Patent Publication Number: US-8967326-B2

Title: Channeling gas flow tube

Description:
RELATED APPLICATIONS 
     This application is a continuation of U.S. patent application Ser. No. 13/540,492, titled “CHANNELING GAS FLOW TUBE”, filed on Jul. 2, 2012, which is a continuation-in-part of U.S. patent application Ser. No. 12/238,253, titled “CHANNELING GAS FLOW TUBE”, filed on Sep. 25, 2008 and issuing on Jul. 3, 2012 as U.S. Pat. No. 8,210,309, the entire specification of which is incorporated herein by reference. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     This invention pertains to tubes through which a fluid may move, and more particularly, to such a tube that channels gases, and articles suspended in a gas flow, centrally or axially down the tube. 
     2. Discussion of the State of the Art 
     Backpressure in engine exhausts is a well-known phenomenon that robs energy from the engine. Mufflers and catalytic converters contribute to the backpressure. It is a primary object of the present invention to provide a tube functional as an exhaust pipe that reduces backpressure and reduces or eliminates the need for a muffler. 
     More generally, many devices known in the art rely on fluid flow, mufflers being one example. Other examples where fluid flow may have deleterious effects include, but are not limited to, firearms (shock waves in barrels reduces kinetic energy of projectile fired and causes extreme noise), projectile flight (drag on projectile reduces range and may destabilize flight), aircraft wings and other airfoils (drag reduces efficiency and turbulence may adversely impact left generated by an airfoil), terrestrial vehicles (drag reduces efficiency), and jet engines (again, drag from fluid flows reduces efficiency). What is needed is a way to reduce deleterious effects of turbulence and shock waves in systems relying on fluid flows, to improve the efficiency or effectiveness of those systems. 
     SUMMARY OF THE INVENTION 
     A tube includes a series of guides with each successive guide smaller than a next prior guide. The tube thus forms an effective 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, various embodiments of the invention serve to employ turbulence 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 may 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. Put another way, the invention provides an effect analogous to Faraday&#39;s Law, in which changes in a magnetic field induce electric current through a conductor; in the case of embodiments of the invention, fluctuations of a flow continuum are employed to accelerate fluid current through a conduit or across a surface treated according to the invention. In Faraday&#39;s Law, greater magnetic flux increases electric current; according to the invention, greater pulse/noise/flux amplitude provides more fluid acceleration and laminar flow (or a higher degree of forward momentum). 
     The collection of the guide smaller ends defines a continuous curved inner line defining an effective inner wall of the tube that funnels gradually and smoothly from the entry end to the exit end. That curved inner line may be logarithmic or parabolic or another continuous curved 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. 
     Gas passing rapidly past the guide cavities induces a domain of axial fluid movement close to the continuous curved 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-accumulating rotor effects causes a Bernoulli effect reducing pressure within the cavities. Because the mouth of the guides are large, 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 shedding the over-spilling or shedding portion in a relaying effect to successive downstream cavities. 
