Abstract
The invention relates to a gaseous fuel composite, a device for producing the gaseous fuel composite, and subcomponents used as part of the device for producing the gaseous fuel composite, and more specifically, to a gaseous composite made of a gas fuel such as natural gas and its oxidant such as air for burning as part of different systems such as fuel burners, combustion chambers, and the like. The device includes several vortex generators each with a curved aerodynamic channel amplifier to create a stream of air to aerate the gas as successive stages using both upward and rotational kinetic energy. Further, a vortex generator may have an axial channel with a conical shape or use different curved channel amplifiers to further create the gaseous fuel composite.
Claims
1. A device for producing a gaseous fuel composite, comprising: an inlet connected a source of gas fuel, a housing between the inlet and an outlet for the passage a gas fuel from the inlet to the outlet from the source of gas fuel, and a plurality of vortex generators, each with an axial channel, the generators being in a stacked configuration in relation to the other vortex generators in the housing between the inlet and the outlet, wherein each of the vortex generators includes a flange defining a ring channel in fluid connection with at least a source of air and a plurality of apertures and associated tangential channels for the passage of air from the ring channel through the apertures and the associated tangential channel for release of the air from the ring channel into the axial channel to form a gaseous fuel composite made of the gas fuel and at least air from the at least one source of air, wherein at least a connection between one of the apertures and the associated tangential channel includes a first curved aerodynamic channel amplifier having a first curvature.
2. The device for producing a gaseous fuel composite of claim 1, wherein the outlet is a nozzle.
3. The device for producing a gaseous fuel composite of claim 2, wherein the gas fuel is natural gas and the device is used in a commercial burner.
4. The device for producing a gaseous fuel composite of claim 1, wherein the inlet is a cylindrical gas inlet.
5. The device for producing a gaseous fuel composite of claim 1, wherein at least another connection between one of the apertures and the associated tangential channel includes a second curved aerodynamic channel amplifier having a second curvature.
6. The device for producing a gaseous fuel composite of claim 1, wherein at least one of the plurality of vortex generators includes a conical axial channel.
7. The device for producing a gaseous fuel composite of claim 1, wherein the plurality of vortex generators is at least three vortex generators.
8. The device for producing a gaseous fuel composite of claim 6, wherein the plurality of vortex generators is at least three vortex generators in addition to the vortex generator with the conical axial channel.
9. A vortex generator for producing a gaseous fuel composite, comprising an axial channel opening, a flange defining a ring channel, and a plurality of apertures in the ring channel, each with an associated tangential channel, for the creation of a passageway from the ring channel through the apertures and the associated tangential channel into the axial channel opening, and wherein at least a connection between one of the apertures and the associated tangential channel includes a first curved aerodynamic channel amplifier having a first curvature.
10. The vortex generator of claim 9, wherein at least another connection between one of the apertures and the associated tangential channel includes a second curved aerodynamic channel amplifier having a second curvature.
11. The vortex generator of claim 9, wherein the axial channel has a conical shape.
12. The vortex generator of claim 9, wherein the ring channel includes a curved portion.
13. A system for the production of a gaseous fuel composite, comprising the process of transforming a gas fuel into a gaseous fuel composite by successive steps of: connecting a device for the production of a gaseous fuel composite to an inlet connected a source of gas fuel having a plurality of vortex generators each with an axial channel, the generators being in a stacked configuration in relation to the other vortex generators in a housing between the inlet and an outlet, wherein each of the vortex generators including a flange defining a ring channel and a plurality of apertures and associated tangential channels, wherein at least a connection between one of the apertures and the associated tangential channel includes a first curved aerodynamic channel amplifier having a first curvature, and aerating the gas fuel with a stream of air traveling from the ring channel via at least one of the plurality of apertures and associated tangential channel into the axial channel for mixture of a first quantity of air with the gas fuel using one of the plurality of vortex generators, and wherein the stream of air includes an upward motion created by the first curvature and a circular motion to form a gaseous fuel composite.
14. The system of claim 13, further comprising a subsequent step of using at least a second vortex generator for further aerating the gaseous fuel composite.
