New! View global litigation for patent families

WO2005113981A1 - Dynamic fluid reactor - Google Patents

Dynamic fluid reactor

Info

Publication number
WO2005113981A1
WO2005113981A1 PCT/ES2005/000288 ES2005000288W WO2005113981A1 WO 2005113981 A1 WO2005113981 A1 WO 2005113981A1 ES 2005000288 W ES2005000288 W ES 2005000288W WO 2005113981 A1 WO2005113981 A1 WO 2005113981A1
Authority
WO
Grant status
Application
Patent type
Prior art keywords
fluid
figure
reactor
profile
wing
Prior art date
Application number
PCT/ES2005/000288
Other languages
Spanish (es)
French (fr)
Inventor
FORMOSO Antonio María SILVAR
Original Assignee
Silvar Formoso Antonio Maria
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS; PRODUCING MECHANICAL POWER; OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03GSPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G7/00Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
    • F03G7/10Alleged perpetua mobilia
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for

Abstract

The invention relates to a dynamic fluid reactor. The invention comprises a conduit (4, 22) which is traversed by a fluid flow that is driven by generating means and which contains a fixed wing with an aerodynamic profile (1, 1', 25, 25', 33, 33'), said fluid generating a lift force on the profile which causes the assembly to move. In order to improve the structure, the conduit comprises one or more cylinders (22) having directions of rotation which can neutralise the effect of a harmful generated force couple, said cylinders rotating at a suitable speed and containing a fluid (3) which adopts a cylindrical tubular shape owing to the centrifugal force. Moreover, the aerodynamic profile or inductor (25, 25', 33, 33') is fixed in relation to the support structure (28) and can move closer to the fluid ring (24), rubbing the surface thereof and entering same in order to utilise the suction and/or pressure force (depending on the surface geometry thereof), when the shape of the liquid vein deforms.

Description

REACTOR fluid dynamics OBJECT OF THE INVENTION

The present invention as expressed in the title of this specification, relates to a dynamic-fluid reactor which has significant advantageous features over known reactors, based on the principle of action and reaction.

The present invention is based on the theory of lift of a wing, ie, system action and reaction forces involved in a wing airfoil, as are those of a plane.

The airfoil generates a non-inertial reaction force, but gravity.

If the opposing force which causes the elevation of the wing, is gravity, what is the reaction where there is no gravity? . In this simple idea the reactor object of the invention is based.

If possible, use only the effective component produced by the wing profile to the passage of a fluid, or increase, may generate the lift force, or where there is only tensile gravity. The object of the invention is therefore a reactor as fluid dynamics system support, steering, pulling and pushing for motor vehicles or ships. For its movement is not dependent on soil, air, or gravity.

Knowing how the wing of an aircraft, that is able to transform energy generally horizontal communicating to the ship in vertical displacement of the horizontal fluid it is transformed by a vacuum induced on the upper face of the wing, a force lift and other brake and resistance.

The principle of action and reaction is a dilemma here, because the change of a horizontal force is not equivalent cross reaction. And this is what is used for self-propelling the aircraft. Brake force and resistance is traditionally overcome by increased thrust produced by the various motors and reactors have been designed.

The principle of the invention can summarized as follows: the fluid to move through a wing, instead of moving the wing by a fluid, thereby producing the same lift force; - move a large flow is easier and cheaper than the cost of energy consumed by traditional engines to produce the necessary thrust. It is also an object of the invention to use the force produced by the vacuum or pressure induced by the velocity of a fluid on a surface that constricts or expands the compartment or channel through which fluid flows or remains stationary and all enclosed or partially . Previously only the wings as 'passive' element of a structure to hold it in the air or lift on water or any other fluid were used. The present invention allows the use of traction generated and controllable in intensity, direction and half. It is also based on the effect of a fluid that moves at high speed under a narrowing or expansion similar to a wing profile element or inductor vacuum or pressure, fluid velocity. BACKGROUND OF THE INVENTION Currently aircraft (airplanes, helicopters, spaceships, etc.) and vehicles of all kinds reaction known.

To date only the wings as "passive" element of the structure is used as stated above.

DESCRIPTION OF THE INVENTION In general, the fluid dynamics, of the invention, the reactor comprises a conduit which is crossed by a fluid flow (air or another gas or liquid), this fluid-driven generating means any conventional type, with the particularity that within it is arranged transversely airfoil wing of the general type that have previously been defined as aircraft wing. The wing is anchored to the duct walls and the passage of fluid a lift force around wing causes raising of the assembly is created. Therefore, the fundamental principle is to make the fluid to move in a circular shape within two structures approximately tubular and concentric. There are at least two points on which to place a wing that produces the desired effect lift, as discussed below in connection with the drawings.

The airfoils traditionally conditional on the speed of the apparatus. You can change the profile when more lift at low speeds is required. As what is of interest for the reactor in question is the only support a maximum lift profile of the lower fluid velocity is searched, whereby the movement of the flowing total mass is optimized. Another interesting concept is that by putting the wing between two approximately cylindrical objects, have to apply other special profiles for this use.

It is further achieved that the fluid opposes little resistance, as the movement initiated once all the mass inertia a circular catch so consumption needed to maintain the movement of the mass of fluid will be minimal.

