WO2017112010A1 - Apparatus for eliminating wingtip vortices - Google Patents

Abstract

A wingtip device comprising a tube with internal waveguide surfaces and a means for vortices collection, affixed to a wing or air foil to capture wingtip vortices and convert them to smooth, laminar flow thereby eliminating the effects of vortical drag on the aircraft. As vortices occur 5around a wingtip, they are channeled or otherwise directed towards the inlet end of the device, through the waveguide tube which consists of a series of waveguides, and out the exit end as laminar flow, resulting in thrust.

Description

APPARATUS FOR ELIMINATING WINGTIP VORTICES

RELATED APPLICATIONS

[001] This application is a PCT filing of and claims priority to United States patent application serial number 15/263,347 titled "APPARATUS FOR ELIMINATING WINGTIP VORTICES"filed on September 12, 2016, which claims the benefit of, and priority to, United States provisional patent application serial number 62/217,803, titled "WINGTIP VORTEX

CONVERTER" and filed on September 11, 2015, and is also a continuation-in-part of United States patent application serial number 14/636,150, titled "CHANNELING FLUIDIC

WAVEGUIDE SURFACES AND TUBES" and filed on March 2, 2016, which is a continuationof United States patent application serial number 13/938,213, titled "CHANNELING GAS FLOW TUBE" and filed on July 9, 2013, now U.S. Patent No. 8,967,326, which was a continuation of United States patent application serial number 13/540,492, now U.S. Patent No. 8,479,878 B2 also titled "CHANNELING GAS FLOW TUBE", filed on July 2, 2012, which is a continuation-in-part of United States patent application serial number 12/238,253, titled

"CHANNELING GAS FLOW TUBE", filed on September 25, 2008 and issuing on July 3, 2012 as United States patent number 8,210,309, the entire specification of each of which is incorporated herein by reference.

BACKGROUND OF THE INVENTION

Field of the Invention

[002] The present invention is in the field of aeronautics and the mitigation of drag associated with movement of objects such as a wing, airfoil or plane through a fluid, such as air.

Discussion of the State of the Art

[003] Drag is generated by a solid object interacting and in contact with a fluid. It adversely affects an object moving through fluid by slowing it down. Drag can be described as one of theaerodynamic forces acting on an aircraft resulting from its movement through the air; it affects both powered and unpowered aircraft, and it acts as a force applied along and opposite to the motion of the aircraft. [004] A powered aircraft experiences four primary forces whilst in motion: lift, weight, thrust and drag. In accordance with Newton's third law, lift counteracts the effects of weight, and therefore, thrust must overcome the combined effects of drag in order for the craft to remain in motion. A powered aircraft differs from a glider as it has a propulsion system which generates 5thrust to overcome the combined effects of drag. The amount of thrust required to overcome drag is reduced if the drag on the craft is reduced. Hence, the amount of power needed to be generated to induce motion is less on a craft where the effects of drag have been reduced, mitigated, or eliminated.

[005] A glider, having no propulsion system, has only three forces acting on it during free flight: lOlift, weight and drag. Both powered and unpowered aircraft are affected by drag. Both also have airfoils as wings, which are used to generate lift to oppose the effects of weight. However, airfoils are also solid objects that move through the air and, as a result of being in contact with the air, also generate drag.

[006] There is a general consensus in the field to devise ways to increase the efficiency of 15aircraft by reducing the amount of energy needed to power an aircraft. For those skilled in the art, the idea of increasing efficiency may be understood as the focus of reducing the effects of drag. Drag can be broken down into various components, but for the topic of the embodiment, the effects of drag on wings or airfoils, and more specifically how the air moves around the foil or wing is the target.

20[007] For an airfoil to lift, the pressure below the plane or surface must be greater than the pressure above the plane or surface. As long as there is a solid object between the high and low pressures, the object will experience force as lift resulting from the imbalance of pressures on either side of the object. Near the free end of the airfoil or wing, the air is free to move from the high-pressure boundary to the low-pressure boundary, and as it does so, the air whips around the

25tip of the airfoil, and wingtip vortices are produced. Vortices are turbulent in nature; the wingtip vortices create downwash, and combine with the overall effects of drag on the aircraft.

[008] Airfoil size and shape, boundary surface material, and overall wing geometry affect how the fluid or air flows over the foil, including how it flows around the free end of the foil or wing. Various wingtip devices known in the art have been devised over the years as means to reduce 30the effects of wingtip vortices. While these devices aim to reduce the effects of wingtip vortices, the vortices remain active, even at a lesser magnitude, and the corresponding induced drag still exists to a lesser extent.

[009] Fig. 1 (PRIOR ART) is a simplistic sectional view showing how wing tip vortices 100, 101 occur when an object 1, such as an airfoil 1, wing 1 or other solid body 1, moves through a fluid6 or combination of fluids 6, such as air 6, space 6, or water 6. For an airfoil 1 to experience a lift force 8, the airfoil 1 must encounter high-pressure 3 below the airfoil 1 and low-pressure 2 above the airfoil plane 1 or surface 1. As long as there is a solid object 1 between the high-pressure 3 and low-pressure 2, the object 1 will experience a resultant lift force 8 resulting from the imbalance of pressures on either side of the object 1. [010] Fig. 2 (PRIOR ART) shows another view in plan of how wingtip vortices 100, 101 are produced when an object 1, such as an airfoil 1, wing 1 or other solid body 1, moves through a fluid 6 or combination of fluids 6, such as air 6, space 6, or liquid 6. Near the free-end 15 of an airfoil 1 or wing 1, the air 102 that is about to come into contact with the airfoil 1 is free to move from the high-pressure boundary 3 to the low-pressure boundary 2, and as it does so, the air 102whips around the tip 15 of the airfoil 1, and wingtip vortices 100 are created and generate tip vortices as drag 101.