15. The system of claim 13, wherein the gaseous fuel composite is released from the device at a nozzle.
16. The system of claim 13, wherein the gas fuel is natural gas and the system is used to improve the performances of a commercial burner.
17. The system of claim 13, wherein at least another connection between one of the apertures and the associated tangential channel includes a second curved aerodynamic channel amplifier having a second curvature.
18. The system of claim 13, wherein at least one of the plurality of vortex generators includes a conical axial channel.
19. A gaseous fuel composite made of a first gas fuel traveling linearly and aerated by a series of at least two streams at different staggered distances along a linear axial chamber, where each stream includes kinetic energy in the form of a circular motion and kinetic energy in the form of an upward motion, and where the stream is further compressed and accelerated in the axial chamber by a conical reduction of the axial chamber and a nozzle release.
20. The gaseous fuel composite of claim 19, wherein the gas fuel is a natural gas and the nozzle is connected to a burner.
Description
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Certain embodiments are shown in the drawings. However, it is understood that the present disclosure is not limited to the arrangements and instrumentality shown in the attached drawings.
[0013] FIG. 1A is a cross-section of a device for producing a fuel composite from a fuel gas according to an embodiment of the present disclosure.
[0014] FIG. 1 is the device of FIG. 1A where of the radius is illustrated in volumetric solid and the front left quarter has been removed to better illustrate the different elements of the embodiment of the present disclosure.
[0015] FIG. 1B is a plan view of the device of FIG. 1C as shown along cut line A-A illustrating the five generator rings.
[0016] FIG. 1C is an isometric representation of the device of FIG. 1.
[0017] FIG. 1D is a plan view of the device of FIG. 1C as shown along cut line B-B illustrating the input and output zones.
[0018] FIG. 2 is a partially cut view of the device of FIG. 1 where the external housing is opened at approximately 120 and where approximately 90 is removed from the generators for better illustration.
[0019] FIG. 3 is a vortex generator ring with a curved ring channel and a curved tangential channel according to an embodiment of the present disclosure.
[0020] FIG. 3A is a top view and the associated plan view along cut line A-A of the vortex generator ring of FIG. 3.
[0021] FIG. 3B is a top view of the vortex generator ring of FIG. 3.
[0022] FIG. 3C is a series of three isometric views at different orientations of the vortex generator ring of FIG. 3.
[0023] FIG. 3D is a top view and the associated partial plan view along cut line C-C of the vortex generator ring of FIG. 3.
[0024] FIG. 3E is a close-up portion of the partial plan view as shown by circle D in FIG. 3D.
[0025] FIG. 4 is a top isometric view of a vortex generator ring illustrating the flow of gas from the ring channel to the axial channel and forming a vortex according to an embodiment of the present disclosure.
[0026] FIG. 5 is a perspective view of the vortex generator of FIG. 4 with a cut-off section to better illustrate the flow of gas from the ring channel to the axial channel.
[0027] FIG. 6 is a side view of a 3D illustration of the vortex generator of FIG. 4 illustrating how the curved tangential channel creates an upward movement in the air as it enters the axial channel.
[0028] FIG. 6A is a top view and the associated plan view along cut line A-A of the vortex generator ring of FIG. 6.
[0029] FIG. 6B is a top view of the vortex generator ring of FIG. 6.
[0030] FIG. 6C is a series of three isometric views at different orientations of the vortex generator ring of FIG. 6.
[0031] FIG. 7 is the side view of FIG. 6 illustrating how the upward movement in the air mixes in with the flow of the gas fuel in the axial channel.
[0032] FIG. 7A is a top view of the vortex generator ring of FIG. 7 a along with a plan view see from cut line A-A.
[0033] FIG. 7B is a series of two isometric views at different orientations of the vortex generator ring of FIG. 7.
[0034] FIG. 8 is a median cross-cut view of the vortex generator as shown in FIG. 7 illustrating the upward movement of the oxidant gas within the fuel gas in the axial channel.