Another key point of the invention is that by using a cylindrical duct sealed can be used as the most suitable fluid, both gases and liquids as we stated above. Then, entering a denser fluid that air support would win. Because the material used should be as smooth and dense as possible, the airfoils will also be studied according to these parameters. It would be a very low viscosity fluid with a movement that entailed the least possible effort. For more dense fluids may be inert laminar flow profile too far, so could interest wings lower section to reduce the amount of fluid and thus reduce weight.

To move the fluid in a circular or rotary, can be used a mechanical option using blades, propellers, turbines, etc., or by using reactors induction or magnetic stirrers for movement of fluids that have no moving parts, whereby If the fluid velocity that can be achieved is sufficient, this would be the best choice for maintenance, structural weight and quality of flow. On the contrary, the use of propeller blades and the mechanical solution, generate many more turbulence, negative for the proper functioning of the wings. As fluid movement it generates a torque which would move the workpiece in the opposite direction, as discussed below action is balanced by placing two cylinders with opposed pairs. In another embodiment, multiple cylinders could be distributed in the positions of the sides of a polygon, or even in an arrangement or toroidal sections in this way.

Well, after the first trials, it has encountered the problem of generating a fluid flow at high speed and stable, or behave like a laminar flow.

The elements that make the fluid to move generate multitude of turbulence greatly disturb the flow.

To overcome this drawback and according to the present invention, based on the same theory of the laws of hydrodynamics and the Bernouilli theorem, the laminar flow in a circular motion in which to install the wing or inductor profile as we will call hereinafter , is achieved by rotating a hollow vertical shaft into which a quantity of fluid due to the centrifugal force against the walls to form a ring or tubular shape is fluid cylinder. Once operating speed is reached, preferably, and a perfect cylinder is formed, is installed in the central hollow portion, at least one fixed or orientable profile inductor push past him when approaching a surface. When it begins to push the fluid moving at high speed, the suction effect is achieved (or thrust as discussed below) profile similar to an airplane wing. Can install two or more cylinders or parallel and reverse turns drums, anchored to the same fixed support structure to balance the torque.

These cylinders can be placed as described in the main patent, in the position they occupy the sides of a regular polygon with three or more sides, and even if the technique allows, reaching a toroid. also it provides a radial distribution also compensates the pair.

According to the invention, interested fluid very high density and may also suits a high viscosity to avoid the effect "wake" that a fluid with low density yields and is inconvenient for the proper operation of the inductor profile, not it works well in turbulent fluids.

It has further been found that high density less effect on the fluid, ie the distance between the wing and the cylinder wall or may be less Tambor rotating this cause.

As the weight of the apparatus would be high with a fluid of high density, it is provided as follows: A profile that circulate perfectly parallel to the fluid but with many small mounds by generating face vacuum and small cavities or spherical or not traces in the pressure generating face (similar to the surface of a golf ball).

To optimize performance, the length of the drum is that which structurally may be built and considering that the bigger the diameter more traction, also interested in a large diameter, so must analyze what the optimum performance depending on the size, weight apparatus and traction obtained. Another application of the Bernoulli's theorem, would have the opposite effect: an increase in the channel section, the pressure can be increased; therefore it is a compressive force. Similar to what happens to the wings of a bird, a pressure rise running thrust under the wing, thus joining the resulting by placing another inductor pressure profile on the opposite side of the rotor forces occurs. When approaching the piston or screw displacement inductor compression profile, it is formed below a zone of influence of the compression induced effect. Small cavities provided for generating face pressure would be formed similarly to having a golf ball.

The profile or profiles inductors mounted in the duct or ducts fluid flow, can only be empty or only inductors pressure, or combine according interest.

In short, it is a system that allows the use of traction generated and controllable in intensity, direction and half. The fluid moves at high speed under a narrowing or expansion by the existence of the inductor profile vacuum or pressure due to the fluid velocity.

Another direct application of the invention, very interesting, is that as the induced vacuum or compression fluid, it cools or heating, respectively, as the circuit is closed, may tend to freeze or heat and indeed Presumably that the only reaction to traction occurs on the inductor profile is significant loss of energy in the inductor profile vacuum and heat in the inductor pressure profile, and thereby cooling or heating is achieved evident.

To balance the machine generating cold or heat, preferably it should be placed two or more wings or inducers profiles distributed radially as it is not getting displacements.

This cold or heat generated has the advantage that occurs in the machine without compressors and heat exchangers itself with the environment and probably cheaper than traditional systems, one very interesting for cooling or heating circuits of large factories, thermal solution, nuclear, buildings, appliances, etc., without the exchange of calories toxic, radioactive products arising, or the environment is disturbed by pouring into rivers warmer water that has been collected with the expense that this It poses to the environment and its already fragile balance, as usual.

To facilitate understanding of the characteristics of the invention and forming an integral part of this specification, some sheets of drawings are attached in which figures, in an illustrative and not limiting, represent the following:

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a system diagram of forces of action and reaction acting on a wing.

Figure 2 is a partial, schematic and perspective view of a conduit through which a fluid stream in closed circuit following ring in the upper and lower sections are respective wings supporting one direction. Figure 3 is a view similar to Figure 2, when the flow and the wings have a special profile adapted to the duct section.

Figure 4 is a view similar to Figures 2 and 3, when the flow travels through an asymmetric considering the location of the wing.