[011] Fig. 3 (PRIOR ART) illustrates the creation of wingtip vortices 101 as a result of offset or unbalanced pressures 2, 3 being applied to a solid surface 1 moving through a fluid 6, thereby creating friction 18 or drag 18 on the respective solid surface 1. Vortices 100, 101 are turbulent innature; the wingtip vortices 100 create downwash 101, and combine with the overall effects of drag 7 on the aircraft 17.

[012] Fig. 4a (PRIOR ART) illustrates how a particular solid object 1 when represented as a rectangular-tipped wing 4 passing through a fluid 6 generates turbulent flow 103 in form of a counter-rotational dual-vortex profile 105, as detailed in Figure 4c. [013] Fig. 4b (PRIOR ART) illustrates how a particular solid object 1 when represented as a rounded-tipped wing 5 passing through a fluid 6 generates turbulent flow 104 in form of a counter-rotational dual-vortex profile 105, as detailed in Figure 4c. [014] Fig. 5 (PRIOR ART) is a diagram of a conventional wingtip known in the art which would create large vortices and higher drag, as well as a blended winglet known in the art for reducing the effects of drag, but not eliminating these effects.

[015] Figs. 6a, 6b, 6c (PRIOR ART) is a series of diagrams illustrating a wingtip known in theprior art to reduce the effects of drag on a wingtip, but not eliminating these effects.

[016] What is needed in the art is an apparatus to capture wingtip vortices and convert turbulent flow resulting from wingtip vortices into smooth, laminar flow, thereby eliminating the corresponding adverse effects of wingtip vortices on an airfoil.

SUMMARY OF THE INVENTION [017] Although the invention may be described in terms of wingtip devices or winglets, the invention is not limited as such. Embodiments of the invention may be construed as enhancing lifting surfaces, particularly to wings or air foils, and more particularly to aircraft, including planar air foils or wings with or without the use of winglets. This invention may also apply to uses, which include either static or dynamic lifting surfaces such as helicopters, projectiles or vessels movingthrough a fluid.

[018] The invention reduces overall drag effects and captures corresponding fluids attributing to drag and conversion of said fluids to laminar, non-turbulent flow. In a particular aspect, this invention provides a method and apparatus for reducing the overall drag on a moving object with wings or airfoils by eliminating wingtip vortices. [019] This invention pertains to tubes having specially configured internal walls, through which a fluid may move with improved efficiency, and more particularly, to such tubes that channel gases, and articles suspended in a gas flow, centrally or axially down the tube. In a particular aspect, this invention provides an apparatus, which captures vortices to eliminate drag forces occurring as turbulent flow or vortices at the end of a plane as it moves through a fluid, such asair or space. This invention also concerns surfaces that incorporate aspects of the specially configured internal walls of those tubes that improve the flow characteristics over the surfaces to produce beneficial results.

[020] When fluid flows through tubes, there will intrinsically be a velocity differential between fluid near the wall of the tube and fluid in the center even if the flow is turbulent. Thus, it has been observed that vortex formation occurs along the edge of a free axisymmetric tubular jet, for example, one exiting a gas to atmosphere. The vortex formation is caused by Kelvin-Helmholtz instability and the vortices as a result of that instability eventually collapse after the flow is vented to the atmosphere. A theory espoused by the inventor holds that if vortices were permitted to 5form and flourish while flowing in the confines of the tube, the result would be a beneficial absorption and organization of the energy within the tube.

[021] Tubes in accordance with the present invention are believed to function superiorly to the prior art. Such tubes are substantially free of baffles or surfaces that are inclined toward the fluid flow within the tube. Preferably even baffles perpendicular to the direction of flow are avoided. lORather this invention provides tubes that embody an expansion chamber containing waveguides or flow guides past which fluid is conducted. The waveguides extend inwardly from the walls of the chamber and are inclined in the direction of fluid flow within the chamber leaving an unobstructed path for the flow of fluid from the inlet to the outlet. The succession of guides so inclined create a series of cavities in which fluid vortices are created because of the velocity of

15fluid flow, and the spinning vortices in turn induce the formation of a boundary layer that might also be termed a "shear boundary" that is slower than the flow in the middle of the unobstructed flow path.

[022] More specifically, a tube for moving a fluid, and more particularly a gas, between an entry end which preferably resembles a venturi inlet where the fluid is introduced and an exhaust

20end where the fluid exits the tube includes a chamber having a series of waveguides. The waveguides extend inwardly from the walls of the chamber and are inclined in the direction of flow with the edges of the waveguides terminating to leave an unobstructed path for fluid flow from the inlet to the outlet. The series of waveguides (also called "flow guides" at times herein) in turn form and define annular guide cavities which are volumes defined by a guide edge

25extending generally in the direction of flow and forming one portion of a partially enclosed volume of each cavity. The inclination of the waveguides results in a structure where each of the guide cavities (which can be readily envisioned by viewing the attached drawings) extends behind and upstream of the guide edge and has a cavity mouth immediately downstream of the guide edge that opens the cavity volume in the direction of flow. Characteristics of the fluid flow

30such as the density and viscosity of the fluid (both of which participate in the calculation of