[0035] FIG. 9 is a side view of the vortex generator of FIG. 7 illustrating the upward movement of the oxidant gas in the fuel gas.
[0036] FIG. 9A s a top view of the vortex generator ring of FIG. 9.
[0037] FIG. 9B is a cut view taken along cut line A-A illustrating the curved ring channel.
[0038] FIG. 9C is a series of two isometric views at different orientations of the vortex generator ring of FIG. 9.
[0039] FIG. 10 is a top view of the vortex generator of FIG. 9 illustrating the perpendicular flow of oxidant gas along the tangential channels.
[0040] FIG. 11 is a plan view of the device of FIG. 1 illustrating the compression and formation of the gaseous fuel composite at the nozzle according to an embodiment of the present disclosure.
[0041] FIG. 12 is a plan view of a portion of the device of FIG. 1 where several vortex generators are stacked each with different configurations according to another embodiment of the present disclosure.
[0042] FIG. 13 is a partially cut view of the device of FIG. 12 illustrating the device of FIG. 1 where several different vortex generators are stacked linearly in the device.
[0043] FIG. 14 is a partially cut view of the device of FIG. 12 illustrating a different removed portion than in FIG. 13.
[0044] FIG. 15 is a side view of a three-dimensional partly cut view of the device of FIG. 12 illustrating the different channels.
[0045] FIG. 16 is a three-dimensional view with dashed lines of the different portions of the top vortex generator placed next to the nozzle of the device of FIG. 12 according to an embodiment of the present disclosure.
[0046] FIG. 16A is a top view of the vortex generator ring of FIG. 16.
[0047] FIG. 16B is a cut view taken along cut line A-A illustrating the tangential channels.
[0048] FIG. 16C is a series of two isometric views at different orientations of the vortex generator ring of FIG. 16.
[0049] FIG. 17 is a partly cut away view of the vortex generator of FIG. 16 with an internal conical portion as part of the axial channel.
[0050] FIG. 18 is a top view of the vortex generator of FIG. 16.
[0051] FIG. 19 is a partly cut away view of the vortex generator of FIG. 16 illustrating the different flows within the device.
DETAILED DESCRIPTION
[0052] For the purposes of promoting and understanding the principles disclosed herein, reference is now made to the preferred embodiments illustrated in the drawings, and specific language is used to describe the same. It is nevertheless understood that no limitation of the scope of the invention is hereby intended. Such alterations and further modifications in the illustrated devices and such further applications of the principles disclosed and illustrated herein are contemplated as would normally occur to one skilled in the art to which this disclosure relates.
[0053] Incorporation by Reference
[0054] The following specification incorporates by reference all figures, disclosures, claims, headers, and titles of International Application Nos. PCT/US08/75374, filed Sep. 5, 2008, entitled Dynamic Mixing of Fluids, and PCT/US08/075,366, also filed on Sep. 5, 2008, entitled Method of Dynamic Mixing of Fluids, along with nationalized U.S. application Ser. Nos. 12/529,625, filed Sep. 2, 2009, entitled Dynamic Mixing of Fluids, and 12/529,617, filed Sep. 2, 2009, entitled Method of Dynamic Mixing of Fluids, and International Application No. PCT/US2009/043547, filed on May 12, 2009, also entitled System and Apparatus for Condensation of Liquid from Gas and Method of Collection of Liquid.
[0055] Energy Efficiency Test
[0056] In one embodiment, methane gas (CH.sub.4) is used as the fuel gas and air containing oxygen gas (O.sub.2) is used as the oxidant of the methane gas. The chemical equation associated with the combustion of the methane is described as: CH.sub.4+2O.sub.2CO.sub.2+2H.sub.2O. Two molecules of water are created during this process and two molecules of oxygen are needed for the combustion.
[0057] At room pressure, with 1 mol of gas taking the volume of 22.4 liters, a volume of 22.4 m.sup.3 of methane gas corresponds to 1000 mol of gas where this gas having a molar mass of 16.042 g/mol producing a weight of 16.042 kg of CH.sub.4 for the 1000 mol of gas. The weight of the oxygen needed for the combustion is 64.0192 kg based on a molar mass at room temperature of 32.0096 g/mol and produces 36.03 kg of water at a molar mass of 18.015 g/mol.