     It has been empirically shown that when the tube is installed as an automotive exhaust pipe, gas exits the tube with reduced sound and more efficiently as measured by □increased increased performance, measured both in horsepower and in torque, as indicated in vehicle dynamometer tests. It has also been shown empirically that when the tunnel is employed as a chute, 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 through 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 from the tube inner walls, hence providing a mode of object, particulate, viscosity, slurry or other object separation where their 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 and the tunnel interior wall 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 When installed as part of an engine exhaust pipe as mentioned above, the device has been found to be an effective muffler without using conventional baffles and silencers that seek to cancel shockwaves, in a manner consistent with cavity resonance effects. Expansive forces are utilized or expended as a motive force to accelerate a fluid jet axially, so if used their expansive potential lowers the potential amplitude of sound or compression waves, thereby reducing sound without using conventional baffling. It has also been found that a change in the dimensions of the guides changes engine exhaust sound, usually lowering an audible frequency or pitch; when used as a ballistic arms silencer, the acoustic bass response is deeper. The silencer&#39;s flashpoint length is also extended, indicating compression waves have expanded. Expanding waves are characteristic of an expansion chamber effect, but waves being stretched along a trajectory (such as sound/light, are characteristic of Doppler Shift). 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 reduces or eliminates compression waves that are found in conventional automobile exhaust systems. Specifically, as a fluid jet moves through a tunnel or over a surface-treatment embodiment of the invention, cavitation effects caused by and within the guides reorganize fluid-dynamic forces in such a way that force vectors become aligned with the fluid jet&#39;s preferred direction of flow, thereby optimizing fluid movement and reducing heat and noise generation. Shockwaves of an initial flow continuum are employed as a motive force causing cavitation effects to become beneficial in accomplishing that optimization. It is also suspected that the funneling effect of the outer gas flow along the tube inner wall contributes to a partial destruction of compression waves in the exhaust. The outer gas layer also acts as a smooth boundary to the inner flow which promotes even flow to the inner flow. 
     In a preferred embodiment of the invention, a tube for moving gas between an entry end into which gas is introduced and an exit end through which gas exits the tube, the tube comprising a plurality of adjoining adjacent□ guides, each guide comprising an outer half of a smoothly-curved, modified torus, and an outer rigid tube wall, is disclosed. According to the embodiment, 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. 
     According to another embodiment, the tube further comprises a plenum between the outer rigid tube wall and a plurality of outer surfaces of the plurality of adjoining adjacent guides, the plenum further comprising a plurality of air inlets proximate to the inlet end of the tube, and an outlet nozzle at the exit end of the tube which is adapted to receive exhaust gas as it exits the tube. The passage of high-speed exhaust gases through the outlet nozzle causes a pressure drop that pulls in ambient air from the plenum, the flow of air from the air inlets through the plenum to the outlet nozzle acting to cool the external surface of the tube. 
     According to another embodiment, the tube acts as a muffler for an internal combustion engine. According to yet another embodiment, the tube acts as a silencer for a firearm. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWING FIGURES 
       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 invention. 
         FIG. 1  is a longitudinal cross sectional view of a channeling gas flow tube, according to an embodiment of the invention. 
         FIG. 2  is a longitudinal cross section view of a typical guide of which the tube of  FIG. 1  is comprised. 
         FIG. 3  is a longitudinal cross section view of a portion of the tube of  FIG. 1  showing vortices in cavities of the respective guides comprising the tubes. 
         FIG. 4  is a longitudinal cross sectional view of an alternative embodiment of the invention, showing an external straight line comprised of a plurality of guides with cavities in which vortices are formed as gas passes the cavities. 
         FIG. 5  is a perspective view of the tube of  FIG. 1 . 
         FIG. 6  is a diagram of a novel muffler design, according to a preferred embodiment of the invention. 
         FIG. 7  is a diagram of a novel firearm silencer design, according to an embodiment of the invention. 
         FIG. 8  is a diagram of a novel firearm ammunition design, according to an embodiment of the invention. 
         FIG. 9  (PRIOR ART) is a diagram of a K-type firearm silencer known in the art. 
         FIG. 10  is a cross-sectional view of an airplane wing or airfoil modified in accordance with an embodiment of the invention. 
         FIG. 11  is a diagram illustrating various aspects of a mechanism for converting turbulent flow into orderly flow, according to an embodiment of the invention. 
         FIG. 12  is a diagram showing exemplary modifications to a truck to reduce drag and improve fuel efficiency thereof, according to an embodiment of the invention. 
         FIG. 13  is a diagram showing an exemplary modification of a jet engine to reduce turbulence and drag and improve fuel efficiency thereof, according to an embodiment of the invention. 
         FIG. 14  is a diagram of a novel jet engine design according to an embodiment of the invention. 
     
    
    
     DETAILED DESCRIPTION 
     The inventor has conceived, and reduced to practice, a channeling gas flow tube that addresses 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 reference herein. 
