arranged, and/or mounted to the tower segment and comprises at least an airflow manipulation arrangement and a support arrangement. The airflow manipulation arrangement includes an airflow manipulator which is configured for affecting an airflow around the tower segment. The support arrangement is configured for supporting the airflow manipulation arrangement and for mounting the airflow manipulation arrangement to the tower segment. The airflow manipulation arrangement and the support arrangement are configured such, when mounted to the tower segment, that the airflow manipulator projects a tower diameter in radial direction by at least 5%, in particular at least 10%, preferred at least 15%, in particular not more than 30%, further in particular not more than 20%, of the tower diameter, or that the airflow manipulator is essentially parallel to the tower segment. By this, an effective measure against vortex shedding effects is put in place. 110510610010105106102103. A system for a tower segment ( , ) of a tower () of a wind turbine () , the tower segment ( , ) having a longitudinal direction () and a radial direction () , the system comprising:{'b': 130', '131, 'an airflow manipulation arrangement () having an airflow manipulator (), and'}{'b': 120', '130', '130', '105', '106, 'a support arrangement () configured for supporting the airflow manipulation arrangement () and for mounting the airflow manipulation arrangement () to the tower segment (, ),'}{'b': 130', '120', '105', '106', '131', '103', '104', '105', '106', '105', '106', '131, 'wherein the airflow manipulation arrangement () and the support arrangement () are configured such, ...

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Номер записи: 56
09-04-2020 дата публикации

Skin grooves used for directing fluid on aircraft, landcraft, spacecraft, and watercraft related vehicles or propelled/projectile objects

Номер: US20200108916A1
Автор: Taylor DiAnte&#39; Brown
Принадлежит: Taylor DiAnte&#39; Brown

The skin grooves provide a methodology in directing the flow of fluid on multiple types of vehicles and objects. The grooves within the skin allow the fluid to be directed. The grooves work similarly to a water slide. The groove within the water slide directs the water accordingly. By utilizing the same method of directing the flow of fluid on an aircraft, landcraft, spacecraft, and watercraft related vehicles or propelled/projectile objects, it provides limitations to drag.

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Номер записи: 57
10-05-2018 дата публикации

CONTAINERS, BOTTLES, DRUMS, VATS, AND TANKS HAVING A SLIPPERY SURFACE

Номер: US20180127594A1
Автор: Aizenberg Joanna, AIZENBERG Michael, Kang Sung Hoon, Kim Philseok, WONG Tak Sing
Принадлежит:

The present disclosure describes a strategy to create self-healing, slippery liquid-infused porous surfaces. Roughened (e.g., porous) surfaces can be utilized to lock in place a lubricating fluid, referred to herein as Liquid B to repel a wide range of materials, referred to herein as Object A (Solid A or Liquid A). Slippery liquid-infused porous surfaces outperforms other conventional surfaces in its capability to repel various simple and complex liquids (water, hydrocarbons, crude oil and blood), maintain low-contact-angle hysteresis (<2.5°), quickly restore liquid-repellency after physical damage (within 0.1-1 s), resist ice, microorganisms and insects adhesion, and function at high pressures (up to at least 690 atm). Some exemplary application where slippery liquid-infused porous surfaces will be useful include energy-efficient fluid handling and transportation, optical sensing, medicine, and as self-cleaning, and anti-fouling materials operating in extreme environments. 184-. (canceled)85. A container comprising a slippery surface , wherein the slippery surface comprises:a roughened surface; anda lubricating liquid having an affinity for the roughened surface,wherein the affinity is such that the lubricating liquid spontaneously wets the roughened surface and adheres within the roughened surface to form a stabilized liquid overlayer forming the slippery surface.86. The container according to claim 85 , wherein the roughened surface is chemically functionalized with one or more chemical functional groups claim 85 , andwherein the lubricating liquid has an affinity for the one or more chemical functional groups.87. The container according to claim 86 , wherein the roughened surface has a roughness factor that is greater than 1 claim 86 , wherein the roughness factor is defined as a ratio between a real surface area of the roughened surface and a projected surface area of the roughened surface.88. The container according to claim 87 , wherein the roughness factor ...

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Номер записи: 58
03-06-2021 дата публикации

Method and Apparatus of Plasma Flow Control for Drag Reduction

Номер: US20210164503A1
Автор: Corke Thomas C., Thomas Flint O.
Принадлежит:

A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow. 1. A plasma plate comprising: a dielectric;', 'a first electrode exposed to a fluid flow;', 'a second electrode separated from the fluid flow by the dielectric;', 'a pulsed direct current power supply providing a first voltage to the first electrode and a second voltage to the second electrode; and, 'a plurality of plasma actuators positioned on a surface, each plasma actuator comprising the plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow, and', 'the exposed electrode is adapted to produce opposing spanwise blowing with a stagnation line in a space between neighboring covered electrodes., 'a bus operably connected to distribute power to the plasma actuators, positioned to minimize flow disturbances, wherein2. The plasma plate of wherein the plasma actuators are arranged to produce a reduction in the drag of the fluid flow across the surface.3. The plasma plate of wherein the reduction in the drag is accomplished by smoothing low-speed streaks to prevent streak transient growth instability.4. The plasma plate of wherein the plasma actuators are arranged to control stall as the fluid flows over the surface.5. The plasma plate of wherein the plasma plate is positioned internally in a ...

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Номер записи: 59
28-05-2015 дата публикации

STRUCTURALLY ENHANCED PLASTICS WITH FILLER REINFORCEMENTS

Номер: US20150144834A1
Автор: Johnson, SR. WILLIAM L.
Принадлежит:

A composition comprising a fluid, and a material dispersed in the fluid, the material made up of particles having a complex three dimensional surface area such as a sharp blade-like surface, the particles having an aspect ratio larger than 0.7 for promoting kinetic boundary layer mixing in a non-linear-viscosity zone. The composition may further include an additive dispersed in the fluid. The fluid may be a thermopolymer material. A method of extruding the fluid includes feeding the fluid into an extruder, feeding additives into the extruder, feeding a material into the extruder, passing the material through a mixing zone in the extruder to disperse the material within the fluid wherein the material migrates to a boundary layer of the fluid to promote kinetic mixing of the additives within the fluid, the kinetic mixing taking place in a non-linear viscosity zone. 162-. (canceled)63. An improved additive for use in a fluid flowing through equipment where the flowing fluid has a stream velocity (U) and a boundary layer flow velocity (u) , wherein (U) and (u) are affected by filler loading , heat transfer , shear effects and chemical reactions , wherein the improvement comprises:particles having a sharp conchoidal surface and a complex three-dimensional surface area, said particles having a diameter approximately equal to a theoretical starting diameter;wherein said particle theoretical starting diameter is defined by a height measured perpendicular to a surface where u=0.99U.64. The improved additive according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , sharp surface.65. The improved additive according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , sharp claim 63 , blade-like surface.66. The improved additive according to wherein said complex three-dimensional surface area comprises a smooth claim 63 , curved surface.67. The improved additive according to wherein said particles comprise a ...

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Номер записи: 60
17-05-2018 дата публикации

TWIN-FIN FAIRING

Номер: US20180135666A1
Автор: Meijer Karst, VAN BELKOM Arnoldus
Принадлежит:

A fairing () for improving fluid flow around a circular-cylindrical object comprises a first fairing-element () and a second fairing-element (), which are releasable relative to one another. The fairing-elements are easy to manufacture, compactly stackable, and easy to install around the object. In installed condition, the first fairing-element and the second fairing-element are mutually connected in circumferential direction of the fairing, while forming a twin-fin fairing, which reduces vortex-induced vibrations around the object, while providing favourable flow resistance, and without performing galloping motions. 1. Twin-fin fairing for improving fluid flow around a circular-cylindrical object , wherein the fairing has an operation condition in which:the fairing is installed around said circular-cylindrical object and, under influence of said fluid flow, is reciprocally rotatable relative to the object about the longitudinal direction of the object,the circumferential direction and the longitudinal direction of the circular-cylindrical object are defining a corresponding circumferential direction of the fairing and a corresponding longitudinal direction of the fairing, respectively, andthe fairing comprises, along at least one subrange of its overall-range in its longitudinal direction, and as seen in perpendicular cross-section relative to its longitudinal direction, at least one U-shaped portion, respectively, which according to the curvature of its U-shape envelopes the object in the circumferential direction of the fairing, and wherein the fairing comprises a first fin and a second fin, which are formed by the at least one U-shaped portion, and which are protruding in a free-ending manner relative to the object, according to the two free-ending legs, respectively, of said U-shape, and which make the fairing rotate according to said reciprocal rotatability under influence of said fluid flow,characterized in thatthe fairing comprises a first fairing-element ...

