WO2005113981A1 - Reacteur fluido-dynamique - Google Patents
Reacteur fluido-dynamique Download PDFInfo
- 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
- WIPO (PCT)
- Prior art keywords
- fluid
- profile
- dynamic reactor
- wing
- reactor
- Prior art date
Links
- 239000012530 fluid Substances 0.000 title claims abstract description 120
- 230000000694 effects Effects 0.000 claims abstract description 15
- 239000007788 liquid Substances 0.000 claims abstract description 6
- 210000003462 vein Anatomy 0.000 claims abstract description 4
- 230000001939 inductive effect Effects 0.000 claims description 16
- 230000009471 action Effects 0.000 claims description 10
- 230000006698 induction Effects 0.000 claims description 8
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 5
- 230000001133 acceleration Effects 0.000 claims description 4
- NOQGZXFMHARMLW-UHFFFAOYSA-N Daminozide Chemical compound CN(C)NC(=O)CCC(O)=O NOQGZXFMHARMLW-UHFFFAOYSA-N 0.000 claims description 2
- 230000004075 alteration Effects 0.000 claims description 2
- 238000013459 approach Methods 0.000 claims description 2
- 238000005086 pumping Methods 0.000 claims description 2
- 210000000481 breast Anatomy 0.000 claims 1
- 238000005188 flotation Methods 0.000 claims 1
- 239000002828 fuel tank Substances 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 description 12
- 230000005484 gravity Effects 0.000 description 11
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000001965 increasing effect Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000000411 inducer Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000036961 partial effect Effects 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000004049 embossing Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000003472 neutralizing effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 210000003456 pulmonary alveoli Anatomy 0.000 description 1
- 230000002285 radioactive effect Effects 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
- 230000001131 transforming effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
- F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
- F03G7/10—Alleged perpetua mobilia
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
Definitions
- the present invention refers to a fluid-dynamic reactor which has notable advantageous characteristics over known reactors, based on the principle of action and reaction.
- the present invention is based on the theory of support of a wing, that is, the system of action and reaction of the forces involved in a wing with an aerodynamic profile, as they are those of an airplane.
- the profile of the wing generates a reaction force not inertial, but gravitational.
- the reactor object of the invention is based on this simple idea.
- the object of the invention is therefore a fluid-dynamic reactor as a lift, steering, traction and thrust system for vehicles or automobile ships. For its movement does not depend on soil, atmosphere, or gravity.
- the principle of the invention can be synthesized in the following: that the fluid moves through a wing, instead of moving the wing through a fluid, thus achieving the same bearing force; - Moving a large flow is easier and cheaper than the energy cost consumed by traditional engines to produce the necessary thrust. It is also the 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 narrows or expands the compartment or channel through which the fluid circulates or remains static and completely or partially enclosed . Previously, only the wings were used as a "passive" element of a structure to hold it in the air or lift it over water or any other fluid. The present invention allows the use of the traction generated and controllable in intensity, direction and medium.
- the fluid-dynamic reactor object of the invention, includes a conduit that is traveled by a fluid stream (air or other gas, or even liquid), this fluid being driven by generating means of any conventional type, with the particularity that an aerodynamic profile wing of the general type is arranged transversely which we have previously defined as airplane wing.
- the wing is anchored to the walls of the duct and the flow of the fluid creates a lifting force around the wing that causes the assembly to rise. Therefore, the fundamental principle is to make the fluid move in a circular manner within two structures, approximately tubular and concentric. There are at least two points at which to place a wing that produces the desired lift effect, as we will see later in relation to the drawings.
- the wing profiles are traditionally subject to the speed of the apparatus.
- the profile can be modified when more support is needed at low speeds.
- a maximum lift profile will be sought at the slowest speed of the fluid, which will optimize the movement of the total flowing mass.
- Another interesting concept is that when putting the wing between two approximately cylindrical objects, another type of special profiles will have to be applied for this use.