     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 inventions 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 skilled 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 limited 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. 
     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. 
     A description of an embodiment with several components in communication 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 generally 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 by 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 carried 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. 
     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 may be used in place of the more than one device or article. 
     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. 
     Techniques and mechanisms described or referenced herein will sometimes be described in 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 included 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 
       FIG. 1  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 moving gas  100  or for moving articles within gas  100  may be defined between an entry end into which gas  100  is introduced and an exit end through which gas  100  exits tube  10 . Tube  10  comprises a plurality of adjoining adjacent guides  16 , each guide  16  comprising an outer half of a modified torus□ forming toroidal grooves opening inward. Each guide  20  is adjacent to a next guide  22 , except of course the last guide  24 , which ends the tube  10 . The plurality of adjacent guides  16  connected together at their mouths forms a closed tube wall  26  with each guide  16  forming a cavity  28  with a cavity wall  30  around the cavity  28  and a cavity mouth  32  opening into tube  10 . 
     According to a preferred embodiment, cavity wall  30  of guide  33  extends upward beyond its 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 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 continuous 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 . 
     Guides  16  are shaped such that a vortex  40  forms within each cavity  28  as gas  100  passes through tube  10 , while promoting smooth flow 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  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 , which is smaller than entry end  12 . 
     According to another embodiment, the plurality of guides  16  is disposed such that outer line  38  tangential to cavity walls of said plurality of guides outside of tube  10  is straight. 
       FIG. 2  is a longitudinal cross section view of a typical guide  16  of which the tube of  FIG. 1  is comprised.  FIG. 3  is a longitudinal cross section view of a portion of the tube of  FIG. 1  showing vortices  40  in cavities of the respective guides comprising the tubes. 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 encounters 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 substantially 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. 
     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, with angular momentum that is also compressible. A compressible form, whether mechanical or fluidic in nature, is known to have the ability to absorb shocks (that is, shock waves or sudden, severe compressions waves). In the case of the stable fluid structure here, the absorbed shock is either transformed into additional rotation, or absorbed in the same manner as would be accomplished by a spring or mechanical shock absorber. 
       FIG. 4  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 guides  16  with cavities  28  in which vortices  40  are formed as gas passes cavities from entrance  12  to exit  14 . 
       FIG. 5  is a perspective view of the exterior of tube  10  of  FIG. 1 . 
       FIG. 6  is a diagram of a novel muffler  600 , according to a preferred embodiment of the invention. According to the embodiment, muffler  600  comprises a forward exhaust gas intake  601 , a main body  604 , and an exhaust gas exit  605  located distally from intake  601 . Muffler  600  further comprises, at the forward (that is, distal from exit  605 ) end of body  604 , an external shroud  602  which is penetrated by a plurality of air intake vents  603  generally aligned axially along shroud  602  (although other arrangements are possible; the arrangement shown is merely exemplary; furthermore, some embodiments may omit shroud  602  and vents  603  altogether). As in the case of tube  10  shown in previous figures, exhaust gas flows from intake  601  to exit  605  in a generally axial direction relative to muffler  600 . Internally, muffler  600  is comprised of a plurality of guides  611 - 614  of progressively greater length (proceeding axially from intake  601  to outlet  605 ). Optionally, interior surfaces of guides  611 - 614  may be modified along their portions  621 - 624  that are downstream of each guide&#39;s vortex-inducing cavity, in effect harnessing a scaled-down version of the same effect as is used by the invention overall, to further smooth flow along the inner surfaces of guides  611 - 614 . One role of the vortex rotation in cavities  611  is to act as a “mixer” that dissipates pressure pulses originating from for example an engine&#39;s exhaust by converting it, via the vortex, into orderly axial motion. Also optionally, when vents  603  are used, exit component  605  comprises an inner surface  630  shaped to form a nozzle  650  at the exit of the final guide  614 , such that the passage of fast-flowing fluid (exhaust gases) through the nozzle will create a low pressure point and therefore entrain air that enters via vents  603  and flows through plenum  640  (formed between the external walls of guides  611 - 614  and the internal wall of main body  604 ). This axial of cooler ambient air, caused to flow by the vacuum created by nozzle  650 , acts to cool external surfaces of muffler  600  and to also cool the exhaust gases exiting from final guide  614  and passing through nozzle  605 . It has been found, as described above, that the entrainment of exhaust gases by the boundary layer cause by vortices  40  in guides  611 - 614  may actually draw a slight vacuum on an engine emitting the exhaust gases, in contrast to the usual effect of mufflers, which exert a back pressure on the engine, reducing its efficiency. Moreover, the embodiment may optionally be outfitted with a turbine shaft for a high-torque turbocharger, in which the shaft extends forward and outside of the embodiment to drive a pump for a secondary air injection (turbocharging). 