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Номер записи: 61
09-05-2019 дата публикации

SWIM SPA HAVING A WALL INSERT

Номер: US20190134479A1
Автор: JR. David R., Livingston
Принадлежит:

An improved swim spa is described which has a tank having a head end and a foot end filled with water. A forward current is created by pumping equipment which directs the forward current from a head end of the tank, past a swimmer in the water to a foot end of the tank. The pumping equipment may be attached to a removable wall insert to which may be removed to allow easy repair and maintenance. The forward current allows the swimmer to swim in place. The width of the forward current is chosen to be at least twice its depth. A diverter at the foot end of the tank has a curved surface for redirecting the forward current toward the sidewalls and then back toward the head wall in a horizontal plane and downward and back toward the head wall in a vertical plane. 1. A more efficient swim spa requiring less energy to operate , comprising: i. a first side wall and a second side wall each having a head end and a foot end;', 'ii. a foot wall positioned substantially perpendicular to the side walls, thereby connecting the foot ends of the side walls;', 'iii. a head wall positioned substantially perpendicular to the side walls, thereby connecting the head ends of the side walls in order to create the tank;, 'a. a tank having a head end and a foot end, the tank being filled with a volume of water, the tank comprisingb. pumping equipment that includes at least two side-by-side propellers that are driven by a single drive and at approximately equal speed that create a single forward current of water limited to one or more output windows at a surface of the water, wherein the single forward current of water has a width at least twice a height of the forward current of water;c. a nozzle attached to the one or more output windows, wherein the nozzle is adapted to be continuously adjustable to adjust a width and height or angle of the forward current of water received from the output window such that the nozzle is capable of directing the single forward current of water slightly below ...

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Номер записи: 62
08-09-2022 дата публикации

FIRST FLUSH DIVERTER SYSTEM

Номер: US20220282743A1
Автор: FENTON REGAN Renata, GARCÍA VELÁZQUEZ Jesús Hiram, LOMNITZ CLIMENT Enrique
Принадлежит:

A system for diverting an adjustable number of liters of a first flush, which has a modular, in series or parallel configuration to expand the maximum adjustable capacity. Additionally, a rainwater collection system for delivery of said rainwater to a domestic system for use thereof. The system comprises first flush diverter, screening stage, filtering stages, buffering stage, settling/resting stage, disinfection and/or purification stage. 120-. (canceled)21. A system for diverting an adjustable amount of water , wherein rainwater runs through a main pipe , said system comprising:at least one closed diverter container, wherein said diverter container has a maximum height and volumetric capacity, a lower part of said diverter container comprises at least one water outlet valve, and an upper part of said diverter container comprises at least one water inlet defined by an orifice having a preset area and shape on the diverter container surface;one pipe per the at least one closed diverter container, said pipe including a length at least partially similar to the height of the diverter container, and including an area and shape substantially equal to that of the water inlet orifice where the pipe is vertically inserted, such that the pipe is attached to the diverter container, with the pipe lower end remaining inside and at the lower part of the diverter container, and with the pipe upper end remaining at least at level with the diverter container upper surface; andat least one three-way connection, wherein the first and second outlets of said at least one three-way connection are attached to the main pipe through which water flows in the direction from the first outlet to the second outlet, such that the third outlet of said at least one three-way connection is pointing downwardly and is attached to the upper end of the corresponding pipe of said at least one diverter container;wherein the said at least one three-way connection is above said at least one diverter ...

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Номер записи: 63
09-05-2019 дата публикации

METHODS AND APPARATUS FOR CONTROLLING FLOW FIELDS

Номер: US20190136881A1
Автор: Amitay Michael, Gildersleeve Samantha
Принадлежит: RENSSELAER POLYTECHNIC INSTITUTE

Methods and systems for controlling a fluid flow field near a surface are disclosed. In some embodiments, the system includes an array of oscillating bodies disposed on the surface to provide physical modification to the flow field. Fluid jets are also emitted from an outlet in the oscillating body to provide virtual modification of the flow field through momentum addition. Fluid jet sources, including synthetic jet generators such as piezoelectric drivers and sources of compressed fluids such as air or water, are positioned to be in fluid communication with the outlet at intervals during the oscillation of the oscillating body. Controlling the oscillation amplitude and frequency of the body, as well as the location of oscillating body outlets and frequency of fluid jet emission, have advantageous effects for the surface such as improved heat transfer properties and reduction in structural vibration and noise. 1. A method of manipulating a flow field over a surface comprising:providing a body having a fluid jet outlet;oscillating said body in said flow field via an oscillator powered by a motor, said oscillator positioned to oscillate said body;generating a fluid jet; andemitting said fluid jet from said fluid jet outlet into said flow field.2. The method of manipulating a flow field according to claim 1 , wherein said fluid jet is generated from a compressed fluid source claim 1 , a synthetic jet generator claim 1 , an external flow stream claim 1 , or a combination thereof.3. The method of manipulating a flow field according to claim 1 , wherein providing a body having a fluid jet outlet further comprises:providing an array of bodies including a first body and an adjacent second body; andoscillating said first body at a first amplitude, frequency, and phase; and oscillating said adjacent second body at a second amplitude, frequency, and phase.4. An actuator assembly for controlling a flow field over a surface comprising:an oscillator, said oscillator positioned to ...

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Номер записи: 64
09-05-2019 дата публикации

COMMUNICATION OR SIGNALING SYSTEM THAT INCLUDES A VARIABLE PRESSURE ACTIVATED POROUS VOLUME EMITTER ALONG WITH RELATED METHODS

Номер: US20190139378A1
Автор: Cole Aaron B., Pienkos Jules E.
Принадлежит:

An exemplary communication or signaling system that includes an energy emission system that can include a control system, a fluid reservoir, fluid transfer structures, a fluid pumping system, an emission structure, an enclosure extending away from the fluid emission structure, a fluid recovery system, and a lens structure adapted to pass energy through the lens structure. The emission structure can include a porous structure and/or structure(s) with a number of fluid emission sections that generate one or more fluid structures such as droplets or other fluid shapes which increase or decrease fluid surface area on the fluid emission structure and thereby increase or decrease energy emissions or absorption on or in relation to the fluid emission structure. The control system can selectively modulate pressure/fluid transfer via the pump into the fluid transfer structures which alter energy emission or absorption that can be detected at a distance. 1. A selective communication or signaling system comprising:a porous media comprising a first and an opposing second side, the first side is formed with an emissive surface having a first surface area, the porous media formed with internal structures that carry fluid in deterministic flow paths such that the porous media causes unsteady flow fields in a fluid resulting in said fluid passing to said first surface area of the emissive surface, wherein the emissive surface is formed with a plurality of apertures configured to selectively exude fluid from the porous media as semi-spherical shapes, droplet or beads form to create a second surface area that is greater than said first surface area;a fluid reservoir including a thermal control system configured to store, collect, transfer, thermally regulate, and/or filter the fluid;a fluid pump coupled to fluid reservoir and the fluid reservoir that selectively pumps said fluid from the reservoir;an input valve in fluid communication with the fluid reservoir and the second side of ...