Reynolds number) are believed to affect the size and configuration of cavities defined by the waveguides. In one embodiment depending upon the characteristics of the fluid flow, each successive guide in the downstream direction may be smaller than a next prior upstream guide. Such a construction would be anticipated more useful in applications where the gas velocity through the chamber is expected to decrease. In such configurations, the tube thus forms an 5effective funnel ending at a tube exit end smaller than a tube entry end. The guides are arranged longitudinally with a smaller end extending toward the exit end extending into a larger end of a next adjacent guide. The larger end of the next adjacent guide extends past the smaller end of its prior flow guide and loops back to taper into smooth connection with the outside of the smaller end of that prior flow guide therein creating a cavity in the guide. In effect, the various lOembodiments of the invention serve to employ vortex turbulence within the guide cavities as a work function to achieve flow and thrust structure modification, by idealizing fluid dynamic interactions into organized geometric structures in a flow continuum. When the flow/waveguide is geometrically configured in a fashion consistent with and sympathetic to the ideal geometry of the fluid dynamic instability being groomed, the flow vector forces also become organized and

15may be directed in a manner that provides allowing an engineered flow continuum protocol providing a benefit such as energy efficiency or shock wave absorption and translation to a fluid continuum with a higher degree of forward momentum.

[023] The collection of the guide smaller ends defines a continuous curved or straight inner line defining an effective inner wall of the tube that funnels gradually and smoothly from the entry 20end to the exit end. That curved inner line may be logarithmic or parabolic or another

continuous curved or straight line. A continuous outside line that tangentially contacts each of the guides outside of the tube may also be drawn between the guides. The outside line may also be straight, logarithmic, or parabolic or any other curved continuous line, though having a higher rate of curvature than does the inner curved line.

25[024] In an alternative embodiment, particularly where the velocity of fluids are relatively high, the waveguides and the cavities that they define can be uniformly sized and spaced thereby greatly improving the efficiency and expense of fabricating the tubes with a series of identical waveguides and guide cavities. In commercial exploitation of this invention, it will often be advisable experimentally to seek a tube design with uniformly sized and spaced waveguides and

30guide cavities because advantages with respect to flow efficiency will nonetheless accrue, and the expense of creating a multi-sized flow-guided tube will be greatly reduced. [025] Gas passing rapidly past the guide cavities induces a cyclic domain of fluid movement or a vortex within each waveguide cavity and a resultant vector of axial fluid movement close to the continuous curved or straight inner line, allowing forces resulting from fluid expansion to enter a cavity, whereupon it is allowed to expand, rotate, reflect and mix. That is, momentum- 5accumulating rotor effects cause a Bernoulli Effect reducing pressure within the cavities. Because the mouth of the guides are large and are relatively unrestricted (by that is meant that fluid does not pass through a restriction to exit the guide cavities), a vortex is induced from a shearing interface between gases within the cavity and the main flow of gas moving down the tube translating kinetic energy from the main flow into the vortex of a respective cavity as well as lOshedding the over-spilling or shedding portion in a relaying effect to successive downstream cavities.

[026] It has been empirically shown that when the tube is installed as a chute for fluid including solids, solid items such as fruit or balls and other particulates depending on their size and the corresponding configuration of the tubular version of the embodiment, may become transported

15through while suspended or may be drawn into some or many of the cavities and routed into or separated from the primary flow, thus preserving the fruit or other item from damage from the side of the tube. It is therefore concluded that the vortices work to form a buffer layer extending generally along a the curved or straight line defining the guide edges from the tube inner walls, hence providing a mode of object, particulate, viscosity, slurry or other object separation where

20their respective sizes cause them to be separated or stripped-away from a primary flow

(throughput fluid jet). The result then is an outer layer of gas moving past the vortices of the waveguides and the tunnel interior wall that is slower than the inner flow of gas nearer the center of the tube. The inner layer then comprises the observed buffer to the inner flow of gas and objects in the inner flow.

25[027] The inventor suggests that the guides induce a density gradient with heavier particles moving to the center of the gas flow and lighter particles moving outward toward the tube interior surface and the vortices. It is suspected that this organization of particles can eliminate vertical flow that is typically produced at free-end wing tips. Specifically, as a fluid jet moves through a tunnel or over a surface-treatment embodiment of the invention, cavitation effects

30caused by and within the guides reorganize fluid-dynamic forces in such a way that force vectors become aligned with the fluid jet's preferred direction of flow, thereby optimizing fluid movement and eliminating the turbulence from the fluid's flow.

[028] In a preferred embodiment of the invention, a tube for moving a fluid, more preferably a gas, between an entry end into which gas is introduced and an exhaust end through which gas 5exits the tube, the tube comprising a closed chamber that has an overall volume that permits expansion of the entry gas, and where the chamber presents to the gas flow a plurality of adjoining adjacent and successive flow guides extending inwardly from the walls of the chamber but terminating to permit a typically central unobstructed path for gas flow from entry to exhaust. Preferably, the inlet has the configuration of a venturi. The waveguides within the chamber are lOinclined generally in the direction of flow thereby defining annular guide cavities between successive inwardly extending waveguide edges and the chamber wall with a cavity mouth open to the unobstructed path; each guide therefore comprises an annular guide cavity volume defined in part by successive guide edges extending generally in the direction of flow and forming a partially enclosed volume upstream of the upstream guide edge and a cavity mouth downstream

15of the guide edge that opens generally without restriction into a region central in the tube where there is unidirectional flow past the guide edges that is relatively unobstructed. The cavity upstream of the guide edge defines a volume that induces the creation of gas vortices when flow occurs, which vortices create a gas boundary layer that moves past the guide edges and cavity mouths more slowly in the direction of flow than the unobstructed flow that is more remote from

20the cavity mouths. A cavity configuration that approximates half of a smoothly-curved, modified torus, and an outer rigid tube wall, encourages the creation of a fluid vortex within the cavity when the flow is established. The approximately toroidal configuration, though preferred, is not essential.