       FIG. 7  is a diagram of a novel firearm silencer  700 , according to an embodiment of the invention. According to the invention, silencer  700  is placed at the open business end of a gun barrel  702 , and admits both bullet  730  and high velocity gases  725  contained within inner wall  701  of barrel  702  at intake  720 . Silencer  700  comprises an external rigid tubular wall  710 , which encloses a cylinder defined by its inner wall  711 . Aligned along inner wall  711  are a plurality of guides  721   a - n , each of which operates as described above to establish vortices  726  that in turn act, via each cavity&#39;s mouth, to align force vectors axially along the interior of the cylinder through which bullet  730  passes. Importantly, shock waves present in gases  725  exiting a gun&#39;s barrel  702  after firing of bullet  730  are dissipated by the action of the plurality of guides  721   a - n , such that a substantial portion of the kinetic energy of such shock waves is dissipated by setting up vortices  726  (since prior to firing vortices  726  would not typically exist, each cavity  721   a - n  acts to reduce the energy of incident shock waves by receiving gases and establishing vortices  726 . Furthermore, the aligned force vectors and the resulting smoothed boundary later moving axially may accelerate bullet  730 . Moreover, it has been observed that exhaust gases exiting silencer  700  tend to be highly collimated, with the result that heat and sound are carried rapidly away from silencer  700  (and thus from the person who fired the gun). It is believed that this highly-collimated exit gas geometry, coupled with the incremental acceleration of bullet  730  by the conversion of shock waves into vortices  726  will serve to increase the range of a given ammunition type by establishing a higher bullet exit velocity and reducing drag when bullet  730  initially leaves silencer  700 . 
       FIG. 9  (PRIOR ART) is a diagram of a K-type firearm silencer known in the art, and is provided to show how the modified silencer  800  of  FIG. 8  differs from the prior art. Specifically, prior art silencer  900 , of a type known as “K-type”, comprises an entrance  901  that admits high-velocity gases from a gun barrel, and a series of truncated conical sections  902   a - n , aligned axially along the length of silencer  900  with their bases oriented toward the forward (exit) end of silencer  900 . Each section  902   a - n  further comprises a plurality of holes  903   a - n  which permit high-speed gases to exit into plenum  910 , thus dissipating compression or shock waves by converting them into turbulent flows and thereby reducing a gun&#39;s acoustic signature when fired. 
     Comparing the prior art silencer illustrated in  FIG. 9  with the silencer embodiment illustrated in  FIG. 7 , several important differences may be noted. Typical K-type gun silencers feature circular expansion vents into surrounding expansion chambers. The singular compression wave from the gun blast is allowed to gradually expand. By contrast, according to the embodiment, the silencer of  FIG. 7  works in the opposite way, with different stage contours with drastically different fluid characterization, and without expansion vents. According to the embodiment, the object is to conserve all the energy of the shockwave and use it as a work function to accelerate the flow (and therefore also to accelerate bullet  730 ), instead of following the approach of conventional silencers by providing “dead-end” expansion chambers where kinetic energy is lost due to cancellation effects. Allowing compression waves to expand and cancel creates an energy conservation condition where thermal heat is generated. In the embodiment, less heat is generated because the kinetic energy moves through the embodiment to increase the velocity of exiting gases (and bullet  730 ). In effect, the embodiment&#39;s toroidal cavity is a temporary domain where compression waves are “invited” to occupy the space, expand, spin and roll ideally as a singular ring vortex, and then to apply its “traction” to the throughput jet-stream, thereby accelerating it. Ideally, all the kinetic energy of the pressure impulse of shockwaves is translated into axial acceleration. 