Figure 5 is a schematic view of the lines of laminar flow around the wing and the duct walls.

Figure 6 is a view similar to Figure 3 including in the duct system helices to cause fluid flow.

Figure 7 is a schematic sectional view of a dual cycle with vanes which generate the flow.

Figures 8a and 8b.- are respective schematic section views showing different positions of location blades that generate fluid flow along the annulus between two coaxial ducts primitive direction.

Figure 9 is a schematic sectional view of a reactor in which fluid motion is performed without moving parts through reactors induction or magnetic stirrers.

Figure 10 is a partial perspective view of a reactor of two cylinders connected with opposite pairs to maintain balance and the resultant have one direction.

Figures lia, 11b and 11c- are respective sectional views, front elevational and plan views of a tubular reactor annular passageway, schematically brackets including the inner cylinder from the outer cylinder and fixing the wings and location of motor propellers for large flow.

Figures 12a, 12b and 12c- are different schematic views of other various possible ways of keeping the balance between cylinders, distributed as polygon sides of a triangular, square, or infinite number of sides to compose a toroidal shape, respectively.

Figures 13a and 13b.- are respective schematic views of the wing of a toroidal reactor, for radial flow directed outwards and inwards. Figure 14a.- is a schematic perspective view of two sets of blades rotating in opposite directions in the case of toroidal reactor, to prevent rotation of the fluid tangentially.

Figure 14b.- is a schematic cross section of the toroidal reactor, including sets of blades of Figure 14a.

Figure 14C is a schematic perspective view of a wing of a toroidal reactor observing the direction of fluid surrounding the wing radially. Figure 15a.- is a schematic sectional view of a toroidal reactor including a flap direction causing turbulence in the laminar flow in the area to where appropriate.

Figure 15b.- shows schematically a plant distribution flap direction.

Figure 16 shows schematically three positions of a movable member positioned within the flow, for the rotation of the ship about its transverse axis.

Figures 17a, 17b and 17c- are respective schematic views, similar to Figure 11, 'including the rotational wings advantage fasteners or brackets wing and central cylinder.

Figure 18.- Is a schematic view, in four positions, one of the ways to laterally displace the ship in areas with gravity through flaps direction.

Figure 19.- Is a schematic view, in two positions a) and b), otherwise laterally displace the vessel in areas with gravity, through a retractable wing inside the flow zone. Figure 20.- Shows in two positions, respective sections of a toroidal reactor with asymmetrical section and different number of annular wings.

Figure 21.- Is a schematic and perspective view of a reactor apparatus according to an embodiment in which it is not necessary to close the fluid flow. the toroidal shape with a radial outward flow.

Figure 22.- Is similar to Figure 21 including annular schematic view wings located on the radial outward flow, and other wings inwards.

Figure 23.- Is a schematic perspective view, similar to Figure 22, with a production flow turbine, located at the top of the opening of the semi-toroidal shape of the reactor. Figure 24.- Is a schematic view in sectional elevation, of a toroidal reactor comprising in the center a cabin for the transport of people and goods, according to a possible application of the invention.

Figure 25.- Is a schematic view in sectional elevation, of another toroidal large reactor, in which the inner chamber of the torus forming annular toroidal where the annular flange is the inner wall of the chamber, could be used as cabin, cargo warehouse, or other uses. Figure 26.- Is a schematic view in elevation of a reactor with two rotating cylinders improvements contemplated by the invention.

Figure 27.- Is a diagrammatic plan view of a rotating cylinder with a pushing device of a vacuum profile inductor, which advances in the cylindrical flow reactor.

Figure 28.- Is a diagram of the zone of influence of vacuum induced fluid velocity profile on the corresponding inductor. Figure 29.- Is a plan view, similar to Figure 2 but including double system or pusher of two inductors profiles: one, the upper, with vacuum effect and another, lower, effective pressure. Figure 30.- Is a schematic view of the zone of influence of pressure induced by the fluid velocity profile on the corresponding inductor.

Figure 31.- Is similar to Figure 4 schematic for the smallest thickness of fluid used with embossed surfaces on both inductors profiles.

Figure 32.- Is an enlarged detail of an inductor vacuum profile, with its active surface provided with mounds for influencing depression induced by the minimum speed. Figure 33.- Is similar to Figure 7 detail, but with hollows or depressions generating overpressure.

Figure 34a.- is a plan view of a vacuum apparatus for inducing the fluid thus cools, losing energy and thus a considerable cooling. Figure 34b.- is a plan view of an apparatus for inducing the fluid pressure and warms, gaining energy and thus a considerable heating.

Figure 35.- Is a schematic view in sectional elevation, of a generator of heat or cold appliance, wherein the fluid itself to be cooled, heated, or 'climatizar general, is the one contained in the tank.

Figure 36.- Is similar to Figure 10 schematic view when the cold or heat generating device has fluid such high density that can be passed into a lighter fluid and that this is the exchanged or pumps to cool or heat the desired item, occupying the internal volume.

Figure 37.- Is a view similar to the previous, with the exchange fluid lower density, forming one coaxial layer being also displaced by the centrifugal force generated.

Figure 38.- Is a view similar to Figures 10 to 12, with the exchange fluid in a separate chamber on the inner wall of the cylinder.