- Another of the fundamental points of the invention is that when using a sealed cylindrical duct, the most suitable fluid can be used, both in gases and in liquids as indicated above. Then, introducing a denser fluid that the air would gain in support. Because the matter used should be as fluid and dense as possible, the wing profiles will also have to be studied according to these parameters. It would be a fluid with a very low viscosity so that its movement involved the least possible effort. For denser fluids it is possible that the inert laminar flow is too far from the profile, so wings of smaller section may be of interest to reduce the amount of fluid and therefore reduce weight.
- a mechanical option can be used by means of blades, propellers, turbines, etc., or, using induction reactors or magnetic stirrers for fluid movement that do not have moving parts, so that If the speed of the fluid that can be achieved is sufficient, this would be the best option for maintenance, structural weight and flow quality.
- the use of propellers and blades of the mechanical solution generate much more turbulence, negative for the proper functioning of the wings.
- the action is balanced by placing two cylinders with opposite pairs.
- the elements that make the fluid move generate a multitude of turbulences that greatly disturb the flow.
- the flow laminar in circular motion in which to install the wing or inductor profile as we will call it in the following it is achieved by rotating a hollow cylinder of vertical axis in whose interior there is an amount of fluid that due to the centrifugal force is applied against the walls forming a ring or tubular fluid form.
- a perfect cylinder is formed, it is installed in the central hollow part, at least a fixed or adjustable profile, inducing the thrust when approaching it superficially.
- cylinders can be placed as described in the main patent, in the position occupied by the sides of a regular polygon with three or more sides, and even if the technique allows it, to reach a toroid.
- a radial distribution is also provided that also compensates for the torque.
- a very high density fluid is of interest and it is also possible that a high viscosity is also convenient to avoid the "wake" effect that a low density fluid produces and that is inconvenient for the correct operation of the inductor profile, which does not It works well in turbulent fluids.
- the high density influences the fluid to a lesser extent, that is, the distance between the wing and the wall of the cylinder or drum can be smaller for this reason.
- the length of the drums will be the one that can be structurally constructed and taking into account that the more diameter the more traction, a large diameter is also of interest, so it will be necessary to analyze the optimum performance according to the size, weight of the apparatus and traction obtained.
- Another application of Bernouilli's same theorem would be the opposite effect: an increase in the section in the canal can increase the pressure; Therefore it is a compression force. Similar to what happens to the wings of a bird, there is an increase in pressure that executes a thrust under the wing, thus adding the resulting forces by placing another pressure inducing profile, on the opposite side of the rotor. As the piston or displacement screw of the compression inductor profile approaches, an area of influence of the induced compression effect is formed below.
- the small holes provided for the pressure generating face would be formed in a manner similar to that of a golf ball.
- the profile or inductor profiles mounted in the fluid circulation duct or ducts can be only vacuum inductors or pressure only, or combine them according to interest.
- Another direct application of the invention which is extremely interesting, is that as it induces vacuum or compression to the fluid, it is cooled or heated respectively, and since the circuit is closed, it is possible that it tends to freezing or heating and in fact it is to be assumed that the only tensile reaction that occurs on the inductor profile is a considerable loss of energy in the vacuum induction profile and heat in the pressure inductor profile, and therefore achieves obvious cooling or heating.
- two or more radially distributed wings or inductor profiles should preferably be located, since it is not about getting displacements.
- This cold or heat generated has the advantage that it is produced in the machine itself without compressors or exchangers with the medium and is probably cheaper than traditional systems, being a very interesting solution for cooling or heating circuits of large factories, thermal plants, nuclear, buildings, devices, etc., without the exchange of calories emit toxic, radioactive products, or the environment is disturbed by pouring into the rivers the hottest water that has been collected, to the detriment that this It is for the environment and its already fragile balance, as usual.
- Figure 2. It is a partial view, schematic and in perspective, of a conduit traveled by a flow of fluid in a closed circuit following an annular direction, in whose upper and lower sections there are paths of support.
- Figure 3. It is a view similar to Figure 2, when the flow and the wings have a special profile adapted to the section of the duct.
- Figure 4. It is a view similar to Figures 2 and 3, when the flow runs through an asymmetric duct taking into account the location of the wing.
- Figure 5. It is a schematic view of the laminar flow lines around the wing and the walls of the duct.