     Note that it is possible to reverse the orientation of cavities  721   a - n  and thereby to cause an increase in exit pressure and a corresponding decrease in exit velocity; such an approach may be useful for example for a steam wand in an espresso machine. 
       FIG. 8  is a diagram of a novel firearm ammunition design, according to an embodiment of the invention. Bullet  801  has been modified, according to the embodiment, in that bullet  801  comprises a plurality of cavities  803   a - n  and  802   a - n  similar to cavities  28  above. Cavities  802   a - n ,  803   a - n  are toroidal, each forming a complex surface of rotation around the centerline of bullet  801 . Similar to the mechanisms described above, cavities  802   a - n ,  803   a - n  enable vortices to be established within their respective interiors. Cavities  803   a - n  are distributed along the curved forward portion of bullet  801 , and cavities  802   a - n  are distributed along the cylindrical after portion of bullet  801 . Collectively, these cavities  802   a - n ,  803   a - n  cause a smooth boundary layer to be established, as described above, and thus reduce aerodynamic drag on bullet  801 . Similarly, bullet  810  comprises cavities  812   a - n  along its curved forward end, for the same purpose. Additionally, bullet  810  has a modified rear surface  811 , which instead of being planar comprises a half-toroidal depression, which allows vortex  815  to form, thus reducing turbulence at the trailing edge of bullet  810  as it travels through the atmosphere. Finally, the lower part of  FIG. 8  illustrates a complete round of ammunition comprising cartridge  820  and a modified bullet  801 . 
       FIG. 10  is a cross-sectional view of two modified airplane wings (or airfoils), each modified in accordance with an embodiment of the invention. According to the embodiment, airfoil  1000  is conventional in design, but further comprises a plurality of cavities  1001  along its leading upper edge. Cavities  1001  act in the same fashion as cavities  28  described above, establishing vortices within the cavities and thus facilitating establishment of a smooth, low-drag boundary layer along the upper surface of airfoil  1000 . Since realignment of force vectors by vortices within cavities  1001  will tend to accelerate fluid (i.e., gas) flowing along the upper surface, not only will drag forces on airfoil  1000  be reduced, but also lift will be improved since there will be a greater pressure differential between the lower and upper edges of airfoil  1000  compared to conventional designs. Airfoil  1010  is similarly conventional in design, except that it further comprises two set of cavities  1011 ,  1012 , one on the upper surface and one on the lower surface of the airfoil  1010 . This arrangement serves to reduce drag forces acting to retard motion (to the left) of airfoil  1010  through the atmosphere, although at the cost of no net effect on lift (as compared with airfoil  1000 , which has drag reduced by a lesser amount but also has enhanced lift properties). It will be appreciated by one having ordinary skill in the art that various configurations of cavities are possible, according to the invention, each with its own benefits, and any of which may be used according to the invention. 
       FIG. 11  is a diagram illustrating various aspects of a mechanism  1100  for converting turbulent flow into orderly flow, according to an embodiment of the invention.  FIG. 11  illustrates a single typical stage of a device such as that illustrated in  FIG. 1 , and is provided here for clarity and more detail. According to the embodiment, gases (or any fluids) flow from inlet aperture or entrance  1120  through a tunnel volume  1123 , exiting through an outlet aperture or exit along line  1103  and then displaying a thrust profile  1130  after exit (this profile may vary depending on operating point of the system). Volume  1121  is a typical cavity volume in which a vortex is established, and volume  1122  is a working volume with an outer wall comprised of a portion  1110  with a convex profile and a subsequent portion  1111  with a concave profile (“subsequent” in the sense that it is downstream relative to the gas flow  1123 , which is shown going from left to right), the transition occurring at a point in length signified by line  1102 . 