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Номер записи: 65
04-06-2015 дата публикации

CONSTRUCTION AND A TENSION ELEMENT COMPRISING A CABLE AND ONE OR MORE STRAKES

Номер: US20150152610A1
Автор: Georgakis Christos Thomas, Kleissl Kenneth
Принадлежит:

The invention provides a construction comprising a structural element and at least one cable () arranged in tension to carry at least a part of the weight of the structural element. The cable defines an outer surface () onto which at least one strake () forms a protrusion for reducing rain and wind induced vibrations. The strake has a height being a distance from a strake root part connected to the outer surface of the cable and a strake end part terminating the strake outwards away from the cable, and the strake has a width being transverse to the height, the width decreasing in the direction from the strake root part towards the strake end part. The height is less than 5 percent of the diameter of the cable. Furthermore, the strake comprises a first strake surface portion facing away from the cable, which first strake surface portion is concave or straight. 1. A construction comprising a structural element and at least one cable arranged in tension to carry at least a part of the weight of the structural element , the cable defining an outer surface onto which at least one strake forms a protrusion for reducing rain and wind induced vibrations , wherein the strake has a height being a distance from a strake root part connected to the outer surface of the cable and a strake end part terminating the strake outwards away from the cable , the strake having a width being transverse to the height , the width decreasing in the direction from the strake root part towards the strake end part , wherein the height is less than 5 percent of the diameter of the cable , and wherein the strake comprises a first strake surface portion facing away from the cable , the first strake surface portion being concave or straight , and wherein the first strake surface portion extends from the strake root part to the strake end part to provide a ramp for rivulets flowing longitudinally along the outer surface of the cable.2. A construction according to claim 1 , wherein the first strake ...

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Номер записи: 66
04-06-2015 дата публикации

CONSTRUCTION AND A TENSION ELEMENT COMPRISING A CABLE AND A PLURALITY OF STRAKES

Номер: US20150152611A1
Автор: Georgakis Christos Thomas, Kleissl Kenneth
Принадлежит:

The invention provides a construction comprising a structural element and at least one cable () arranged in tension to carry at least a part of the weight of the structural element. The cable defines an outer surface () onto which a plurality of strakes () form protrusions for reducing rain and wind induced vibrations. Each strake has a height being a distance from a strake root part connected to the outer surface of the cable and a strake end part terminating the strake outwards form the cable, a width being transverse to the height, and a length transverse to the height and width and along which length the strake is connected to the cable. The length of each strake is shorter than the circumference of the outer surface, and the height is less than 5 percent of the diameter of the cable. 1. A construction comprising a structural element and at least one cable arranged in tension to carry at least a part of the weight of the structural element , the cable defining an outer surface onto which a plurality of strakes form protrusions for reducing rain and wind induced vibrations , wherein each strake has a height being a distance from a strake root part connected to the outer surface of the cable and a strake end part terminating the strake outwards form the cable , a width being transverse to the height , and a length transverse to the height and width and along which length the strake is connected to the cable , the length of each strake being shorter than the circumference of the outer surface , wherein the height is less than 5 percent of the diameter of the cable , and wherein the longitudinal direction of the strake extends in a direction substantially orthogonal to the longitudinal direction of the outer surface.2. (canceled)3. A construction according to claim 1 , wherein the length of each strake is less than half of the circumference of the outer surface.4. A construction according to claim 1 , wherein the cable defines a plurality of first cross-sections ...

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Номер записи: 67
21-08-2014 дата публикации

Devices and methods for programming fluid flow using sequenced microstructures

Номер: US20140230909A1
Автор: Dino Di Carlo, Elodie Sollier, Hamed AMINI
Принадлежит: UNIVERSITY OF CALIFORNIA

A microfluidic platform is disclosed that uses obstacles placed at particular location(s) within the channel cross-section to turn and stretch fluid. The asymmetric flow behavior upstream and downstream of the obstacle(s) due to fluid inertia manifests itself as a total deformation of the topology of streamlines that effectively creates a tunable net secondary flow. The system and methods passively creates strong secondary flows at moderate to high flow rates in microchannels. These flows can be accurately controlled by the numbers and particular geometric placement of the obstacle(s) within the channel.

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Номер записи: 68
15-09-2022 дата публикации

Helical Strake Attachment for Tubular Structural Members

Номер: US20220290791A1
Автор: Boe Brandon G., Christman Bernie, Fairbairn Mark H., Fonville, Hunter Richard J., II Harold W., Jackson Aubrey L., Ramsay David M., Slocum Richard M., Sterny Daniel J., Van Brunt Troy, Van Wyhe Jason
Принадлежит:

A helical strake pole system that includes a tubular pole having a longitudinal axis and threaded attachment points. The system further includes a helical strake fin disposed circumferentially around a portion of the tubular pole along the longitudinal axis. The system further includes couplers disposed on the tubular pole. The couplers are configured such that each coupler has a first portion with a slot configured to receive an upper portion of the helical strake fin and a second portion configured to removably coupled to a threaded attachment point of the tubular pole. In addition, each coupler is configured to position a portion of the helical strake fin substantially perpendicular to a surface of the tubular pole. 120.-. (canceled)21. A helical strake system , comprising:a tubular structural member having a longitudinal axis and comprising a plurality of threaded attachment points;a helical strake fin disposed circumferentially around a portion of the tubular structural member along the longitudinal axis;a plurality of couplers disposed on the tubular structural member, wherein: a first portion comprising a slot configured to receive an upper portion of the helical strake fin; and', 'a second portion configured to be removably coupled to a threaded attachment point of the tubular structural member; and', 'each coupler configured to position a portion of the helical strake fin substantially perpendicular to a surface of the tubular structural member., 'each coupler comprises22. The system of claim 21 , wherein: a respective first attachment point on one side of the helical strake fin; and', 'a respective second attachment point on an opposing side of the helical strake fin., 'the second portion of the coupler is coupled to23. The system of claim 21 , wherein: substantially cover one side of the helical strake fin disposed within the coupler; and', 'partially cover an opposing side of the helical strake fin disposed within the coupler., 'the slot in the first ...

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Номер записи: 69
16-05-2019 дата публикации

METHOD AND APPARATUS FOR COMBINED ANEMOMETER AND PLASMA ACTUATOR

Номер: US20190145443A1
Автор: Behroozi Cyrus, Julian Dominico P., Smullin Sylvia Joan
Принадлежит:

A method and a device for measuring a fluid flow characteristic of an ambient fluid and modifying fluid flow of the ambient fluid, the method including: applying a first voltage between a first electrode and a second electrode, the first voltage being sufficient to generate a plasma in the first space; applying a second voltage between the first electrode and a third electrode, the second voltage being sufficient to generate a plasma in the second space; measuring a first current between the first and second electrodes, and a second current between the first and third electrodes; determining a fluid flow characteristic of the ambient fluid; and applying a third voltage between the first and second electrodes, the third voltage being sufficient to generate a plasma in the first space sufficient to modify fluid flow of the ambient fluid in the first direction in the first space. 1. A method for measuring a fluid flow characteristic of an ambient fluid and modifying fluid flow of the ambient fluid , the method comprising:applying a first voltage between a first electrode and a second electrode electrically insulated from the first electrode, the first electrode extending in a plane and the second electrode extending along the plane, the first and second electrodes being laterally spaced apart from each other in a first direction in the plane, the ambient fluid at least partially occupying a first space adjacent to the first electrode,wherein the first voltage is sufficient to generate a plasma in the first space;simultaneously to applying the first voltage, applying a second voltage between the first electrode and a third electrode electrically insulated from the first electrode, the third electrode extending along the plane and laterally spaced apart from the first electrode in a second direction in the plane opposite the first direction, the ambient fluid at least partially occupying a second space adjacent to the first electrode and opposite to the first space, ...

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Номер записи: 70
31-05-2018 дата публикации

ACTUATORS FOR FLOW CONTROL AT SURFACES OF AERODYNAMIC PROFILES

Номер: US20180149178A1
Автор: CASPARI Ralf, ERMANN Emanuel, HELLER Gerd, JORDAN Nicole, KONIGORSKI Detlev, SCHNÄUBELT Stefan, WEICHWALD Robert
Принадлежит:

An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators. 1. An assembly for arrangement in or at the surface of an aerodynamic profile , wherein the assembly comprises an array of actuators , which are designed as piezo actuators and plasma actuators , wherein surface elements are provided on a surface of the assembly.2. The assembly according to claim 1 , wherein the plasma actuators are designed to be miniaturized.3. The assembly according to claim 2 , wherein the plasma actuators are designed as SDBD or as MEE actuators.4. The assembly according to claim 1 , wherein the array comprises at least 10000 actuators per square meter.5. The assembly according to claim 1 , wherein the surface elements comprise a bionic structure.6. The assembly according to claim 1 , wherein the surface elements comprise different materials with different characteristics.7. The assembly according to claim 1 , wherein at least a pair of two piezo actuators claim 1 , which are mechanically coupled with each other for creating a piezo transformer claim 1 , is provided.8. The assembly according to claim 1 , wherein individual different actuator types are repeatedly arranged next to each other in form of an array (actuator A next to actuator B claim 1 , next to actuator C claim 1 , next to actuator A claim 1 , and so on); an arrangement of groups of actuators of the same type next to each other is also possible (as a chess board pattern with two actuator types and alternatingly with three or more types of actuators claim 1 , respectively).9. An aerodynamic profile having an assembly arranged on its surface claim 1 , the assembly comprising an array of actuators claim 1 , which are designed as piezo actuators and plasma actuators claim 1 , wherein surface elements are provided on a surface of the assembly.10. (canceled)11. A method of measuring at least one operating parameter of at least ...