- Figure 6 It is a view similar to Figure 3 including in the duct a system of propellers to cause fluid flow.
- Figure 7. It is a schematic sectional view of a double cycle system with blades that generate the flow.
- FIGS 8a and 8b are respective schematic views in section, showing different positions of the blades that generate the flow of fluid following an annular direction between two coaxial primitive ducts.
- Figure 9. It is a schematic view of the section of a reactor in which the movement of the fluid is carried out without moving parts, by means of induction reactors or magnetic stirrers.
- Figure 10. It is a partial perspective view of a two-cylinder reactor joined and with opposite pairs to maintain balance and that the resulting one has only one direction.
- Figures lia, 11b and 11c- are respective sectional views, front elevation and plan, of an annular tubular conduit of the reactor, schematically including the fixing brackets of the inner cylinder with respect to the outer cylinder, as well as the fixing of the wings and the location of drive propellers for high flow.
- Figures 12a, 12b and 12c- They are different schematic views of many other possible ways of maintaining the balance between cylinders, distributed as sides of a triangular, quadrangular, or infinite number of sides to compose a toroidal shape, respectively.
- Figures 13a and 13b. They are respective schematic views of the wing of a toroidal reactor, for radial flow directed towards the exterior and towards the interior.
- Figure 14a.- It is a schematic perspective view of two sets of blades rotating in opposite directions in the case of the toroidal reactor, to prevent the rotation of the fluid in a tangential direction.
- Figure 14b It is a schematic cross-section of the toroidal reactor, including the sets of blades of Figure 14a.
- Figure 14c It is a schematic perspective view of a wing of a toroidal reactor observing the direction of the fluid that surrounds the wing radially.
- Figure 15a.- It is a schematic view of the section of a toroidal reactor including a direction flap that produces turbulence in the laminar flow in the area where it corresponds.
- Figure 15b Schematically shows a plan distribution of the address flaps.
- Figure 16. Schematically shows three positions of a moving part placed inside the flow, to achieve the rotation of the ship on its transverse axis.
- Figures 17a, 17b and 17c are respective schematic views, similar to those of Figure 11, 'including the rotational wings taking advantage of the fixing elements or supports of the wing and central cylinder.
- Figure 18. It is a schematic view, in four positions, of one of the ways to move the ship laterally in areas with gravity, by means of steering flaps.
- Figure 19 It is a schematic view, in two positions a) and b), of another way to move the ship laterally in areas with gravity, by means of a retractable wing within the flow zone.
- Figure 20. Shows in two positions, respective sections of a toroidal reactor with asymmetric section and different number of annular wings.
- Figure 21 It is a schematic and perspective view of a reactor apparatus, according to an embodiment variant in which it is not necessary to close the fluid flow in. the toroidal shape, with a radial outward flow.
- Figure 22 It is a schematic view similar to Figure 21 including annular wings located in the radial flow outwards, and other wings inwards.
- Figure 23. It is a schematic and perspective view, similar to Figure 22, with a flow-producing turbine, located at the top of the opening of the semitoroidal shape of the reactor.
- Figure 24. It is a schematic sectional elevation view of a toroidal reactor that includes in the center a cabin for transporting people and goods, according to a possible application of the invention.
- Figure 25. It is a schematic sectional elevation view of another large toroidal reactor, in which the inner chamber of the toroid that forms the internal wall of the toroidal annular chamber where the annular wing is located, could be used as a cabin, Cargo warehouse, or other uses.
- Figure 26. It is a schematic elevation view of a rotating two-cylinder reactor with the improvements contemplated by the invention.
- Figure 27 It is a schematic plan view of a rotating cylinder with a pushing device of a vacuum inductor profile, which advances in the cylindrical flow of the reactor.
- Figure 28. It is a diagram of the vacuum influence zone induced by the fluid velocity on the corresponding inductor profile.
- Figure 29.- It is a plan view, similar to Figure 2 but including a double system or pushing device with two inductor profiles: one, the upper one, with a vacuum effect and the other, the lower one, with a pressure effect.