[029] A curved and generally half-toroidal configuration (or generally half-elliptical

25configuration) at the upstream confines encourages vortex formation within the cavity is

preferred. However, it will be understood that fluids will tend to form vortices in any compliant volume, so those in the art will understand the preference for some curvature the upstream end of the waveguide cavities. But even when a curved configuration is absent, beneficial results are obtained. In angular guide cavities, the vortices are formed, and although believed more likely to 30be fragmented, beneficial results are nonetheless realized. [030] According to the implementation of the embodiments, each guide forms an internal cavity with a cavity mouth opening into an inner portion of the tube, the cavities shaped such that a vortex forms within each of the cavities as gas passes through the tube, and the flow of fluid in the tube is unidirectional and axial from the entry end to the exit end.

5[031] Aside from the applications of this invention to obtain advantages in fluid flow though flow enclosures or tubes, this invention enables the modification of surfaces to reduce fluid friction or drag over the surfaces by incorporating surface waveguides similar in shape and function to those described above in tubes. Such modification to a surface over which fluids, particularly gases, may be expected to flow substantially unidirectionally can reduce the frictional lOresistance of the fluid or gas over the surface. Accordingly, advantageous results can be achieved by placement of waveguides having the configuration of the flow guides discussed above on the external surfaces of airfoils and nacelles, e.g., those present on aircraft, search

[032] The disclosed method and apparatus can be better understood with reference to the following illustrations and figures. The apparatuses in the drawing figures are not necessarily to 15scale.

[033] Accordingly, the inventor has reduced to practice a wingtip device affixed to a wing or air foil for the purpose of capturing wingtip vortices and converting them to smooth, laminar flow, comprising a tube or series of tubes for assisting fluid flow between an inlet end opening where fluid is introduced and an outlet end opening through which fluid exits the tube and for

20eliminating wingtip vortices at wingtips accompanying the fluid movement, further comprising a closed chamber intermediate the opening and exhaust ends for receiving the fluid from the inlet, which closed chamber has an overall volume which permits expansion of the entry fluid, wherein the closed chamber presents to the fluid flow a series of waveguides arranged successively in an axial direction and inclined inwardly from interior walls of the closed chamber generally in the

25direction of flow that leave an unobstructed path for fluid flow from the inlet end to the outlet end, the waveguides defining a plurality of annular guide cavities between successive inwardly extending edges of the waveguides and the outer wall of the chamber each annular guide cavity having at least a volume upstream of the guide edge and a cavity mouth open to the

unobstructed path, and the waveguides being sized and spaced such that fluid vortices are

30created within the annular guide cavities when fluid flow occurs, which vortices create a fluid boundary layer that moves past the guide edges and cavity mouths more slowly in the direction of flow than the unobstructed fluid flow more remote from the cavity mouths.

[034] As another embodiment, an aircraft with reduced wingtip vortical drag, comprising a wing or plurality of wings, each wing further comprising a wingtip, a wingtip device in form of 5the embodiment, a means for channeling air from the wingtip into the wingtip device, and the wingtip device affixed to a free end of the wing that is aligned parallel or nearly parallel to a central axis of an aircraft fuselage which receives a stream of vortices from the wing surface.

[035] In yet a further embodiment, an apparatus wherein the means for channeling or collecting fluid from the wingtip into the wingtip device comprises a cowling affixed to the wing lOnear the wingtip, such that wingtip vortices are captured by the cowling before being introduced to the wingtip device upstream open end or as a closed tube, cylinder or cone affixed to a location along a trailing edge of the wing near the wingtip, such that wingtip vortices are directed along the outside surface of the closed tube, cylinder or cone before being introduced to the wingtip device upstream open end.

15 BRIEF DESCRIPTION OF THE DRAWING FIGURES

[036] The accompanying drawings illustrate several embodiments of the invention and, together with the description, serve to explain the principles of the invention according to the embodiments. One skilled in the art will recognize that the particular embodiments illustrated in the drawings are merely exemplary, and are not intended to limit the scope of the present 20invention.

[037] Fig. 1 (PRIOR ART) illustrates how wing tip vortices occur when an object, such as an air foil, wing or other solid body, moves through a fluid or combination of fluids, such as air, space, or water.

[038] Fig. 2 (PRIOR ART) shows another view of how wing tip vortices are produced when an 25object, such as an air foil, wing or other solid body, moves through a fluid or combination of fluids, such as air, space, or liquid.

[039] Fig. 3 (PRIOR ART) illustrates the creation of wingtip vortices as a result of offset or unbalanced pressures being applied to a solid surface moving through a fluid, thereby creating friction or drag on the respective solid surface. [040] Fig. 4 (PRIOR ART) is comprised of three figures: 4a, 4b, and 4c, all of which illustrate how turbulent flow in form of vortices is created by a variety of airfoils passing through a given fluid.

[041] Fig. 5 (PRIOR ART) is a diagram of a conventional wingtip known in the art which 5would create large vortices and higher drag, as well as a blended winglet known in the art for reducing the effects of drag, but not eliminating these effects.

[042] Figs. 6a, 6b, 6c (PRIOR ART) is a series of diagrams illustrating a split spiroid wingtip known in the prior art to reduce the effects of drag on a wingtip, but not eliminating these effects.