[0058] In a burner, a flow of methane of 1000 scf/h enters the combustion chamber (1 scf=28.32 liters, 1000 scf/h=28.32 m.sup.3/h, or 1264 mol/h). At the flow rate of 1000 scf/h, the reaction requires 80.92 kg/h of oxygen, and produces 45.514 kg/h of water.
[0059] In one test, 9,700 scf/h of air is introduced into the device to produce a gaseous fuel composite. Air has 21% oxygen, so the oxygen introduced is 2,037 scf/h. This volume is taken as the stoichiometric ratio of methane to air for combustion. The gaseous fuel composite has a total weight of 10,670 scf/h (1000 scf/h of methane and 9,700 scf/h of air).
[0060] The optimal thermal output for methane gas is 891 kj/mol or 840 BTU/mol (1 BTU=1.06 kj). Burning of 1000 scf/h of methane or 1264 mol/h of methane corresponds to 1,061,760 BTU/h of thermal output. The real thermal energy released is found to be 90% of the maximal output or approximately 955,585 BTU/h for a natural gas.
[0061] A test was conducted with and without the device shown in FIG. 1 installed on a commercial burner. Without the device, the following was measured: air input T.sub.ai=3 C. (37 F.), air output T.sub.o=66 C. (152 F.), with T=T.sub.oT.sub.ai=63 C., air input humidity 68% with c.sub.air=1.018 kj/(kg K) resulting in 64.134 kj or 60.848 BTU of energy used to heat the air from the combustion of the gaseous fluid composite. As 10,911 scf of air was used, corresponding to 309 liters of air or 370.8 kg of air, the heating energy was 23,780 kj or 22,652 BTU.
[0062] With the device, the volume of the fuel composite being 1000 scf/h and 2,448 scf of air with a 29% volume of gas in the fuel composite, a total of 45.51 kg of water is released per hour if no other source of intake is taken outside of the gaseous fuel composite. The thermal efficiency taken at 90% of the theoretical value of 955,585 BTU/h for a gas with 29% of methane is 277,119 BTU/h.
[0063] With the device for producing the gaseous fuel composite, air input T.sub.ai=11 C. (52 F.), air output T.sub.o=85.5 C. (185.5 F.), with T=T.sub.oT.sub.ai=74.5 C., air input humidity 87% with c.sub.air=1.027 kj/(kg K) resulting in 76.5115 kj or 72.59 BTU of energy used to heat the air from the combustion of the gaseous fluid composite. With a volume of air of 10,741 scf during the heat exchange corresponding to 365.022 kg of air, the energy needed to heat is 26,497 BTU.
[0064] As a consequence, 26,497 BTU are used to warm the air using the device for producing the gaseous fuel composite when compared with 22,652 BTU without the device. The increased output with the device is 3,845 BTU or approximately 17%. This corresponds to the increase in thermal efficiency of burning of the natural gas when it is first transformed into a gaseous fuel composite.
[0065] Carbon Oxide Release Test
[0066] Under normal circumstances, gas is sent out into a burner using an atomizer where the natural gas is dispersed in air in an open chamber. In the gaseous fuel composite device as shown in FIG. 1, a gas fuel composite created with air is merged into the natural gas before it is released into the burner. In a test, 100% of stoichiometric air was provided in a furnace via the atomizer with at least 10% excess air. The monoxide of carbon concentration under high fire is 1,093 ppm (or mg) for a gas flow of 1000 scf/h, and with a ratio of 1:5 on the concentration of CO and CO.sub.2, the concentration is 5,465 ppm (or mg) for the same input volume. For a lower gas flow of 505.241 scf/h corresponding to a low-fire condition, the CO concentration is 3,999.36 ppm and the concentration of CO.sub.2 is 20,000 ppm.