- Figure 30.- It is a schematic view of the pressure influence zone induced by the velocity of the fluid on the corresponding inductor profile.
- Figure 31.- It is a schematic view similar to Figure 4, to see the smaller thickness of fluid that is used with embossed surfaces in both inductor profiles.
- Figure 32. It is an enlarged detail of a vacuum inductor profile, with its active surface provided with mounds to see the influence on depression, induced by the minimum speed.
- Figure 33. It is a detail similar to Figure 7, but with hollows or depressions generating overpressure.
- Figure 34a It is a plan view of an apparatus for inducing vacuum to the fluid that is thus cooling, losing energy and therefore considerable cooling.
- Figure 34b. It is a plan view of an apparatus for inducing pressure to the fluid that is thus heating, gaining energy and therefore considerable heating.
- Figure 35 It is a schematic sectional elevation view of a cold or heat generating apparatus, in which the fluid itself to be cooled, heated, or in general to be heated, is the one contained within the tank.
- Figure 36 It is a schematic view similar to Figure 10, when the cold or heat generating apparatus has the fluid of such high density that it can be passed to another lighter fluid inside and that it is the one that is exchanged or Pumps to cool or heat the desired element, occupying the internal volume.
- Figure 37 It is a view similar to the previous one, with the exchange fluid of lower density, forming another layer coaxial when also displaced by the centrifugal force generated.
- Figure 38 It is a view similar to Figures 10 to 12, with the exchange fluid in an independent chamber located in the inner wall of the cylinder.
- A Effective force produced by the profile of wing 1 to the passage of a fluid.
- FIG 2 we see schematically represented the way to move a fluid in a circular direction, within two tubular structures 2 and 3, being in this case concentric although with an oval section.
- the wings 1 would be located in the upper and lower areas of the annular chamber 4 configured between both surfaces concentric tubular 2 and 3.
- FIG 3 we see schematically represented the cross section of another annular chamber 4 configured between two generally elliptical and concentric surfaces 2 'and 3'. Being the circular and non-linear flow, another type of section may be of interest for the inner 3 'and outer 2' cylinders, thus achieving minimal friction.
- the design of the wings 1 can vary considerably, not only as an adaptation to a cyclic flow with interesting centrifugal forces, but also depending on the speed and type of fluid.
- the calculation of the profiles of both the container cylinders and the wings has to be studied and tested for a long time since a new concept of fluid mechanics is opened and there are many variants that can be included to optimize the consumption and motor performance.
- the distances between the profile of the wing 1 and the upper and lower walls of the cylinders, as can be deduced when observing Figure 5, will be ideal for achieving an approximately inert laminar flow without considerable influence by friction on the walls 2 and 3, as produced by the wing. Also, physical surface treatments (semi-dryness such as golf balls or similar) and chemical treatments may be applied.
- Figure 6 shows how to move the circular fluid, mechanically by means of propellers 5.
- Figure 9 shows a fluid movement system made by induction reactors or magnetic stirrers, which lacking moving parts would be the best option to not disturb the flow, provided that the systems were as light as possible.
- FIG. 12a Just as in relation to figure 10 we saw a balance system of the pair of forces by means of two parallel cylinders, other possible ways to solve this problem are shown in figures 12a and 12b, arranging the cylinders forming a three- and four-sided polygon respectively.
- the number of sides can be increased and thus come to the conception of a toroidal arrangement such as that shown in Figure 12c, which allows solving the fluid problem in an equivalent manner to that of a turbine and is easier to produce an induced rotation.
- annular wing element 8 or 8 the fluid must be passed in order for it to act and sustain and move the reactor.
- mechanical means or inductive means can be used.
- Double turbine of dextrógiras and levógiras blades is used, inside or outside the toroidal shape.
- Reference 9 of Figure 14a designates these turbines. In the case of being located towards the walls closest to the center of the toroidal shape, they are referenced with 9 'and if they are in the outer zone and therefore have a larger diameter, they are with 9' •.
- FIG 15a the schematic section of a toroidal reactor is observed, the external toroidal wall is referenced with the number 12 and the internal one with the number 13, the flow circulating in the direction indicated by the arrows.