DESCRIPTION OF AN EMBODIMENT OF THE INVENTION Referring to the numbering adopted in the figures, we can see how the fluid-dynamic reactor, that the invention proposes, based on the system of action and reaction in a wing airfoil, or aircraft wing, such as referenced with number 1 in figure 1. on its center of gravity forces act action:

A: Effective force produced by the wing profile 1 to the passage of fluid.

B: The vertical force component A in response to gravity.

C: is the horizontal component of the force A, as feed force. The reaction forces are: D: resistance produced by friction. E: Gravitational force on the apparatus. F: Force resulting from the D and E components which precludes effective action A. In this figure 1 are indicated the lines of laminar flow in the vicinity of the wing 1.

If used alone or increase the component A, it can generate the lift force, or where there is only tensile gravity. In Figure 2 we schematically represented how to move in a circular fluid within two tubular structures 2 and 3, being in this case but with a concentric oval section. 1 wings would be located in the upper and lower zones of the annular chamber 4 formed between two concentric tubular surfaces 2 and 3.

In Figure 3 we see illustrated schematically the cross section of another annular chamber 4 formed between two surfaces generally elliptical and concentric 2 'and 3'. As the circulating flow and nonlinear, may be interested other the inner cylinder section 3 'and outer 2', thereby achieving minimum friction. The wing design l 1 can vary considerably, not only as a cyclic flow adaptation interesting centrifugal forces, but also depending on the speed and type of fluid. The calculation of the profiles of both cylinders and containers wing, has long studied and tested for a new concept of fluid mechanics opens and there are many variants that can be included to optimize consumption and driving performance. The traditional study of wings was based on parallel horizontal laminar flows, but with this new design according to the invention, flows may vary curves to take for example the inertial force that can increase the lift on the upper surface of the wing. In Figure 4 we see other distribution cylinder 2 '' and 3 '' and a wing 1 '.

The distances between the wing profile 1 and the upper and lower walls of the cylinders, as deduced from observing figure 5, be suitable for achieving laminar approximately inert without considerable influence by friction on the walls 2 a flow and 3, as produced by the wing. It also may apply physical surface treatments (semioquedades such as golf balls or the like) and chemical

(Eg treatments tefIónicos) that minimize friction if necessary, or mechanical like the wings of laminar flow. In Figure 6 it is shown how to move the fluid in a circular direction, in a mechanical way by means of propellers 5.

In Figure 7 we see a dual cycle with blade 6 located in the common flow intermediate zone, circulating the fluid in the direction of the arrows. In Figures 8a and 8b represented we see other systems flow blades.

In Figure 9 shows a system of fluid movement performed using reactors induction or magnetic stirrers, that the absence of moving parts would be the best option to not disturb the flow, provided that the systems be as light as possible.

Placing two cylinders as shown in Figure 10, with opposed pairs, the balance is maintained and the resulting stress will only one direction, marked by the upper arrows. The directions of movement generated by the pairs of forces are indicated by arrows lower.

Referring to lia, 11b and 11c has been referenced with number 7, the support fixing the central cylinder 3 to 2 and the outer wing or wings 1 where appropriate. We also see the layout of the driving propellers 5 for high flow.

As in connection with Figure 10 we saw a balancing system torque by two 'parallel cylinders, in Figures 12a and 12b other possible to solve this problem forms shown, arranging the cylinder forming a polygon three and four sides respectively. The number of sides can be increased and reach the conception of a toroidal arrangement as shown in Figure 12c, which allows to solve the problem of fluid equivalently to a turbine and is easier to produce an induced rotation.

To date, the concepts of lift of the wings of the aircraft it was thought that laminar flow anterior and posterior should remain unchanged and this could be something like this with current processes. According to the invention and according to a toroidal resolution of the reactor in question, the laminar flow upper and lower must be the same before and after passing through the wing, but not necessarily equal to each other, which allows a circular wing, with a profile with radial and edge ribbing attack inwardly or outwardly of this annular shape. In Figures 13a and 13b this wing section referenced with number 8 and 8 'respectively for radial flow outward or toward the center is observed.

Once conceived this element annular flange 8 or 8 •, you have to pass the fluid to act and lift and movement of the reactor occurs. They can be used as in the previous case, mechanical means or inductive means. Mechanical means using similar to those of any turbine, rotating the set for a flow outward or inward, depending where the wing and the direction is selected to be placed radial fins, which will cause the annular wing start acting on its upper face producing suction necessary to generate an antigravity force or acceleration in the direction of the supporting part. In Figures 14a, 14b and 14c, see how the radially directed flow. double dextrorotatory and levorotatory turbine blades is used, inside or outside of the toroidal form. The reference 9 designates Figure 14a these turbines. For be situated towards the nearest wall to the center of the toroidal form, they are referenced 9 'and if they are in the outer area and therefore have a larger diameter, which are 9' •.

Referring to Figures 15a and 15b, we see how to move the reactor. Accelerating or decelerating the reactor this movement is obtained in that the upper face of the piece (rise faster or slower) and if there is a nearby gravitational field can "fall" at a controlled rate. To change the direction of the assembly is basically apply three systems: one would accelerate or decelerate a flow area to raise or lower respectively and thus change the direction; another by means of flaps 10 which produce turbulence in the laminar flow 11 in the area where you want to run the reactor, thereby pulling the rest of the assembly may rotate the piece in that direction. Once the flap 10 would collect all the wing 8 to "throw" homogeneously in that direction. Mainly they propose four flaps as shown in Figure 15b, but may be from one or more, depending on the speed of rotation desired.