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Номер записи: 71
07-05-2020 дата публикации

VIV SUPPRESSION STRAKE ASSEMBLY

Номер: US20200141517A1
Автор: ESSELBRUGGE Martin, STEENHUIS André Luur Jan
Принадлежит: BLUEMARINE OFFSHORE YARD SERVICE B.V.

Vortex Induced Vibration (VIV) suppression strakes, in particular VIV suppression strakes are arranged on subsea pipelines. A VIV suppression strake assembly includes a strake fin support shell that is configured to be arranged against the outer surface of a section of pipe and at least one strake fin having a fin tip and a fin base. The strake fin support shell includes an aperture that is configured for inserting the fin therein, and the fin is provided at the fin base with an anchor, which anchor is configured for engaging the fin support shell on the pipe side of the aperture. The aperture is a slot dimensioned to allow the fin to be inserted in the slot from the pipe side of the slot with the fin tip leading until the fin base engages the shell. 2. The VIV suppression strake assembly according to claim 1 , wherein a width of the slot is less than the combined thicknesses of the anchor at the fin base.3. The VIV suppression strake assembly according to claim 1 , wherein:the stiffness of the strake fin support shell is greater than the stiffness of the strake fin.4. The VIV suppression strake assembly according to claim 1 , wherein:the strake fin support shell and the strake fin are made of materials having different properties.5. The VIV suppression strake assembly according to claim 1 , wherein:the strake fin support shell is made of a polyolefin.6. The VIV suppression strake assembly according to claim 1 , wherein:the strake fin is made of a material from a group comprising polyurethane, vulcanised elastomer, and a plastomer.7. The VIV suppression strake assembly according to claim 1 , wherein:the shell comprises on the pipe side of the aperture a seat for the anchor.8. The VIV suppression strake assembly according to claim 7 , wherein:the anchor and the seat have complementary nesting shapes.9. The VIV suppression strake assembly according to claim 8 , wherein:the complementary nesting shapes comprise interlocking shapes that are configured to lock movement ...

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Номер записи: 72
07-06-2018 дата публикации

AIR CONDUCTION ELEMENT FOR REDUCING AIR RESISTANCE OF A LOAD-CARRYING VEHICLE

Номер: US20180154951A1
Автор: ALGÜERA José Manuel, Richter Martin, SCHMIDT Dirk
Принадлежит:

An air conduction element for reducing the air resistance of a load-carrying vehicle having a load space structure. The air conduction element can be externally mounted in the rear region of the load space structure and includes an air conduction duct with a front air inlet opening and a rear air outlet opening, front and rear being in relation to the direction of travel (x). The air inlet opening overlaps the load space structure in the direction of travel (x) and the air outlet opening is arranged behind the load space structure within the cross-sectional contour thereof. The air conduction element has a cover which delimits the air conduction duct. It was therefore the aim to devise an air conduction element which does not increase the dimensions of the load space structure when the vehicle is driving slowly or is at a standstill. For this purpose, the cover is produced from a flexible flat material. 1. An air conduction element for reducing air resistance of a load-carrying vehicle having a cargo space structure , which can be externally mounted in a rear region of the cargo space structure and comprises an air conduction duct with a front air inlet opening and a rear air outlet opening in a direction of travel (x) , wherein the air inlet opening overlaps the cargo space structure in the direction of travel (x) and the air outlet opening is arranged behind the cargo space structure within its cross section contour , wherein the air conduction element comprises a cover which delimits the air conduction duct , wherein the cover is produced from a flexible flat structure.2. The air conduction element as claimed in claim 1 , wherein the cover is held by spacing elements on the cargo space structure.3. The air conduction element as claimed in claim 2 , wherein the spacing elements engage with the cover and the cargo space structure.4. The air conduction element as claimed in claim 2 , wherein the spacing elements are formed from belts or cables.5. The air conduction ...

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Номер записи: 73
15-06-2017 дата публикации

Aerodynamic device for motor-vehicle

Номер: US20170166267A1
Автор: Enrico Modesto RIBALDONE, Luca MIRETTI
Принадлежит: Centro Ricerche Fiat SCpA

Aerodynamic device for a motor-vehicle including a panel structure located under the front part of the motor-vehicle and elastically biased towards a raised position and configured to be moved towards a lowered position due to an airflow which invests the motor-vehicle during travel. The aerodynamic device includes a bag structure provided inside of a cavity for receiving in its interior the airflow which invests the motor-vehicle during travel, in such a way that above a predetermined threshold value of the motor-vehicle speed, the bag structure is inflated and pushes the panel structure towards its lowered position.

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Номер записи: 74
30-05-2019 дата публикации

HIGH SPEED ROTATING BODIES WITH TRANSVERSE JETS AS A FUNCTION OF ANGLE OF ATTACK, REYNOLDS NUMBER, AND VELOCITY OF THE JET EXIT

Номер: US20190162212A1
Автор: Alhussan Khaled Abdullah
Принадлежит:

A system includes an elongated cylindrical body having a first end extending to a second end; an outer surface and an inner surface; a thickness extending from the inner surface to the outer surface; and a plurality of openings extending from the inner surface to the outer surface. The system further includes a fluid injection apparatus disposed within the elongated cylindrical body, the fluid injection apparatus is configured to pass fluid through the openings. 1. A system , comprising: a first end extending to a second end;', 'an outer surface and an inner surface;', 'a thickness extending from the inner surface to the outer surface; and', 'a plurality of openings extending from the inner surface to the outer surface; and, 'an elongated cylindrical body, havinga fluid injection apparatus disposed within the elongated cylindrical body, the fluid injection apparatus is configured to pass fluid through the openings;wherein the elongated cylindrical body travel through a jet stream.2. The system of claim 1 , wherein the elongated cylindrical body travels through the jet stream at a high speed.3. The system of claim 2 , wherein the high speed is approximately Mach number 2.4. The system of claim 1 , wherein the elongated cylindrical body travels at an angle through the jet stream.5. The system of claim 1 , wherein the fluid injection apparatus is configured to inject a jet of fluid into a boundary layer surrounding the outer surface of the elongated cylindrical body as a function of angle of attack claim 1 , Reynolds number claim 1 , and velocity of the jet exit.6. The system of claim 1 , wherein the elongated body rotates within the jet stream.7. The system of claim 6 , wherein the elongated body rotates at approximately 10 claim 6 ,000 RPM.8. The system of claim 7 , wherein the elongated body travels within the jet stream at approximately Mach number 2.9. The system of claim 1 , wherein the location of the plurality of openings is approximately ⅓ length of the ...

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Номер записи: 75
30-05-2019 дата публикации

SYSTEM THAT CREATES A COMPLEX FLUID MECHANISM OVER A BLUNT BODY WITH AND WITHOUT A DECELERATOR AND WITH REGARD TO A TOTAL AERODYNAMIC DRAG

Номер: US20190163849A1
Автор: Alhussan Khaled Abdullah
Принадлежит:

A system for creating an analysis to be used in development of a design methodology for creating a blunt body with optimal performance, the system includes a first blunt body model lacking a deceleration device; a second blunt body model with a deceleration device integrated into the second blunt body model; a computational fluid dynamic module to perform data analysis on the first blunt body model and the second blunt body model; contoured plots relating to fluid flow around the first blunt body and the second blunt body as determined by the computational fluid dynamics module; the contoured plots provide a numerical analysis to be used to develop a design of the blunt body with optimal performance. 1. A system for creating an analysis to be used in development of a design methodology for creating a blunt body with optimal performance , the system comprising:a first blunt body model lacking a deceleration device;a second blunt body model with a deceleration device integrated into the second blunt body model;a computational fluid dynamic module configured to perform data analysis on the first blunt body model and the second blunt body model;a plurality of contoured plots relating to fluid flow around the first blunt body and the second blunt body as determined by the computational fluid dynamics module;wherein the plurality of contoured plots provide a numerical analysis to be used to develop a design of the blunt body with optimal performance.2. The system of claim 1 , wherein the deceleration device is integrated into an end opposite of a blunt end of the second blunt body module.3. The system of claim 1 , wherein the plurality of contoured plots comprises:a visual representation of detached shock waves associated with the first blunt body model movement through fluid and the second blunt body movement through fluid; anda visual representation of flow separation associated with the first blunt body model movement through fluid and the second blunt body movement ...