- the third system is to include a retracted alar section 18 within the flow zone, as shown in Figure 19. With the wing 18 positioned vertically interfering with the flow, the wing traction will be lateral. The displacement of the wing can be achieved by a mechanical or hydraulic system.
- Figure 16 we see schematically how to rotate the ship on its transverse axis.
- a piece 14 is placed inside the flow, similar to that referenced with the number 7 in Figure 11 (lia, 11b and 11c).
- This piece 14 is spindle-shaped and consists of a fixed central part 15 and two other mobiles 16 and 17 at its ends.
- the rotation will be forced in one direction or another, as shown in positions b) and c) of this figure 16.
- the rotational wing 14 will have the leading edge in the same direction as the leading edge of the main wing 1 and at the bottom will be in the reverse position.
- Figure 20 shows schematically in two positions a) and b), the section of a toroidal reactor with walls 12 (exterior) and 13 (interior), in which two or more annular wings 8 or 8 'have been placed, which can be placed in parallel or one behind the other so that maximum performance is obtained according to the fluid and / or the speed of the latter and / or the shape of the profile.
- the toroidal section of the outer surface and the inside of the reactor will have a specific profile depending on the fluid introduced and in search of the greater performance of the whole.
- Figure 21 shows an apparatus 19 with annular wings 8 with radial flow outwards and a turbine 9 of high flow and compensated double rotation.
- Figure 22 shows the option of ring wings 8 and 8 'with radial flow outward and inward, thus channeling the air further towards the axial outlet area of the flow.
- the reactor is operated by any of the systems described. It could be placed in the axial emptying of the anatospheric antigravity toroidal reactor, such as the one generally referenced with the number 20 of figure 24, a cabin 21 for transporting people and goods.
- the inner toroid chamber 13 could be used, such as cabin, cargo warehouse, engines and even fuel.
- toroids or cylindrical sections could be applied to ships of great weight to be able to land and take off at points where the gravity is higher or to give it greater acceleration and speed of movement.
- the profile 33 is a pressure inducer instead of a vacuum because, as seen more clearly in Figure 30, it has a central depression that disturbs the liquid vein in the sense of increasing its section and therefore an area of influence is formed 31 'of the forces generated and whose result is radial and of the same meaning (or practically the same) to the forces 29 generated by the profile 25, referenced in this case with 29' because they go to the profile 33 and therefore add up.
- This profile 33 is a pressure inducer or compression force on the corresponding cylinder or piston 26.
- Figures 31 to 33 show the general arrangement of a cylinder 22 of the reactor, similar to that of Figure 29, in which a fluid 24 has been used. preferably of high density with low wall thickness and vacuum and pressure inducing profiles, referenced respectively with 25 • and 33 ', which have their embossed active surface to increase their action on the fluid. Embossing is defined by equidistant or non-symmetrical mounds. or asymmetric, which form a surface such as the mold of a golf ball or the like, in the profile 25 'vacuum inductor (figure 32); and by alveoli or depressions 36, symmetrical or not in the profile 33 'which thus has a surface such as that of a golf ball or the like, inducing overpressure (Figure 33). It is also expected that the fluid will be in addition to dense, viscous to avoid the turbulent wake that could form, as we had said before.
- vacuum or pressure inductors respectively diametrically opposed and emerging from the fixed axis 34, whose effects are counteracted (see figures 34a and 34b). They could be more than two, being evenly distributed angularly, by way of three or more radios. It could also work with a single profile, preventing movement of the apparatus by directing the resulting force towards a dead zone, such as the ground.