       FIG. 12  is a diagram showing exemplary modifications to a truck  1200  to reduce drag and improve fuel efficiency thereof, according to an embodiment of the invention. According to the embodiment, various cavities may be established along various surfaces of truck  1200  along which air flow occurs during travel of truck  1200 . For example, in some embodiments a truck&#39;s  1200  cab may be modified by the addition of vertical cavities on the top  1201  and sides  1202  of the cab, thus reducing drag caused by the atmosphere as the cab moves (to the left) during truck  1200  operation. Similarly, cavities  1210  may be placed on the top and sides of the trailer of trick  1200 , and cavities  1211  may be placed on the underside of the trailer of truck  1200  as shown; in each case, such cavities act to reduce drag caused by airflow along the trailer as truck  1200  moves to the left. It will be appreciated by one having ordinary skill in the art that various removable containers are often used in place of a complete integral trailer unit in the trucking industry today (for instance, the ubiquitous shipping containers used on container ships). According to the invention, cavities may either be permanently mounted on such containers (in which case they would also serve to reduce drag on a moving container ship, since if many containers had cavities according to the invention, a smoother boundary layer between stacks of containers and the atmosphere may be established), or may be removably amounted prior to transport by truck. Finally, in some embodiments the trailing edge of truck  1200  (or of its trailer or of a mounted container), instead of being planar, comprises a half-toroidal depression, which allows vortex  1221  to form, thus reducing turbulence at the trailing edge of truck  1200  as it travels through the atmosphere. 
       FIG. 13  is a diagram showing an exemplary modification of a conventional jet engine  1300  to reduce turbulence and drag and to improve fuel efficiency thereof, according to an embodiment of the invention. As is typical with jet engines in the art, gases flow from left to right through inlet  1301  of engine  1300  and exit at outlet  1320  (whereupon they expand according to profile  1331 ). According to the invention, drag resulting from this flow may be reduced by modifying the forward end of the cowling of engine  1300  with a plurality of vortex-inducing cavities  1302 ,  1303 . Those cavities  1303  on the exterior surface of engine  1300  reduce drag on the engine as it moves through the atmosphere, while cavities  1302  on the interior surface of the engine  1300  reduce drag that may slow down intake air, and thus improve engine efficiency. Similarly, in some jet engines known in the art, additional air intake is allowed at an inlet point  1310  forward of exhaust cowling  1311  in order to mix exhaust gases with cooler air, in order to reduce the temperature of gases exiting at point  1320  from engine  1300 . According to an embodiment, a plurality of vortex-inducing cavities  1312  is provided on the internal surface of exhaust cowling  1330  in order to facilitate establishment (via methods discussed above) of a smoothed boundary layer flow  1330  that acts to reduce drag as well as to reduce turbulence in exit gases by enabling a smoother boundary layer  1331  just aft of the engine as it passes through the atmosphere. 