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Номер записи: 76
30-05-2019 дата публикации

SYSTEM CONFIGURED TO CHANGE THE MACH NUMBER FOR DIFFERENT ANGLES OF ATTACK WITH DIFFERENT SPEEDS FOR ACHIEVING CHANGING AERODYNAMIC FORCES AND VELOCITY WITH A DECELERATION DEVICE INTEGRATED WITH A BLUNT BODY

Номер: US20190163850A1
Автор: Alhussan Khaled Abdullah
Принадлежит:

A system to change a Mach number for different angles of attack with different speeds to achieving changing aerodynamic forces and velocity with a deceleration device integrated with a blunt body, the system includes a blunt body model having a deceleration device integrated into the blunt body model; a computational fluid dynamic module to perform data analysis on the blunt body model as the blunt body model receives fluid flow; a selection of Mach numbers to be inputted into the computational fluid dynamics module; a selection of angles of attack to be inputted into the computational fluid dynamics module; and contoured plots created via the computational fluid dynamics; the contoured plots relates to fluid flow around the blunt body model, with the contoured plots providing data relating to one or more of the selection of Mach numbers and one or more of the selection of angles of attack; and the contoured plots provides data analysis to be used to develop a design of a blunt body with optimal performance. 1. A system configured to change a Mach number for different angles of attack with different speeds to achieving changing aerodynamic forces and velocity with a deceleration device integrated with a blunt body , the system comprising:a blunt body model having a deceleration device integrated into the blunt body model;a computational fluid dynamic module configured to perform data analysis on the blunt body model as the blunt body model receives fluid flow;a selection of Mach numbers configured to be inputted into the computational fluid dynamics module;a selection of angles of attack configured to be inputted into the computational fluid dynamics module; anda plurality of contoured plots created via the computational fluid dynamics;wherein the plurality of contoured plots relates to fluid flow around the blunt body model, with the plurality of contoured plots providing data relating to one or more of the selection of Mach numbers and one or more of the selection ...

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Номер записи: 77
01-07-2021 дата публикации

Processing apparatus, and manufacturing method of movable body

Номер: US20210197315A1
Автор: Masayuki Shiraishi, Yosuke Tatsuzaki
Принадлежит: Nikon Corp

A processing apparatus has: a light irradiation apparatus that irradiates a surface of an object with a processing light; and a partition member that surrounds a space including an optical path between the surface of the object and an optical member that is disposed at the most object side in an optical system of the light irradiation apparatus that allows the processing light to pass therethrough.

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Номер записи: 78
21-06-2018 дата публикации

MULTI-FUNCTIONAL FLAP USED AS A BACK-FLOW FLAP

Номер: US20180171975A1
Автор: Röhm Dieter
Принадлежит:

The invention relates to a device of a safety system and/or resource and energy-efficiency improvement system for influencing the flow around an aero- or hydrodynamic body, preferably an aerofoil, according to the principle of a back-flow flap, characterized in that: said device, together with the aero- or hydrodynamic body, in particular aerofoil, form at least a partial shift of the delimitation of the flap region by means of the back-flow flap and the delimiting component thereof when the back-flow flap is partially and/or completely raised, thus influencing the trailing edge separation vortex/vortices and/or the flap separation vortex/vortices; and in that the delimitation of the flap region shifts completely up to or beyond the profile trailing edge, or shifts only to a section in front of the profile trailing edge. The delimitation component is movably connected to the aerofoil by means of a basic element and is preferably permanently secured and/or releasably secured for maintenance purposes, thus ensuring a long service life for the rotor blade and/or wind turbine and/or flap system, preferably >5 years, particularly preferably >10 years, and most particularly preferably >=20 years, and/or thus optionally allowing simple removal/replacement. 175-. (canceled)76. A device in the form of a wind turbine rotor blade comprising a passive or active flap system for improving the output ,comprising a base element which reinforces the rotor blade, andat least one flap attached thereto,wherein the base element comprises a support face on the rotor blade, andwherein the flap is attached to the base element so as to be movable and is formed as a passive back-flow flap.77. The device according to claim 76 , wherein the movable attachment of the flap to the base element is formed using a joint made of resilient material claim 76 , in particular in the form of film claim 76 , textiles claim 76 , in particular textiles comprising glass fibres or aramid fibres claim 76 , one ...

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Номер записи: 79
06-06-2019 дата публикации

PART AND METHOD FOR PRODUCING A PART HAVING REDUCED DRAG BY NON-CONSTANT RIBLETS

Номер: US20190168862A1
Автор: MARTY Julien Roger Marcel, RIERA William Henri Joseph, TALBOTEC Jerome Jean-Yves
Принадлежит: SAFRAN AIRCRAFT ENGINES

Part comprising a wall which comprises a first zone (), a first zone () and the second zone (), a network of riblets being formed on the first zone (), the second zone () and also on the transition zone () so as to reduce the drag of the part when a flow of air flows along said wall; the height, the width and the spacing of the riblets formed on the transition zone () changing along said transition zone () so as to pass from the height, width and spacing of the riblets formed on the first zone at a first end of the transition zone to the height, width and spacing of the riblets formed on the second zone () at a second end of the transition zone (), the transition zone () comprising a central portion on which the riblets comprise on one hand the height and the width that are respectively equal to the height and width of the riblets on the first zone (), and on the other hand a spacing equal to the spacing of the riblets of the second zone (). 1154154254541542t. A turbomachine part () for an aircraft comprising a wall which comprises a first zone () , a second zone () , and a transition zone () located between the first zone () and the second zone () ,{'b': 6', '541', '542', '54, 'i': 't', 'an array of riblets () being formed on the first zone (), on the second zone (), and also on the transition zone (), the riblets being oriented parallel to the principal direction of airflow;'}{'b': 6', '1', '2', '1', '2', '1', '2', '6, 'the riblets () comprising an apex (S), a height (H, H, Ht), a width (L, L, Lt), and a spacing (E, E, Et) which corresponds to the distance between the apices (S) of adjacent riblets ();'}{'b': 1', '1', '1', '6', '541', '541, 'the height (H), the width (L), and the spacing (E) of the riblets () of the first zone () being constant on the first zone ();'}{'b': 2', '2', '2', '6', '542', '542, 'the height (H), the width (L), and the spacing (E) of the riblets () of the second zone () being constant on the second zone ();'}{'b': 6', '54', '54', '1', '1', ...

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Номер записи: 80
21-06-2018 дата публикации

DEVICE AND METHOD FOR CONTROLLING FLUID FLOW OVER AN OPTICAL INSTRUMENT

Номер: US20180172040A1
Автор: Hamill Dustin, Miller Kirk A., Salinas Mauricio A.
Принадлежит:

A device is provided for controlling fluid flow over a window of a movable optical instrument housing. The device includes a generally annular body having an inner peripheral edge configured to correspond to a peripheral edge of the window of the housing and an outer peripheral edge, an arcuate outer surface disposed between the inner peripheral edge and the outer peripheral edge, and a reduced width portion between the inner peripheral edge and the outer peripheral edge. The reduced width portion is configured to lower elevation torque. Other embodiments of the device and methods for controlling fluid flow are further disclosed. 1. A device for controlling fluid flow over a window of a movable optical instrument housing , the device comprising:a generally annular body having an inner peripheral edge configured to correspond to a peripheral edge of the window of the housing and an outer peripheral edge, an arcuate outer surface disposed between the inner peripheral edge and the outer peripheral edge, and a reduced width portion between the inner peripheral edge and the outer peripheral edge, the reduced width portion being configured to lower elevation torque.2. The device of claim 1 , wherein the inner peripheral edge is generally circular in shape and the outer peripheral edge is generally circular in shape.3. The device of claim 2 , the reduced width portion includes a chord that defines a portion of the outer peripheral edge.4. The device of claim 1 , wherein the reduced width portion constitutes a first reduced width portion at one side of the body of the device claim 1 , the device further comprising a second reduced width portion at an opposite side of the body of the device.5. The device of claim 4 , wherein the device is configured to be rotated with respect to the housing.6. The device of claim 5 , further comprising a mechanism configured to rotate the device with respect to the housing.7. The device of claim 6 , wherein the mechanism includes a motor ...