Abstract
Applications Claiming Priority (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 WO2005113981A1 (fr) | 2005-12-01 |
Family
ID=35428446
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/ES2005/000288 WO2005113981A1 (fr) | 2004-05-21 | 2005-05-20 | Reacteur fluido-dynamique |
Country Status (1)
Country | Link |
---|---|
WO (1) | WO2005113981A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2012091533A3 (fr) * | 2010-12-27 | 2013-02-28 | Alibi Akhmejanov | Dispositif pour générer une force de sustentation (options) |
US20160009376A1 (en) * | 2012-12-09 | 2016-01-14 | Bogdan Tudor Bucheru | Semi-open Fluid Jet VTOL Aircraft |
EA032549B1 (ru) * | 2017-10-11 | 2019-06-28 | Алиби Хакимович Ахмеджанов | Аэродинамический аппарат |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58214681A (ja) * | 1982-06-07 | 1983-12-13 | Yukutada Naito | 無反動推進機関 |
US4953397A (en) * | 1989-07-25 | 1990-09-04 | The Boeing Company | Continuous flow hypersonic centrifugal wind tunnel |
WO1994020741A1 (fr) * | 1993-03-02 | 1994-09-15 | Jae Hwan Kim | Systeme generant une puissance, une force de propulsion et une sustentation a l'aide d'un fluide |
ES2154603A1 (es) * | 1999-09-02 | 2001-04-01 | Blazquez Cayetano Vazquez | Vehiculo apto para viajes y transportes. |
-
2005
- 2005-05-20 WO PCT/ES2005/000288 patent/WO2005113981A1/fr active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS58214681A (ja) * | 1982-06-07 | 1983-12-13 | Yukutada Naito | 無反動推進機関 |
US4953397A (en) * | 1989-07-25 | 1990-09-04 | The Boeing Company | Continuous flow hypersonic centrifugal wind tunnel |
WO1994020741A1 (fr) * | 1993-03-02 | 1994-09-15 | Jae Hwan Kim | Systeme generant une puissance, une force de propulsion et une sustentation a l'aide d'un fluide |
ES2154603A1 (es) * | 1999-09-02 | 2001-04-01 | Blazquez Cayetano Vazquez | Vehiculo apto para viajes y transportes. |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2012091533A3 (fr) * | 2010-12-27 | 2013-02-28 | Alibi Akhmejanov | Dispositif pour générer une force de sustentation (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 |
EA032549B1 (ru) * | 2017-10-11 | 2019-06-28 | Алиби Хакимович Ахмеджанов | Аэродинамический аппарат |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
ES2694040T3 (es) | Aparato volador de despegue vertical | |
ES2224218T3 (es) | Aerogenerador con efecto magnus. | |
ES2539950T3 (es) | Dispositivo de restricción de balanceo para turbinas eólicas | |
US9863313B2 (en) | Power generation using buoyancy-induced vortices | |
ES2745760T3 (es) | Deflector de flujo para pala | |
WO2005113981A1 (fr) | Reacteur fluido-dynamique | |
US11427300B2 (en) | Lift nacelle | |
WO2017055649A1 (fr) | Dispositif pour convertir l'énergie cinétique d'un flux des vagues, de vent ou de cours d'eau en énergie mécanique de rotation | |
EP3573889B1 (fr) | Appareil aérodynamique | |
US20200079496A1 (en) | Pipe Props Rotary Wing | |
CN207045724U (zh) | 旋翼飞行器 | |
ES2544557T3 (es) | Turbina eólica de eje vertical con rotores Flettner | |
ES2291550T3 (es) | Turbina eolica darrieus. | |
WO2012023866A1 (fr) | Génératrice éolienne marine à pales extensibles | |
US11739731B2 (en) | Vortex station | |
WO2012078122A1 (fr) | Procédé de génération de poussée et dispositif de sa mise en oeuvre | |
ES2514990B2 (es) | Sistema de aceleración del flujo del aire para aerogeneradores | |
RU2516986C1 (ru) | Аэродинамическая градирня | |
ES2911109B2 (es) | Turbina oblonga | |
ES2397408B1 (es) | Fuente, que aprovecha la diferencia de densidad de los fluidos, para la producción de energía renovable, mejorada. | |
JP2012503140A (ja) | スラストエンジン | |
ES2287795T3 (es) | Aeronave. | |
US20240060472A1 (en) | Vortex station | |
ES2751752T3 (es) | Perfil aerodinámico y aparato de turbina | |
ES2365074B1 (es) | Fuente, que aprovecha la diferencia de densidad de los fluidos, para la producción de energía renovable. |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
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 |
|
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 |
|
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 |
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 |