[043] Fig. 7a is a graphical representation of how fluid flows through a channeling gas flow lOtube, according to an embodiment of the invention.

[044] Fig. 7b and Fig. 7c show how vortices are collected from various types of wings or airfoils into the embodiment.

[045] Fig. 8 is a static graphical illustration simulating fluid flow through the embodiment matching experimental results.

15[046] Fig. 9 is a longitudinal cross sectional view of a channeling gas flow tube, according to an embodiment of the invention.

[047] Fig. 10 is a longitudinal cross section view of a portion of the tube of Fig. 9 showing vortices in cavities of the respective guides comprising the tubes.

[048] Fig. 11 is a longitudinal cross sectional view of an alternative embodiment of the

20invention, showing an external straight line comprised of a plurality of guides with cavities in which vortices are formed as gas passes the cavities.

[049] Fig. 12 is a plan view of a channeling gas flow tube, according to an embodiment of the invention, integrated with the wing or airfoil at the free end of the wing or airfoil.

[050] Fig. 13a is a three-dimensional view of a channeling gas flow tube in a configuration 25where the embodiment is a part of the wingtip, being termed as integrated with the wing or airfoil.

[051] Fig. 13b is a lateral cross sectional view taken near the intake of the embodiment, where the embodiment and wing intersect. [052] Fig. 13c is a longitudinal cross sectional view of the embodiment. [053] Fig. 13d is a view on the underside of the wing or airfoil.

[054] Fig. 13e shows the embodiment as viewed from beyond the free end, looking towards the embodiment, with the wing or airfoil beyond. [055] Fig. 14 shows a given configuration of the embodiment when integrated with the wing or airfoil.

[056] Fig. 15 shows another possible configuration of the integrated wing type, in an "over- under" style, with multiple channeling gas flow tubes inside a surface boundary encapsulating the embodiment. [057] Fig. 16 shows yet another possible configuration of the integrated wing type, in a "radial- concentric" style, with multiple channeling gas flow tubes inside a surface boundary

encapsulating the entire embodiment.

[058] Fig. 17 shows yet another possible configuration of the integrated wing type, in a "single, coarse" style, with a single channeling gas flow tube. [059] Fig. 18 shows yet another possible configuration of the integrated wing type, in a "single, fine" style, with a single channeling gas flow tube of smaller diameter than the "single, course".

[060] Fig. 19 is a plan view of a channeling gas flow tube, according to an embodiment of the invention, trailing downstream of the free end of the wing or airfoil, yet still connected to the wing or airfoil. [061] Fig. 20a is a three-dimensional view of a channeling gas flow tube in a configuration where the embodiment is a trailing downstream of the wingtip, being termed as trailing or trailing-tube of the embodiment.

[062] Fig. 20b is a lateral cross sectional view taken near the intake of the embodiment, where the embodiment and connection to the wing or airfoil interact. [063] Fig. 20c is a longitudinal cross sectional view of the embodiment.

[064] Fig. 20d is a view of a possible connection type between the embodiment and the wing or airfoil. [065] Fig. 20e shows the embodiment as viewed from beyond the free end, looking towards the embodiment, with the wing or airfoil beyond.

[066] Fig. 21 shows a given configuration of the embodiment when trailing the wing or airfoil.

[067] Fig. 22 shows another possible configuration of the trailing-tube wing type, in an "over- Sunder" style, with multiple channeling gas flow tubes inside a surface boundary encapsulating the embodiment.

[068] Fig. 23 shows yet another possible configuration of the trailing-tube wing type, in a "radial-concentric" style, with multiple channeling gas flow tubes inside a surface boundary encapsulating the entire embodiment. 0[069] Fig. 24 shows yet another possible configuration of the trailing-tube wing type, in a "single, coarse" style, with a single channeling gas flow tube.

[070] Fig. 25 shows yet another possible configuration of the trailing-tube wing type, in a "single, fine" style, with a single channeling gas flow tube of smaller diameter than the "single, course". 5[071] Figs. 26a, 26b 26c illustrate endless possibilities for improving any type of wingtip with the embodiment.

[072] Fig. 27 is an illustration of a variant arrangement of the wingtip vortex suppressor of the invention.

[073] Fig. 28 is a further illustration of the variant configuration shown in Fig. 27. 0 DETAILED DESCRIPTION

[074] Headings of sections provided in this patent application and the title of this patent application are for convenience only, and are not to be taken as limiting the disclosure in any way.

[075] The inventor has conceived, and reduced to practice, channeling gas flow surfaces and5tubes that address the challenges and problems in the art outlined above. Various techniques will now be described in detail with reference to a few example embodiments thereof, as illustrated in the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of one or more aspects and/or features described or referenced herein. However, it will be apparent to one skilled in the art, that one or more aspects and/or features described or referenced herein may be practiced without some or all of these specific details. In other instances, well known process steps and/or structures have not been described in detail in order to not obscure some of the aspects and/or features described or 5reference herein.