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Номер записи: 81
18-09-2014 дата публикации

BOUNDARY LAYER CONTROL SYSTEM

Номер: US20140265432A1
Автор: Kimura Yukihide
Принадлежит: TOYOTA JIDOSHA KABUSHIKI KAISHA

A boundary layer control system includes a boundary layer separating portion that separates a boundary layer of an airflow at an underside of a body of a moving object from a main flow of the airflow, and an ejecting portion that ejects fluid in a state different from that of the boundary layer and the main flow, between the boundary layer and the main flow that have been separated by the boundary layer separating portion. This boundary layer control system is characterized in that boundary layer and the main flow are reliably separated by the fluid in a state different from that of the boundary layer and the main flow, so the percentage of the main flow that is slowed down (i.e., reduced in velocity) by the boundary layer is reduced. 1. A boundary layer control system comprising:a boundary layer separating portion that separates a boundary layer of an airflow at a surface of a body of a moving object from a main flow of the airflow;an ejecting portion that ejects fluid in a state different from that of the boundary layer and the main flow, between the boundary layer and the main flow that have been separated by the boundary layer separating portion; anda suction portion that is provided behind the boundary layer separating portion in a longitudinal direction of the moving object, and sucks in fluid included in the boundary layer, wherein the ejecting portion ejects the fluid sucked in by the suction portion, between the boundary layer and the main flow.2. The boundary layer control system according to claim 1 , wherein the ejecting portion ejects fluid in which at least one of a fluid velocity claim 1 , a fluid pressure claim 1 , and a fluid temperature is different from that of the boundary layer and the main flow claim 1 , between the boundary layer and the main flow.3. (canceled)4. The boundary layer control system according to claim 1 , further comprising a control portion that controls the state of the fluid sucked in by the suction portion and supplies the ...

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Номер записи: 82
02-07-2015 дата публикации

Rotary machine

Номер: US20150184750A1
Автор: Hidekazu Uehara, Hiroharu Oyama, Kazuyuki Matsumoto, Koichi Ishizaka, Shin Nishimoto, Yoshihiro Kuwamura, Yoshinori Tanaka, Yoshiyuki Okabe
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

A rotary machine includes turbine moving blades ( 50 ); a casing ( 10 ) covering the turbine moving blades ( 50 ) so as to define a gap at an outer circumference side of the turbine moving blades; a leaf seal ( 70 ) having a seal body ( 71 ) that is disposed in the gap so as to protrude radially inward from the casing ( 10 ) and is capable of coming into contact with the turbine moving blades ( 50 ), and a high-pressure-side plate member ( 73 ) that is disposed along a face facing a high pressure side of the seal body ( 71 ); and a swirling flow inhibitor ( 80 ) that is provided on the high pressure side of the leaf seal ( 70 ) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

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Номер записи: 83
28-06-2018 дата публикации

FLOW MODIFICATION DEVICE, SYSTEM, AND METHOD

Номер: US20180180073A1
Автор: MARCOLLO Hayden, POTTS Andrew Elmhirst
Принадлежит: AMOG Technologies Pty Ltd

A flow modification device connectable to a generally cylindrical element adapted for immersion in a fluid medium, the device comprising an elongate body having a length and a generally circular cross-section; a plurality of raised body portions disposed about and extending along the length of the elongate body, the raised body portions being arranged generally parallel to a longitudinal axis of the body and having a height between 2% and 10% of a diameter of the body; and an aperture extending through the length of the elongate body, the aperture being adapted to receive the generally cylindrical element such that the flow modification device is arranged about the cylindrical element. The plurality of raised body portions are adapted to reduce vortex-induced vibration and/or drag on the cylindrical element when the device is connected to the cylindrical element and the connected device and cylindrical element are immersed in the fluid medium and there is relative movement between the connected device and cylindrical element and the fluid medium. 1. A flow modification device connectable to a generally cylindrical element adapted for immersion in a fluid medium , the device comprising:an elongate body having a length and a generally circular cross-section;a plurality of raised body portions disposed about and extending along the length of the elongate body, the raised body portions being arranged generally parallel to a longitudinal axis of the body and having a height between 2% and 10% of a diameter of the body; andan aperture extending through the length of the elongate body, the aperture being adapted to receive the generally cylindrical element such that the flow modification device is arranged about the cylindrical element;wherein the plurality of raised body portions are adapted to reduce vortex-induced vibration and/or drag on the cylindrical element when the device is connected to the cylindrical element and the connected device and cylindrical element are ...

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Номер записи: 84
29-06-2017 дата публикации

Draft turbulence reduction system and method

Номер: US20170183043A1
Автор: David Connors
Принадлежит: Individual

The present invention is a system and method for reducing the amount of drag experiences by a moving vehicle as the result of primary airflow across vehicle body edges by introducing a secondary airflow at said edge to reduce the negative pressure created by such an edge such that the turbulence caused by the primary airflow is prevented or reduced.

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Номер записи: 85
04-06-2020 дата публикации

FLOW DIVIDER WITH INTERNAL VANE

Номер: US20200173593A1
Автор: Anderson Alan C., Andras John Robert, Tolhurst George Martin, Wickliff Jonathan Bowen
Принадлежит:

A flow splitter may include an inlet, at least two outlets, and an internal vane comprising a first end corresponding to the inlet and a second end corresponding to the at least two outlets, wherein the internal vane is configured to turn, between the first end and the second end, an internal flowing fluid from 0 degrees to a degree between about 60 degrees and 150 degrees. Methods of dividing fluid flow are also provided. 1. A flow splitter comprising:an inlet;at least two outlets; andan internal vane comprising a first end corresponding to the inlet and a second end corresponding to the at least two outlets, wherein the internal vane is configured to turn, between the first end and the second end, an internal flowing fluid from 0 degrees to a degree between about 60 degrees and 150 degrees.2. The flow splitter of claim 1 , wherein the internal vane is configured to split the internal flowing fluid along a first axis claim 1 , whereinthe at least two outlets split the internal flowing fluid,one of the at least two outlets having a first axis component and another outlet having a second axis component, andthe first and second axis components defining a plane.3. The flow splitter of claim 2 , wherein the first axis component and a second axis component of the at least two outlets form an acute angle.4. The flow splitter of claim 2 , wherein the first axis component and a second axis component of the at least two outlets form a right angle.5. The flow splitter of claim 1 , wherein the internal vane is configured to turn the internal flowing fluid between about 80 degrees and 100 degrees.6. The flow splitter of claim 1 , wherein the internal vane is configured to turn the internal flowing fluid by about 90 degrees.7. The flow splitter of claim 1 , wherein the internal vane forms a first conduit and a second conduit using the internal vane.8. The flow splitter of claim 7 , wherein the first conduit and the second conduit have equal cross-sectional areas between the ...