If under the influence of a gravitational field, this effect would cause a lateral displacement. In Figure 15a schematic section of a toroidal reactor is observed, the toroidal outer wall is referenced with number 12 and internal with number 13, the flow circulating in the direction indicated by arrows. The third system is to include a section alar 18 retracted within the flow area, as shown in Figure 19. With the wing 18 positioned vertically interfering with the flow, will pull the wing side. Wing displacement can be obtained by a mechanical or hydraulic system.

In Figure 16 schematically we see how the ship to rotate about its transverse axis. To this end a piece 14 is positioned within the flow, similar to with reference number 7 in Figure 11 (lia, 11b and 11c). This part 14 is spindle-shaped and is formed by a fixed central portion 15 and two mobile 16 and 17 to their ends. Depending on how moving parts to rotate the rotation force in either direction, as shown in positions b) and c) of this figure 16. At the top, the rotational wing 14 will have the leading edge in the same direction as the leading edge of the main wing 1 and the lower part is in the reverse position.

Making special reference now to Figure 18, we can see how to move laterally ship through flaps direction 10, by rotating one of them the ship will fall slightly from that side, position b). If we combine with a small acceleration of the apparatus, position c), they become the flaps 10 to place and the unit will move inclined toward that side, as shown in position d).

In Figure 20 is shown schematically in two positions a) and b), the section of a toroidal reactor walls 12 (outer) and 13 (inside), in which are placed two or more annular wings 8 or 8 ', the which they can be placed in parallel or one after the other so that the maximum yield is obtained according to the fluid and / or the speed thereof and / or the profile shape.

The toroidal section of the outer surface and the interior of the reactor will have a certain profile depending on the introduced fluid and for the greatest overall performance.

For the toroidal reactor, which section may be the same as that shown in Figure 14b, as is necessary for the fluid to move only in a radial direction and not tangential, can prevent rotation of the fluid in this direction by putting two sets of blades Similar to the referenced 9 in figure 14a, one turning right and one to the left to stabilize the assembly. Making special reference now to Figures 21, 22 and 23, we see different system applications.

It is possible to adapt the operating principle of the invention, an apparatus in an atmosphere or fluid without closing the flow in the annular toroidal chamber. It could work in a similar way to that of a helicopter but safe way, because it could be located very close to cables or buildings without danger of getting stoned them, and even sticking completely. Also this device would be less affected by wind gusts or turbulence, moving less air since sustaining the support wings and not the turbine. Figure 21 shows an apparatus 19 with annular radial wings 8 outward flow and a turbine 9 high flow and double offset rotation shown. In Figure 22 the option of annular wings 8 and 8 'is shown with radial flow outwardly and inwardly and channeling the air towards the axial zone outflow.

Another possibility of operation would be to place the turbine at the top of the axial recess would toroidal shape, which is simpler mechanically generate the necessary flow as deduced from observing figure 23.

As for the possible applications are innumerable, assuming that the reactor has run for any of the systems described. It could be placed in the axial void of the toroidal reactor antigravity anatmosférico, such as referenced in general with number 20 in Figure 24, a cabin 21 for transporting people and goods.

You could get in and out of the atmosphere at the "speed you were interested without the problems currently arising from entry into freefall.

It could move at the speed you want and accelerate in space with minimum consumption. In large toroids (see Figure 25) the inner torus chamber 13 could be used as cabin, cargo warehouse, and even fuel engines.

Depending on the needs you could apply one or more toroids or cylindrical sections weighty ships to land and take off at points where gravity is higher or to give greater acceleration and speed of movement.

Now making special reference to figures 26 to 38, we can see the improvements contemplated in the second part of the invention, consisting in making the flow of fluid circulating in the duct where it is transversely and fixed the wing airfoil, or inducer of vacuum or pressure profile, on which the lift force or thrust is applied created; is formed by rotating a circular cylinder 22 driven by the corresponding motor 23, within which is located a fluid 24 that by rotation adopts cylindrical shape forming a layer of constant thickness and which rotates at high speed.

Wing or profile 25 inducer emptied as shown in Figure 2 and which in this case has a symmetrical profile but may have other suitable, is in a retracted principle not pose obstacle to fluid movement until the speed is reached regime.

At this point and being assisted inductor profile by a hydraulic cylinder or mechanical element, or generally a mechanism of adjustable approach such as referenced 26 in this embodiment, it is made to radially advance to establish contact and partial invade or fully vein moving liquid, as shown in figure 27. the arrow 27 shows the direction of rotation of the cylinder 22 and therefore the fluid 24. for reasons of balance and neutralize the torque, the reactor has two cylinders 22 which rotate in opposite directions, fixed to the supporting structure 28 as shown in figure 26. in figure 28 the lines of force 29 caused by the vacuum induced fluid velocity 24 in the direction marked by observed the arrows 30. the vacuum zone of influence is referenced with the number 31. the movement of the assembly is effected in the direction of arrows 32.