[076] One or more different inventions may be described in the present application. Further, for one or more of the inventions described herein, numerous alternative embodiments may be described; it should be understood that these are presented for illustrative purposes only. The described embodiments are not intended to be limiting in any sense. One or more of the lOinventions may be widely applicable to numerous embodiments, as is readily apparent from the disclosure. In general, embodiments are described in sufficient detail to enable those skilled in the art to practice one or more of the inventions, and it is to be understood that other embodiments may be utilized and that structural, logical, software, electrical and other changes may be made without departing from the scope of the particular inventions. Accordingly, those

15skilled in the art will recognize that one or more of the inventions may be practiced with various modifications and alterations. Particular features of one or more of the inventions may be described with reference to one or more particular embodiments or figures that form a part of the present disclosure, and in which are shown, by way of illustration, specific embodiments of one or more of the inventions. It should be understood, however, that such features are not

201imited to usage in the one or more particular embodiments or figures with reference to which they are described. The present disclosure is neither a literal description of all embodiments of one or more of the inventions nor a listing of features of one or more of the inventions that must be present in all embodiments.

[077] A description of an embodiment with several components in contact, relation, or 25communication with each other does not imply that all such components are required. To the contrary, a variety of optional components may be described to illustrate a wide variety of possible embodiments of one or more of the inventions and in order to more fully illustrate one or more aspects of the inventions. Similarly, although process steps, method steps, algorithms or the like may be described in a sequential order, such processes, methods and algorithms may 30generally be configured to work in alternate orders, unless specifically stated to the contrary. In other words, any sequence or order of steps that may be described in this patent application does not, in and of itself, indicate a requirement that the steps be performed in that order. The steps of described processes may be performed in any order practical. Further, some steps may be performed simultaneously despite being described or implied as occurring non-simultaneously (e.g., because one step is described after the other step). Moreover, the illustration of a process 5by its depiction in a drawing does not imply that the illustrated process is exclusive of other variations and modifications thereto, does not imply that the illustrated process or any of its steps are necessary to one or more of the invention(s), and does not imply that the illustrated process is preferred. Also, steps are generally described once per embodiment, but this does not mean they must occur once, or that they may only occur once each time a process, method, or algorithm is lOcarried out or executed. Some steps may be omitted in some embodiments or some occurrences, or some steps may be executed more than once in a given embodiment or occurrence.

[078] When a single device or article is described, it will be readily apparent that more than one device or article may be used in place of a single device or article. Similarly, where more than one device or article is described, it will be readily apparent that a single device or article 15may be used in place of the more than one device or article.

[079] The functionality or the features of a device may be alternatively embodied by one or more other devices that are not explicitly described as having such functionality or features. Thus, other embodiments of one or more of the inventions need not include the device itself.

[080] Techniques and mechanisms described or referenced herein will sometimes be described 20in singular form for clarity. However, it should be noted that particular embodiments include multiple iterations of a technique or multiple instantiations of a mechanism unless noted otherwise. Process descriptions or blocks in figures should be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps in the process. Alternate implementations are 25included within the scope of embodiments of the present invention in which, for example, functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those having ordinary skill in the art.

Detailed Description of Embodiments [081] For a flow of turbulent fluid 105 to be converted to smooth, laminar flow 106 of the same fluid, the given fluid flow will pass through a channeling gas flow tube 10, according to an embodiment of the invention. The tube 10 can be in its natural shape or bound by a surface boundary 11 to reduce the effects of drag 18 of the embodiment itself.

5[082] Fig. 7a is a graphical representation illustrating a cross-section through a preferred embodiment of the invention with a preferred condition of turbulent fluid flow 105 entering the series of waveguides 16 bound by an outer shell 11 whereby internal vortices 40 are created. Fig. 9, as detailed below, further develops the simplified concept as portrayed in Fig 7a. As the fluid 100 enters the first flow-guide 36, regardless of state, be it laminar or turbulent, the fluid flow 100 lOwill move through the channeling gas flow tube 10. The vortex 40 formed inside cavity 28 is formed from the fluid flow 100 moving past cavity 28, and establishes a stable structure of fluid 106 resulting in thrust exiting the last succession waveguide 24.

[083] According to the invention, vortices 40 are established shortly after flow 100 is commenced, with each vortex 40 arising naturally from edge effects of flow 100 when it

15encounters mouths 32 of cavities 28. It is one of the advantages of the invention that, once vortices 40 are established, and particularly when sizing of cavities 28 is accomplished as described above, the direction of flow in vortices 40 at mouths 32 is always in parallel with, and aligned with, the bulk of flow 100. Wind tunnel experiments conducted by the inventor have shown that this effect of vortices 40 results in development of a smooth boundary layer running

20substantially along line 37. This boundary layer may effectively entrain fluid in flow 100, thus accelerating flow 100 or reducing drag on flow 100 normally caused by normal edge effects experienced by a fluid flowing along a surface.

[084] The invention applied to any type of wing or foil 1 with a rectangular tipped edge 4 or a round tipped edge 5, whether attached to the wing 1 as a winglet 19 or in a trailing-tube 21

25configuration, has been designed to not only convert the wingtip vortices 105 but also to collect the fluid flow 100 from the free-end of the wingtip 15, as illustrated in Fig. 7b and Fig. 7c.

[085] Computational fluid dynamic ("CFD") studies on waveguide structures 16 of this invention provide insight into the fluid dynamics of a series of waveguides, such as those described in a preferred conception of the embodiment. Fig. 8 illustrates the results of a CFD simulation of inlet vortex flowlines 105 transitioning to spinning flowlines 107 then smoothing out to non-turbulent flow 106.