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Номер записи: 86
05-07-2018 дата публикации

SANITATION SYSTEMS AND COMPONENTS THEREOF HAVING A SLIPPERY SURFACE

Номер: US20180187022A1
Автор: Aizenberg Joanna, AIZENBERG Michael, Kang Sung Hoon, Kim Philseok, WONG Tak Sing
Принадлежит:

The present disclosure describes a strategy to create self-healing, slippery liquid-infused porous surfaces. Roughened (e.g., porous) surfaces can be utilized to lock in place a lubricating fluid, referred to herein as Liquid B to repel a wide range of materials, referred to herein as Object A (Solid A or Liquid A). Slippery liquid-infused porous surfaces outperforms other conventional surfaces in its capability to repel various simple and complex liquids (water, hydrocarbons, crude oil and blood), maintain low-contact-angle hysteresis (<2.5°), quickly restore liquid-repellency after physical damage (within 0.1-1 s), resist ice, microorganisms and insects adhesion, and function at high pressures (up to at least 690 atm). Some exemplary application where slippery liquid-infused porous surfaces will be useful include energy-efficient fluid handling and transportation, optical sensing, medicine, and as self-cleaning, and anti-fouling materials operating in extreme environments. 1. An article comprising a slippery surface capable of reducing adhesion of a foreign material to the article ,wherein the article is a component of a sanitation system;wherein the article comprises:(i) a substrate comprising a roughened surface, and(ii) a lubricating liquid having a chemical affinity for the roughened surface, the lubricating liquid wetting and adhering to the roughened surface to provide a liquid overlayer on the roughened surface, without dewetting from the substrate, to form the slippery surface; andwherein the foreign material comprises waste water, dirt, a fecal matter, urine, blood, a bacterium, a virus, a fungus, a bodily fluid, a tissue, or a combination thereof.2. The article according to claim 1 , wherein the article is a toilet or a sink.3. The article according to claim 1 , wherein the chemical affinity of the lubricating liquid for the roughened surface is determined by an equilibrium contact angle of less than 90°.4. The article according to claim 1 , wherein the ...

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Номер записи: 87
22-07-2021 дата публикации

Enclosure having outer surface with vortex-induced vibration suppression function

Номер: US20210222451A1
Автор: Shengjun MA
Принадлежит: Beijing Goldwind Science and Creation Windpower Equipment Co Ltd

An enclosure having an outer surface with a vortex-induced vibration suppression function is provided. The outer surface of the enclosure is provided with a plurality of annular recesses surrounding the enclosure, such that alternately concave and convex annular recesses and annular bosses configured for disrupting a boundary layer of a laminar flow are formed on the outer surface of the enclosure. An outer surface of the annular boss is provided with a plurality of air guiding grooves, and the plurality of air guiding grooves are distributed in a circumferential direction of the annular boss. The air guiding grooves are inclined upward or downward, such that part of an upwind incoming flow flowing to the annular boss can be guided into the annular recesses adjacent to the annular boss via the air guiding grooves. With the convex-concave outer surface, the cause of formation of the vortex-induced vibration can be prevented.

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Номер записи: 88
13-07-2017 дата публикации

Upper wheel fairing reducing critical vehicle drag

Номер: US20170197673A9
Автор: Garth L. Magee
Принадлежит: Individual

An aerodynamically optimized drag-reduction means and method for optimal minimization of the drag-induced resistive forces upon a terrestrial vehicle wheel, where the drag-induced resistive moments on wheel surfaces pivoting about the point of ground contact are reduced, and the vehicle propulsive forces needed to countervail the resistive forces on the wheel are reduced. The drag reduction means includes: a streamlined wheel cover positioned on a vehicle to shield the faster moving upper wheel surfaces from headwinds; a streamlined wind-deflecting fairing positioned on a vehicle to shield the faster moving upper wheel surfaces from headwinds; an engine exhaust pipe diposed on a vehicle whereby exhaust gases deflect headwinds to shield the faster moving upper wheel surfaces of an automotive wheel; an automotive spoked wheel having streamlined oval-shaped wheel spokes arranged in one or more rows for greater axial strength; a streamlined tailfin rotatably attached to a wheel spoke, which thereby may pivot about the spoke in response to varying crosswinds; and a tire having streamlined tread blocks arranged in an aerodynamic pattern.

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Номер записи: 89
02-10-2014 дата публикации

Slippery surfaces with high pressure stability, optical transparency, and self-healing characteristics

Номер: US20140290731A1
Автор: Joanna Aizenberg, Michael Aizenberg, Philseok Kim, Sung Hoon KANG, Tak Sing Wong
Принадлежит: Harvard College

The present disclosure describes a strategy to create self-healing, slippery liquid-infused porous surfaces (SLIPS). Roughened (e.g., porous) surfaces can be utilized to lock in place a lubricating fluid, referred to herein as Liquid B to repel a wide range of materials, referred to herein as Object A (Solid A or Liquid A). SLIPS outperforms other conventional surfaces in its capability to repel various simple and complex liquids (water, hydrocarbons, crude oil and blood), maintain low-contact-angle hysteresis (<2.5°), quickly restore liquid-repellency after physical damage (within 0.1-1 s), resist ice, microorganisms and insects adhesion, and function at high pressures (up to at least 690 atm). Some exemplary application where SLIPS will be useful include energy-efficient fluid handling and transportation, optical sensing, medicine, and as self-cleaning, and anti-fouling materials operating in extreme environments.

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Номер записи: 90
19-07-2018 дата публикации

Devices for Separating Constituents in a Sample and Methods for Use Thereof

Номер: US20180200717A1
Автор: Sohn Lydia Lee, Yang Daniel K.
Принадлежит:

Devices for separating constituents (e.g., cells) in a fluid sample are provided. The device includes a microfluidic conduit configured to carry a flow of a fluid sample and includes two or more separation elements, each separation element including a first region and a second region, where the first region has a cross-sectional area less than a cross-sectional area of the second region. The device also includes a flow resistive element in fluid communication with the microfluidic conduit in a region between two adjacent separation elements. Also provided are methods of using the devices, as well as systems and kits that include the devices. The devices, systems, methods and kits find use in a variety of different applications, including diagnostic assays. 1. A device for separating constituents in a fluid sample , the device comprising:a microfluidic conduit configured to carry a flow of a fluid sample and comprising two or more separation elements, each separation element comprising a first region and a second region, wherein the first region has a cross-sectional area less than a cross-sectional area of the second region; anda flow resistive element in fluid communication with the microfluidic conduit in a region between two adjacent separation elements.2. The device of claim 1 , wherein the first region and the second region of each separation element are arranged symmetrically about a longitudinal axis of the microfluidic conduit.3. The device of claim 1 , wherein the first region and the second region of each separation element are arranged asymmetrically about a longitudinal axis of the microfluidic conduit.4. The device of claim 1 , wherein the two or more separation elements are arranged in series.5. The device of claim 1 , wherein the two or more separation elements are arranged in parallel.6. The device of claim 1 , wherein the two or more separation elements are arranged in series and in parallel.7. The device of claim 1 , wherein the device comprises:a ...

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Номер записи: 91
18-06-2020 дата публикации

SYSTEMS AND METHODS FOR ACTIVE CONTROL OF SURFACE DRAG USING WALL COUPLING

Номер: US20200191177A1
Автор: Holloway Brian C., Marusic Ivan, Smits Alexander J., Wine David William
Принадлежит:

A system includes a surface having a fluid flowing over the surface. The fluid includes a flow regime having a streamwise length scale greater than about 100 times η and less than about 100,000 times η, where η is a viscous length scale of the flow regime, and a convective time scale greater than about 10η′ and less than about 10,000η′, where η′ is a viscous time scale of the flow regime. The system includes a controller that causes at least one of motion the surface to modify fluid flow in the flow regime based on the streamwise length scale and the convective time scale or motion of the flow regime based on the streamwise length scale and the convective time scale. 1. A method for controlling drag caused by fluid flowing over material bodies , comprising:identifying a streamwise length scale of at least one flow regime of a fluid flowing over a surface, the streamwise length scale greater than about 10 times η and less than about 100,000 times η, wherein η is a viscous length scale of the at least one flow regime;identifying a convective time scale of the at least one flow regime, the convective time scale having a duration of greater than about 10η′ and less than about 10,000η′, wherein η′ is a viscous time scale of the at least one flow regime; andcausing at least one of (1) motion of at least a portion of the surface to modify fluid flow in the at least one flow regime of the fluid based on the streamwise length scale and the convective time scale or (2) motion of the at least one flow regime based on the streamwise length scale and the convective time scale.2. The method of claim 1 , further comprising:outputting a control signal to cause at least the portion of the surface to perform the motion corresponding to the streamwise length scale and the convective time scale of the at least one flow regime.3. The method of claim 2 , wherein outputting the control signal includes outputting the control signal to at least one deformer coupled with the surface to cause ...