This particular reference to Figure 29 shows how there is also the profile 25 inductor vacuum, another profile 33 situated diametrically opposite the end of another cylinder 26 radially located on the same inner shaft which was anchored the cylinder 26 discussed above . This inward and axial cylinder or drum axis is fixed or angularly movable for the inductor profile 25 or 33 to change orientation and therefore the device change its direction and is referenced with number 34.

The profile 33 is inductor pressure instead of vacuum because, as seen more clearly in Figure 30, has a central depression which disturbs the liquid vein in the direction of increasing section thereof and therefore a buffer is formed 31 'of the forces generated and whose resultant is radial and the same direction (or substantially the same) forces 29 generated by the profile 25, referenced in this case with 29' because they go into the profile 33 and thus add up. This profile 33 is inductor pressure or compressive force on the cylinder or piston 26 accordingly.

In Figures 31 to 33 the overall arrangement of a cylinder 22 of the reactor, similar to Figure 29, in which is used a fluid 24 preferetemente high density with little wall thickness and profiles inductors vacuum is observed and pressure, respectively referenced 25 and 33 • ', which have their active surface embossed to increase its action on the fluid. Embossing is defined by piles 35 or not equidistant and symmetrical. or asymmetric, forming a mold surface as a golf ball or the like in the profile 25 'inductor vacuum (Fig 32); and alveoli or depressions 36, symmetrical or not profile 33 'thus has a surface such as a golf ball or the like, inducing overpressure (Figure 33). It is also envisaged that the fluid is also dense, viscous to avoid wake turbulence could be formed, as we said above.

The areas of influence of pressure or vacuum induced speed are minimal, are being referenced with 37 for each mound 35 and 37 'for each cell 36.

These resultant forces are radial to the drum 22 and that from a certain degree of inclination with respect to the path, it may no longer be interested, they generate high friction and its contribution is too inclined with respect to the path. We will have to find a balance between capacity and tractive power consumption as by friction produced by this type 'of inductor easy profile is not interested in having too much contact surface.

Referring now to Figures 34 to 38 we can see the application of the invention to the construction of a cold generating apparatus (Figure 34a), or heat

(Figure 34b) as the inductor profile is vacuum pressure 25 or 33.

Advantageously they exist in the drum 22, two profiles

25 or 33 inducers of vacuum or pressure respectively emerging diametraímente opposite and fixed axis 34, whose effects are counteracted (see Figures 34a and 34b). They could be more than two, being uniformly distributed angularly, for three or more radios. It may also work with a single profile, thereby avoiding movement to direct the resultant force to a dead zone apparatus, such as the floor.

Cold or heat generated in the machine without compressor or exchangers as said above itself, can be applied in various ways, according to Figures 35 to 38:

In Figure 35, we see a pumping system to remove the fluid 24 itself by the outlet conduit 38 at the same speed as the replenished by the inlet duct 39, thus maintaining the inductor profile 25, or 33, active .

In Figures 36 and 37 another way to keep the temperature constant is shown, to have another light fluid (air for example) referenced with 24 'that invades the inside (Figure 36) entering the duct 40 and leaving by 41, or However, employing a fluid 24 •• exchange (such as water) that rotation is also distributed as another coaxial layer to the previous one and will not mix the different density (fluid 24 is advantageously much denser than 24 1 '). Exchange fluid enters through conduit 39 and out the referenced 38, having the end of these ducts 38 and 39 bent flush with this fluid layer 24 "(see Figure 37).

The third way aforesaid to achieve the same effect, regardless of the density of the fluid used to heat the fluid 24, it is foreseen in this case shown in Figure 34, a casing 42 to form a chamber 43 of exchange occupied by the fluid gauge of excess calories or kilocalories in this job as climate the element to which it is applied. This exchanger circuit is that keeps the fluid tractor without thermal changes, may be located in the walls of the drum 22 internally or externally, in the inductor profile itself 25 or 25 ', or in the space where the profile, without touching the not disturb fluid.