[086] Introduced in Fig. 7a, Fig. 9 is a longitudinal cross sectional view of a channeling gas flow tube, according to an embodiment of the invention. According to the embodiment, tube 10 for 5moving fluid 100 or for moving articles within fluid 100 may be defined between an entry end 12 into which fluid 100 is introduced and an exit end 14 through which fluid 100 exits tube 10. Tube 10 defines a chamber into which a fluid is conducted with the inlet having a general constriction of a venturi and comprises a plurality of adjoining adjacent guides 16, each guide 16 comprising a curved outer half of a approximating a modified torus forming toroidal grooves or lOwaveguides opening inward. The chamber into which the fluid 100 is conducted from the entry end 12 has an overall volume that permits expansion of the entry fluid. Each guide 16 in this embodiment is adjacent to a next guide that is more constricted in diameter and volume, except of course the last guide 24, which ends the tube or chamber 10. The plurality of adjacent guides 16 connected together at their mouths forms a closed tube wall 26 with each guide 16 forming a

15cavity 28 with a cavity wall 30 around the cavity 28 and a cavity mouth 32 opening into tube 10.

Whether tube 10 is enclosed by a boundary 11 or not does not affect the internal conversion of flow of fluid(s); rather it may be considered to reduce the overall effects of drag 7 upon the tube 10 in its resulting outer form 38 as attached to the foil or wing 1.

[087] According to a preferred embodiment, cavity wall 30 of guide 33 extends upward beyond 20its mouth 32; that is, toward entry end 12, over a next prior adjacent guide 34, again except a first guide 36 at the entry end 12 which is also shaped generally similar to the other guides but does not extend over a prior guide. The plurality of guides 16 is disposed within the chamber such that the mouths 32 of guides 16 are aligned along a curved inner line 37 between entry and exit ends 12, 14. The curved inner line 37 may be logarithmic or parabolic or another form of a 25continuous curved line. Also, an outer line 38 tangential to cavity walls 30 of said plurality of guides 16 outside of tube 10 is curved, which line may be logarithmic, parabolic or another form of a continuous curved line. Clearly, line 38 outside tube 10 has a curvature greater than curved inner line 36 past guide mouths 32.

[088] Guides 16 are shaped such that a vortex 40 forms within each cavity 28 as fluid 100

30passes through tube 10, while promoting smooth flow 106 through tube 10. Thus, cavity wall 30 of each flow guide 16 in extending past the next prior flow guide 34 loops back toward exit end 14 to taper into a smooth connection with that next prior flow guide 34. Guides 16, in this embodiment are generally nozzle shaped, with each successive guide being smaller than a next prior guide such that gas entering entry end 12 is funneled through tube 10 and out exit end 14, 5which is smaller than entry end 12.

[089] According to another embodiment, the plurality of guides 16 is disposed such that outer line 38 is tangential to cavity walls of said plurality of guides outside of tube 10 is straight, as shown in Fig. 7a and Fig. 11. Fig. 11 is a longitudinal cross sectional view of an alternative embodiment 10 of the invention, showing an external straight line 38 comprised of a plurality of lOguides 16 with cavities 28 in which vortices 40 are formed as fluid 100 passes cavities in the chamber from entrance 12 to exit 14.

[090] In a preferred embodiment of the invention, tube 10 either as a singular channeling tube or as multiple channels, is located at the free-end 15 of a wing 1 in an integrated configuration 19. Fig. 12 shows a plan view, looking down onto a wing 1 showing a preferred embodiment of the

15device attached directly to a free-end 15 of wing 1 which may be terminated with either a standard, non-modified wingtip or with any general sweeping wingtip, as proposed in Fig. 26a, Fig. 26b, or Fig. 26c. Focusing on the referenced preferred embodiment 19, Fig. 13a depicts a three-dimensional view whereas tube 10 is built in to wing 1 and from wing an inlet plenum 25 extends into the mouth of an inlet cowling 9 through which fluid 100 is expected to enter entry

20end 12 of tube 10. Cowling 9 may be formed congruently with outer boundary 11 to surround the channeling tube 10 or it may be formed independently. Cowling 9 further detailed in corresponding cross-sectional views Fig. 13b and Fig. 13c is presented as an extension of outer boundary 11 of tube 10 as well as a formed section of wingtip 23. An inlet plenum 25 at the very end of wingtip 23 is envisaged to extend into cowling 9 both atop and underneath wing 1 as a

25way for fluid 100 moving along the wing 1 to be extended into chamber 10. Fig. 13d depicts an alternate view from beneath, looking up at wing 1 and cowling 9. Considering a view apart from the aircraft, Fig. 13e proposes a view of one possible integrated configuration 19 of the wingtip 23 viewed from beyond the free-end of the wing 15, looking toward the invention as it could be attached to an aircraft. Fig. 14 illustrates a basic configuration of an integrated configuration 19

30with a singular tube 10 bound by the enclosing nacelle 11. [091] Multiple possible configurations of the embodiment in an integrated form 19 with the wingtip 23 are proposed in Figs. 15, 16, 17 and 18. Illustrations referenced are not intended to be exhaustive; merely they are intended to qualify the invention as not being limited to a singular tube, either bound by a common sheath 11 or in multiple devices that are either enclosed by a 5common sheath or nacelle 11 or by several individual sheaths or nacelles 11. Within a common boundary 11, it is also possible to configure the device in more than one channeling tube 10, as depicted in the cross-sections 13 of Figs. 15-18. Whilst it may be misunderstood that nacelle 11 always follows the outer boundary line 38, it should be realized as a possibility but not a requirement. The outer form of the nacelle 11 may follow any form as long as it encompasses lOthe chosen series of waveguides 16.