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Номер записи: 92
29-07-2021 дата публикации

WIND POWER GENERATION APPARATUS, TOWER AND METHOD FOR SUPPRESSING TOWER SHADOW EFFECT OF TOWER

Номер: US20210231106A1
Автор: MA Shengjun
Принадлежит: BEIJING GOLDWIND SCIENCE & CREATION WINDPOWER EQUIPMENT CO., LTD.

A wind power generation apparatus, a tower and a method for suppressing a tower shadow effect of the tower. The tower is provided with suction through holes extending through a circumferential wall thereof, and the suction through holes are distributed in a circumferential direction of the tower; the tower is further provided with a suction apparatus, and the suction apparatus can perform suction to the suction through holes from outside to inside. With the tower and the method, when the suction through holes at a windward side are suctioned, the adverse influence of the tower shadow effect can be weakened or eliminated, a service life of a pitch varying bearing can be prolonged, a noise can be reduced and a wind energy utilization coefficient can be improved. When the suction through holes at a position of a bypassing flow detachment are suctioned, vortex-induced vibrations can also be suppressed. 1. A tower , the tower being provided with suction through holes extending through a circumferential wall of the tower , wherein the suction through holes are distributed in a circumferential direction of the tower; the tower is further provided with a suction apparatus , and the suction apparatus is configured to perform suction to the suction through holes from outside to inside.2. The tower according to claim 1 , wherein a shell is arranged in the tower claim 1 , and a closed annular suction cavity is enclosed by the shell and an inner surface of a region claim 1 , provided with the suction through holes claim 1 , of the tower; the suction apparatus is configured to suction the suction cavity claim 1 , to implement the suction to the suction through holes from outside to inside.3. The tower according to claim 2 , wherein partitions are further arranged in the suction cavity claim 2 , and the suction cavity is divided claim 2 , by the partitions claim 2 , into a plurality of suction chambers distributed in the circumferential direction; the tower further comprises a ...

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Номер записи: 93
29-07-2021 дата публикации

Submerged periodic riblets

Номер: US20210231142A1
Автор: Brian R. Smith, Patrick James Yagle, Paul Douglas McClure
Принадлежит: Lockheed Martin Corp

In one embodiment, a method for reducing drag includes forming a smooth surface on a first portion of a physical object. The method also includes forming periodic riblets on a second portion of the physical object. The second portion of the physical object is adjacent to the first portion of the physical object. Each riblet of the periodic riblets of the second portion of the physical object is depressed below a plane of the smooth surface of the first portion of the physical object. The method further includes generating a flow over the periodic riblets of the second portion of the physical object and over the smooth surface of the first portion of the physical object. A length of each riblet of the periodic riblets runs parallel to a direction of the flow.

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Номер записи: 94
04-07-2019 дата публикации

Airfoils and Machines Incorporating Airfoils

Номер: US20190202503A1
Автор: David A. Shoffler, Michael Suk
Принадлежит: Ess 2 Tech LLC

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

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Номер записи: 95
04-07-2019 дата публикации

Active drag-reduction system and a method of reducing drag experienced by a vehicle

Номер: US20190202505A1
Автор: Hatem ELOGAB, Osama Elogab
Принадлежит: Ogab Ltd

There is provided an active drag-reduction system having first 22 and second 24 fluid outlets located on a vehicle 10 adjacent to a low pressure (drag) region 12 , wherein fluid ejected from the second fluid outlet 24 is at a higher pressure/ejection velocity than from the first fluid outlet 22 . Turbulent and/or low pressure regions adjacent to vehicles are not uniform, but rather have a varying intensity. For instance, the centre of a region may have a lower pressure and/or more turbulent nature than the periphery of the region. The system may inject relatively higher pressure air (or relatively higher speed air) into the relatively lower pressure/more turbulent part of the low pressure/turbulent region, and relatively lower pressure air (or relatively lower speed air) into the relatively higher pressure/less turbulent part of the low pressure/turbulent region, compared to each other.

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Номер записи: 96
04-07-2019 дата публикации

AERODYNAMIC ARTICLES AND METHODS THEREOF

Номер: US20190202547A1
Автор: Johnston Raymond P., Lee Nicholas A., Praggastis Chris A., Wu Pingfan
Принадлежит:

Provided are aerodynamic articles and related methods that use an aerodynamic body with a microstructured surface thereon. The microstructured surface has a plurality of parallel primary ridges defining major capillary channels, and optionally a plurality of parallel secondary ridges having a height less than that of the primary ridges and extending between and generally parallel to the primary ridges. The optional secondary ridges at least partially define two or more minor capillary channels within each major capillary channel. The aerodynamic surface provides reduced drag and is capable providing a high degree of friction against shoe surfaces under oil and water contaminated conditions. 1. An aerodynamic article comprising:an aerodynamic body; a plurality of parallel, primary ridges defining major capillary channels; and', 'a plurality of parallel, secondary ridges having a height less than that of the primary ridges and extending between and generally parallel to the primary ridges, each secondary ridge at least partially defining two or more minor capillary channels within a respective major capillary channel., 'a microstructured surface on the aerodynamic body, the microstructured surface comprising2. The aerodynamic article of claim 1 , wherein the aerodynamic body is comprised of a substrate having a microstructured film disposed on the substrate claim 1 , the microstructured surface being provided on the microstructured film.3. The aerodynamic article of claim 1 , wherein the microstructured surface is an oleophilic surface.4. The aerodynamic article of claim 1 , wherein the primary ridges have an average height H1 in the range of from 25 micrometers to 250 micrometers.5. The aerodynamic article of claim 1 , wherein the secondary ridges have an average height H2 in the range of from 5 micrometers to 50 micrometers.6. The aerodynamic article of claim 1 , wherein the primary ridges have an average height H1 claim 1 , the secondary ridges have an average ...

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Номер записи: 97
26-07-2018 дата публикации

Swirling Jet Actuator for Control of Separated and Mixing Flows

Номер: US20180209452A1
Автор: Farrukh ALVI, Kunihiko Taira, Phillip Munday
Принадлежит: Florida State University Research Foundation Inc

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.

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Номер записи: 98
04-07-2019 дата публикации

Fairing and Method

Номер: US20190203852A1
Автор: SKAUGSET Kjetil
Принадлежит:

A fairing device and method for the reduction of vortex-induced vibrations or motions, the minimization of drag about a substantially cylindrical element immersed in a fluid medium, comprising; a fairing rotatably mounted about the cylindrical element, the fairing comprising a shell with a mainly cylindrical cross-sectional shape with an outer diameter (D) following the outer diameter of the cylindrical element from an upward stagnation point of 0 degrees to at least ±90 degrees, and which at ±90 degrees continues as two fin-like portions in an aft direction, further comprising that the fin-like portions are convexly curved aft of ±90 degrees thus tapering towards each other and defining a tail end opening or gap less than the fairing standoff height. A method for mounting, storage, and deployment of the fairing device is also disclosed. 2. The method of claim 1 , further comprisingapplying at least one shape-fixation device inside the fairing device along the axial direction by unfolding at least one hinged shape-fixation device or devices from between the cylindrical element and the fairing device; andsecuring and locking the said shape fixation device or devices to the fairing device and to the cylindrical element by means of a locking pin.3. The method of claim 2 , further comprising:wherein applying at least one shape-fixation device inside the fairing device along the axial direction by unfolding at least one hinged shape-fixation device or devices from between the cylindrical element and the fairing device; andsecuring and locking the said shape-fixation device or devices to the fairing device and to the cylindrical element by means of grooves within the inside of the fairing device.4. The method of claim 1 , further comprising:applying at least one shape-fixation device inside the fairing device along the axial direction by inserting at least one shape-fixation device into the inside of the fairing device along the axial direction; andsecuring and locking ...

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Номер записи: 99
20-08-2015 дата публикации

Devices for controlling the downforce generated by a vehicle

Номер: US20150232138A1
Автор: Arthur Slight, Dan Parry-Williams
Принадлежит: McLaren Automotive Ltd

A vehicle comprising a flap that is attached to the vehicle in such a way as to permit movement of the flap from a first position to a second position, wherein the flap is configured to alter the downforce generated by the vehicle when the vehicle is in motion by affecting the airflow underneath the vehicle, the effect of the flap on the airflow being dependent upon the second position of the flap.

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Номер записи: 100