Claims

We claim:
1. REACTOR fluid dynamics / characterized by including a support structure (7) of at least one conduit (4,22) through which a fluid stream - driven generating means (5,6) circulating in annular direction, in which within the conduit (4,22) is arranged transversely at least one airfoil (1,1 ', 25,25', 33,33 ') selected from: fixed profiles, profiles angularly adjustable relative to the support structure (7) and combinations of such profiles being selected said at least one profile including: vacuum inductors profiles (25,25 '), inductors pressure profiles (33,33') and combinations thereof, depending on its own section respectively, an elevation or a depression, which disturbs the liquid vein to decrease or increase the section thereof, thereby creating a lift force which causes a tendency to move the assembly.
2. REACTOR fluid dynamics according to claim 1, wherein the fluid conduit travels in closed circuit, forming an annular chamber (4) between the two closed tubular portions (2, 3) at both ends, said tubular portions being selected closed between: tubular portions concentric closed and closed tubular portions nonconcentric following the fluid one annular path, I being provided as aerofoil at least one wing support (1, 1 ') distributed in sense ring and oriented in correspondence with the rotational movement of fluid. 3. REACTOR fluid dynamics according to claim 2, wherein the airfoil (1) is linked to the optimal lift with lower speed of fluid flowing between the tubular conduits (2,
3) generally cylindrical.
4. REACTOR fluid dynamics, according to previous claims, characterized in that the distance between the airfoil (1) and the walls (2, 3) of the duct, is ideal not to disturb laminar to walls flow (2 , 3) thereof.
5. REACTOR fluid dynamics, according to previous claims, characterized in that the means (5, 6, 9) producing the fluid stream are determined by elements selected from: blades, propellers, turbines and the like.
6. REACTOR fluid dynamics, according to claims 1 to 4, wherein the means producing the fluid stream are determined by induction reactors.
7. REACTOR fluid dynamics, according to claims 1 to 6, characterized in that balancing means are provided torque, determined by two parallel modules secured together and opposed pairs, whose forces resulting lift of the wings (1) respective have the same meaning.
8. REACTOR fluid dynamics, according to claims 1 to 6, characterized in that balancing means are provided torque, determined by the arrangement of several modules according to the sides of a polygonal structure of three or more sides.
9. REACTOR fluid dynamics, according to claims 1 to 6, characterized in that the conduit for the fluid path is defined between two generally concentric toroidal shapes (12, 13), the supporting wing (8, 8 ' ) type annulus with aerofoil section and with dextrorotatory or levorotatory laminar depending on the orientation of the wing and having a radial direction the flow stream.
10. REACTOR fluid dynamics according to claim 1, wherein the linear displacement of the reactor assembly, is adjusted by varying the rotor acceleration that varies the lift force resulting from the wing.
11. REACTOR fluid dynamics according to claim 1, wherein the change of direction is achieved by steering flaps (10) inside or outside the wing which produce turbulence in the laminar flow in the desired direction.
12.- REACTOR fluid dynamics according to claim 1, characterized in that the lateral displacement of the vessel is made to include a section wing (18) retracted within said flow vertically mounted thereto for pulling the wing ( 18) is lateral.
13.- REACTOR fluid dynamics, according to claim 9, characterized in that two rotors (9) sets of blades which rotate in opposite directions to stabilize the assembly and the air flow have only radial direction are arranged.
14.- REACTOR fluid dynamics, according to claim 1, wherein the rotation of the ship about its transverse axis is achieved by placing within the flow, a part (14) as formed by a fixed spindle central portion (15) or inert and two movable (16, 17) at their ends being diverted to either side causes the change of direction.
15.- REACTOR fluid dynamics, according to claim 14, wherein said part (14) spindle-shaped, or rotational wing, has at the top, its leading edge in the same direction as the main wing (1, 8), and at the bottom reverse arrangement.
16.- REACTOR fluid dynamics, according to claims 1 to 9, wherein the cross section of the toroidal or annular chamber duct is asymmetric so that the wing / s (8) of the top take a divergent view of the lower / s (8 ') to the flotation or lift components are parallel and to join action.
17.- REACTOR fluid dynamics, according to previous claims, characterized in that the duct or ducts traveled by the fluid bearing walls secured to a cab structure (21) for transport of persons and / or goods.
18.- REACTOR fluid dynamics, according to claims 1 to 16, wherein the inner toroid chamber (13) defines a compartment and cabin, cargo warehouse, engine room, fuel tank, etc.
19.- REACTOR fluid dynamics according to claim 1, wherein said duct, or several of them arranged in parallel, as the sides of a regular polygon, or star located radially, and senses of rotation suitable for neutralizing the effect of a pair of harmful forces generated, is defined by a cylinder (22) driven by a motor rotating at high speed and containing within a certain amount of a fluid (24) adopts tubular cylindrical shape by centrifugal force during rotation, it being provided that the profile or profiles vacuum inductors (25,25 ') and / or inductors profile or pressure profiles (33, 33'), fixed or angularly adjustable relative to the support structure (28) can approach the ring f uid (24), brushing against the surface and move within it to cause the suction force and / or pressure.
20.- REACTOR fluid dynamics, according to claim 19, wherein the fluid (24) is high density.
21.- REACTOR fluid dynamics, according to claim 20, wherein the fluid (24) is also high viscosity.
22.- REACTOR fluid dynamics, according to claim 19, wherein the vacuum profile inductor (25 '), or pressure profile inductor (33'), runs perfectly parallel to the generatrix of the fluid ring (24) and has many small elevations or mounds (35) distributed over the face of vacuum generator and / or small cavities (36) in the face pressure.
23.- REACTOR fluid dynamics, according to claim 19, wherein the vacuum or pressure inductor (25, 25 ', 33, 33') profile is linked to a pusher (26) to initiate and maintain the friction profile inductor (25, 25 ', 33, 33') and withstand pulling assembly.
24.- REACTOR fluid dynamics, according to claim 23, wherein the pusher (26) is arranged as two or more radios, having their active ends connected respectively to a profile or profiles vacuum inductors (25, 25 ') and a profile or profiles pressure inductors (33, 33 '), adding the resulting forces on the assembly structure.
25.- REACTOR fluid dynamics, according to claims 19 to 24, wherein the surface profile inductor (25 ', 33') is embossed, defined by a surface with small mounds (35) for the vacuum effect and depressions (36) or alveoli footprint similar to the effect of pressure.
26.- REACTOR fluid dynamics, according to claim 19, wherein the vacuum circuit is closed, cools the fluid tending to freeze, and are located one, two, or more profiles vacuum inductors (25, 25 ') points regularly distributed to establish the balance of power.
27.- REACTOR fluid dynamics, according to claim 19, wherein the pressure-generating circuit is closed, the fluid warms up considerably and are located one, two, or more inductors pressure profiles (33, 33 ') at points distributed regularly to establish the balance of power.
28.- REACTOR fluid dynamics, according to claims
26 and 27, characterized in that there is a pumping system which removes the fluid (24) at the same rate that resets to maintain the active profile inductor (25, 25 ', 33, 33').
29.- REACTOR fluid dynamics, according to claims
26 and 27, wherein the fluid (24) is of high density and can be passed a lighter fluid (24 ', 24' ') into the cylinder and is the latter fluid that is exchanged or pumped to cool or heat the element in question.
30. -REACTOR fluid dynamics, according to claims 26 and 27, characterized in that a circuit maintainer exchanger fluid (24) without thermal changes and be positioned exchange fluid (43) in the drum walls (22), internally or externally; in the inductor profile (25, 25 '); or even within the area where said profile is, without touching the fluid (24) to not disturb.
PCT/ES2005/000288 2004-05-21 2005-05-20 Dynamic fluid reactor WO2005113981A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
ESP200401221 2004-05-21
ES200401221 2004-05-21
ES200501218 2005-05-19
ESP200501218 2005-05-19