[092] Similar to Fig. 12, Fig. 19 depicts a plan view of an alternative configuration of the embodiment hereinafter referred to as a "trailing-tube" configuration or design. In the trailing- tube configuration, an idealized embodiment of the invention trails behind or downstream of wingtip 23, attached by an extension 27 which connects the invention to a free-end 15 of the wing

151 which may be terminated with either a standard, non-modified wingtip or with any general sweeping wingtip, as proposed in Figs. 26a, 26b, or 26c. With a trailing-tube configuration in mind, Fig. 20 illustrates a three-dimensional view whereas tube 10 is attached downstream of wingtip 23 and from wing an extension tube 27 connects the wingtip to either an inlet cowling 9 or directly to tube mouth inlet 12 through which fluid 100 is expected to enter. Extension 27 may

20be formed continuously with wingtip 23 or it may be formed as an independent device which could be separately attached either as an after-market installation or integrated into wingtip 23 as a preferred embodiment of the invention. Cowling 9 further detailed in corresponding cross- sectional views Fig. 20b and Fig. 20c is presented as an extension of outer boundary 11 of tube 10. In the trailing-tube configuration, the attachment bar 27 at the very end of wingtip 23 is

25envisaged to extend into cowling 9 as a way for fluid 100 moving along the wing 1 to be extended into chamber 10. Fig. 20d depicts an alternate view from beneath, looking up at wing 1 and cowling 9. Considering a view apart from the aircraft, Fig. 20e proposes a view of one possible integrated configuration 21 of the wingtip 23 viewed from beyond the free-end of the wing 15, looking toward the invention as it could be attached to an aircraft. Fig. 21 illustrates a

30basic configuration of a trailing-tube configuration 21 with a singular tube 10 bound by the enclosing nacelle 11. [093] Multiple possible configurations of the embodiment in a trailing-tube configuration 21 with the wingtip 23 are proposed in Figs. 22, 23, 24 and 25. Illustrations referenced are not intended to be exhaustive; merely they are intended to qualify the invention as not being limited to a singular tube, either bound by a common sheath 11 or in multiple devices that are either 5enclosed by a common sheath or nacelle 11 or by several individual sheaths or nacelles 11. Within a common boundary 11, it is also possible to configure the device in more than one channeling tube 10, as depicted in the cross-sections 13 of Figs. 22-25. Whilst it may be misunderstood that nacelle 11 always follows the outer boundary line 38, it should be realized as a possibility but not a requirement. The outer form of the nacelle 11 may follow any form as lOlong as it encompasses the chosen series of waveguides 16.

[094] Figs. 27 and 28 show a variant of a wingtip vortex capture device according to an embodiment of the invention. Fig. 27 shows the arrangement, in view of an entire aircraft, of the portion of wingtip shown in Fig. 28. Fig. 28 shows a variant wingtip vortex capture device, according to an embodiment of the invention, where a leading edge of a wing terminates in a

15centerline of a wingtip vortex capture device of the invention, which device is arranged aft of the end of the wing such that vortices created along the wing are shed efficiently directly into the wingtip vortex capture device, which converts the vortices into substantially linear jet flow emitting in an aft direction relative to the flight of the aircraft shown in Fig. 27, thus converting the drag of wingtip vortex shedding into a forward thrust component, improving fuel efficiency of

20the aircraft.

[095] It will be appreciated by one having ordinary skill in the relevant art that the

arrangements and embodiments disclosed herein are exemplary in nature, and other equivalent arrangements are envisioned by the inventor and will be appreciated by one having ordinary skill in the art.

25

Claims

What is claimed is:

1. A wingtip device affixed to a wing or airfoil for the purpose of capturing wingtip vortices and converting them to smooth, laminar flow, comprising:

a tube or series of tubes for assisting fluid flow between an inlet end opening where fluid isintroduced and an outlet end opening through which fluid exits the tube and for eliminating wingtip vortices at wingtips accompanying the fluid movement, further comprising:

a closed chamber intermediate the opening and exhaust ends for receiving the fluid from the inlet, which closed chamber has an overall volume which permits expansion of the entry fluid;

wherein the closed chamber presents to the fluid flow a series of waveguides arranged successively in an axial direction and inclined inwardly from interior walls of the closed chamber generally in the direction of flow that leave an unobstructed path for fluid flow from the inlet end to the outlet end;

the waveguides defining a plurality of annular guide cavities between successive inwardly extending edges of the waveguides and the outer wall of the chamber each annular guide cavity having at least a volume upstream of the guide edge and a cavity mouth open to the unobstructed path;

the waveguides being sized and spaced such that fluid vortices are created within the annular guide cavities when fluid flow occurs, which vortices create a fluid boundary layer that moves past the guide edges and cavity mouths more slowly in the direction of flow than the unobstructed fluid flow more remote from the cavity mouths.

2. An aircraft with reduced wingtip vortical drag, comprising:

a wing or plurality of wings, each wing further comprising:

a wingtip,

a wingtip device in form of the embodiment,

a means for channeling air from the wingtip into the wingtip device,

the wingtip device affixed to a free end of the wing that is aligned parallel or nearly parallel to a central axis of an aircraft fuselage which receives a stream of vortices from the wing surface.

3. The device in accordance with claim 2 wherein the means for channeling fluid from the wingtip into the wingtip device comprises:

a cowling affixed to the wing near the wingtip, such that wingtip vortices are captured by the cowling before being introduced to the wingtip device upstream open end.

5

4. The device in accordance with claim 2 wherein the means for channeling air from the wingtip into the wingtip device comprises:

a closed tube, cylinder or cone affixed to a location along a trailing edge of the wing near the wingtip, such that wingtip vortices are directed along the outside surface of the closed tube, lOcylinder or cone before being introduced to the wingtip device upstream open end.