       FIG. 14  is a diagram of a novel jet engine  1400  according to an embodiment of the invention. According to the embodiment, engine  1400  comprises a rigid exterior wall  1402  that is a solid of rotation whose cross-section is substantially an airfoil. A plurality of combustion cavities  1411 , similar in nature to cavities  28  in  FIG. 1 , is arranged on the interior surface of external wall  1402 . In a focal point of cavity  1411 , a fuel injection ring  1410  is placed, which is penetrated by numerous fuel outlet nozzles, holes, or injectors. Fuel injection ring  1410  may further comprise one or more igniters to ignite fuel entering cavity  1411 , or separate igniters may be provided at various locations along the inner surface of cavity  1411 . As fuel is injected into cavity  1411 , its combustion and expansion causes a vortex to emerge within cavity  1411 . Expanding combustion gases exit cavity  1411  in a substantially axial flow, thus creating a smooth boundary layer similar to those established according to previously discussed embodiments of the invention. Since expansion and acceleration of gases exiting to the right, in conjunction with the airfoil shape of external wall  1402 , will pull ambient air in through inlet aperture  1401  and accelerate these gases toward exit  1440 , thus accelerating engine  1400  (to the left) and any vehicle to which it is attached. Advantageously, in some embodiments cavities  1450  are provided on external surfaces of engine  1400  to reduce drag, similar to those described above with reference to  FIG. 13 . Various sensors  1420 ,  1421  may be placed at various points inside engine  1400  to assist in automatic control and measurement of engine operations. For example, sensors  1420  may be placed at a forward position within cavities  1411  in order to measure pressure, since pressure should be at a minimum when a proper vortex is established (because flow at sensor  1420  will be substantially parallel to the inner surface of cavity  1411 , and will have high velocity due to low drag, and thus will induce a low pressure). Using such an arrangement, for example, fuel pressure may be adjusted into a particular cavity on a continuous basis in order to maintain pressure at sensor  1420  at a minimum, and therefore to ensure proper vortex maintenance within cavity  1411 . Similarly, sensors  1421  at a point further aft in cavities  1411  could be used for monitoring pressures in order to assess engine operating conditions (and, of course, sensors  1421  could be used for the same purposes as sensors  1420 ). 
     An initial exhaust prototype for motorcycles with a straight guide profile demonstrated performance increases as described above. On another motorcycle, curvilinear guide surfaces produced a mellower and more pleasing sound, better attenuation, and improved engine performance. The inventor suspects that an effect analogous to that which is used advantageously in musical instruments occurs (specifically, trombones, trumpets, tubas, and other horns comprise curved geometries in their design. If more sound is consumed (attenuated) by an exhaust system according to the invention, it indicates that more compression waves have been employed as a motive force to accelerate gas, therefore better quieting may be used according to the invention as an indicator of better exhaust performance, and in some embodiments manual adjustments of tube  10  geometry (for instance, by changing spacing between guides) may be provided to allow users to “tune” their exhaust system for optimal sound and energetic performance. 
     Because it is well-known that toroidal vortices may become highly charged, such that their organizing structure becomes more resistance to decay, the application of a static or resonant electric field to cavities within various embodiments of the invention provides a novel control means for manipulation of fluid moving through various embodiments. For example, in the inventor&#39;s experiments it was noted that the presence of a resonant electric field applied to a tuned, metallic transducer in the vicinity of a cavity  28  imposed a field that caused evaporation of dew forming on an adjacent metal surface, without any other changing condition commonly associated with evaporation, such as increased heat or lowering of atmospheric relative humidity. The coupling of various embodiments with electric field controls may be used to control a variety of physical effects, especially by way of phase change when water vapor is present in a flow, in which the embodiment may be utilized as a novel evaporative system to absorb heat. Conversely, it has been observed that, when used with internal combustion engine exhaust, water vapor condenses into visible form from the outlet, when the guide design is slightly changed. Accordingly, in various embodiments of the invention, an output of a signal generator is connected to a high-voltage step-up coil or a voltage multiplier, the output voltage of which is connected to one or more guides  30 , each guide  30  being electrically isolated from the others and from an exterior body  604  of the embodiment by an electrical insulator. Each stage receives a signal that imposes control and stimulates intensification of vortex  28  within cavity  30 . 
     The foregoing description of preferred embodiments of the present invention has been provided for the purposes of illustration and description. It is not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many embodiments were chosen and described in order to best explain the principles of the invention and its practical application, thereby enabling others skilled in the art to understand the invention for various embodiments and with various modifications that are suited to the particular use contemplated. It is intended that the scope of the invention be defined by the claims and their equivalents. 
     The skilled person will be aware of a range of possible modifications of the various embodiments described above. Accordingly, the present invention is defined by the claims and their equivalents.