Publications (1)

Publication Number Publication Date
WO2005113981A1 true true WO2005113981A1 (en) 2005-12-01

Family

ID=35428446

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/ES2005/000288 WO2005113981A1 (en) 2004-05-21 2005-05-20 Dynamic fluid reactor

Country Status (1)

Country Link
WO (1) WO2005113981A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012091533A3 (en) * 2010-12-27 2013-02-28 Alibi Akhmejanov The device to generate lift force (options)
US20160009376A1 (en) * 2012-12-09 2016-01-14 Bogdan Tudor Bucheru Semi-open Fluid Jet VTOL Aircraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58214681A (en) * 1982-06-07 1983-12-13 Yukutada Naito Reaction-less propelling engine
US4953397A (en) * 1989-07-25 1990-09-04 The Boeing Company Continuous flow hypersonic centrifugal wind tunnel
WO1994020741A1 (en) * 1993-03-02 1994-09-15 Jae Hwan Kim A system for generating power, propulsive force and lift by use of fluid
ES2154603A1 (en) * 1999-09-02 2001-04-01 Blazquez Cayetano Vazquez Vehicle suitable for travel and transportation.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58214681A (en) * 1982-06-07 1983-12-13 Yukutada Naito Reaction-less propelling engine
US4953397A (en) * 1989-07-25 1990-09-04 The Boeing Company Continuous flow hypersonic centrifugal wind tunnel
WO1994020741A1 (en) * 1993-03-02 1994-09-15 Jae Hwan Kim A system for generating power, propulsive force and lift by use of fluid
ES2154603A1 (en) * 1999-09-02 2001-04-01 Blazquez Cayetano Vazquez Vehicle suitable for travel and transportation.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012091533A3 (en) * 2010-12-27 2013-02-28 Alibi Akhmejanov The device to generate lift force (options)
US20160009376A1 (en) * 2012-12-09 2016-01-14 Bogdan Tudor Bucheru Semi-open Fluid Jet VTOL Aircraft
US9517840B2 (en) * 2012-12-09 2016-12-13 Bogdan Tudor Bucheru Semi-open fluid jet VTOL aircraft
US9714091B1 (en) * 2012-12-09 2017-07-25 Bogdan Tudor Bucheru Semi-open fluid jet VTOL aircraft

Similar Documents

Publication Publication Date Title
US3416729A (en) Liquid aerator
US3083935A (en) Convertible aircraft
US6800955B2 (en) Fluid-powered energy conversion device
US4403755A (en) Method and apparatus for use in harnessing solar energy to provide initial acceleration and propulsion of devices
US4036916A (en) Wind driven electric power generator
US6270309B1 (en) Low drag ducted Ram air turbine generator and cooling system
US20070034738A1 (en) Aerodynamically stable, vtol aircraft
US6616094B2 (en) Lifting platform
US4606697A (en) Wind turbine generator
US4504192A (en) Jet spoiler arrangement for wind turbine
US3100454A (en) High speed ground transportation system
US5873545A (en) Combined flying machine
US6688842B2 (en) Vertical axis wind engine
US6464459B2 (en) Lifting platform with energy recovery
Smith Wake ingestion propulsion benefit
US20080150292A1 (en) Shrouded wind turbine system with yaw control
US3632065A (en) Rotary wing aircraft
US20090084907A1 (en) Ground Effect Vanes Arrangement
US6710469B2 (en) Fluid-powered energy conversion device
US5595358A (en) Multipurpose airborne vehicle
US20080061559A1 (en) Use of Air Internal Energy and Devices
US7112034B2 (en) Wind turbine assembly
US3987987A (en) Self-erecting windmill
US20080265583A1 (en) Water Turbine with Bi-Symmetric Airfoil
US5895011A (en) Turbine airfoil lifting device

Legal Events

Date Code Title Description
AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KM KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NG NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SM SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

121 Ep: the epo has been informed by wipo that ep was designated in this application
DPEN Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase in:

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

122 Ep: pct application non-entry in european phase