[0067] In a test with the device for producing a gaseous fuel composite as shown in FIG. 1, only 25% of the stoichiometric air is inserted into the natural gas to form the composite at a ratio of 1:2.425. In addition, another 10% in volume of air was added from the furnace for a total of 35% air. For a high-fire condition with a natural gas flow of 1000 scf/hr, 259.76 ppm of CO were measured, and by analogy, 1298.8 ppm of CO.sub.2 are found. At a low-fire condition of 504.76 scf/hr of natural gas, the concentration of CO measured is 823.46 ppm and CO.sub.2 is 4,115 ppm.
[0068] When compared to high-fire conditions, the production of CO is reduced from 1,093 to 259.76 ppm, and at low-fire conditions is reduced from 3,999.36 to 823.46 ppm, reductions of 23.8% and 20.6%, respectively. Therefore, it is found that by creating a gaseous fuel composite, even with a small fraction of the stoichiometric air, thermal efficiency improves significantly and production of undesired byproducts is reduced greatly. Atomizer design in the device for producing a gaseous fuel composite allows for optimization of fuel burning and the degradation of unburned fuel. When using an actual gas burner where the thermal efficiency can be as low as 60% to 65%, what is contemplated is improvements in thermal efficiency and degradation of byproducts, impurities, or other unburned fuel elements as part of the process.
[0069] Device for Producing a Gaseous Fuel Composite
[0070] A device for the production of a gaseous fuel composite 10 is shown in FIGS. 1, 2, and 11-15. The different views and embodiments show different possible vortex generators 20 that are described and shown with greater detail in FIGS. 3-10 and 16-19. The system centers on the passage of a fuel gas 112 shown at the bottom of FIG. 1 inside of an axial chamber formed in one example by stacking a plurality of vortex generators 103, 104, 105, 106, and 107, each having an axial opening for the passage from one end shown as area 1 in FIG. 1 to the other end shown as area 7 such as a nozzle 108 or another connector pipe (not shown). The axial opening as shown in FIG. 1A has a constant section until it enters a vortex generator as shown in FIGS. 16-19.
[0071] As the section of the axial opening is reduced, either the speed of the gaseous fuel composite is increased, the density of the gaseous fuel composite is increased, or a combination of both based on upstream conditions. The device 10 as shown includes an upper flange 114 and a lower flange 113 connected hermetically with a housing 102 as shown in the shape of a cylinder with inlets for an external oxidant gas. FIG. 1A shows how multiple sources of air may enter the housing into the ring channels structure also shown in FIG. 2. The air 201, 202, 203, 204, and 205 enters the ring channels and moves upward into transit apertures leading up to tangential channels until the air is released in the axial chamber as shown by 206, 207, 208, 209, and 240, respectively.
[0072] The multistage process shown in FIGS. 1 and 2 where air enters ring channels using a plurality of stacked vortex generators 20 allows for the creating of a gaseous fuel composite in a multistep acceleration process. In this example, five air sources are used, each entering the five ring channels of the vortex generators at areas 2, 3, 4, 5, and 6 as shown in FIG. 1. For example, if the flow of air is constant at the five sources 201, 202, 203, 204, and 205 and represents a fixed fraction of the flow of gas 112 into the device 10, then at the interface between areas 2 and 3 in FIG. 1, the gas is merged with a first portion of air to create the first stage of the gaseous fluid composite. At the interface between area 3 and 4, the already partly aerated gas is further diluted by air, and so on in each successive stage. As the air enters into an area of constant volume, the pressure, density, and speed of the gaseous fuel composite increase. At the nozzle 108, the final stage of the gaseous fuel composite is formed, which exits at 109 as a mixture of air from all of the sources and the gas fuel 112.
[0073] Air is not mixed in the multistage process to produce a gaseous fluid composite simply by releasing air into the internal cavity. FIG. 1B shows in a plan view how within a single device as shown in FIG. 1C the multiple vortex generators are stacked in zones 2, 3, 4, 5, and 6. The device 10 as shown is compact and serves as a device that can be used to replace conventional nozzles. FIG. 1D shows two possible inlet and outlet interfaces 1 and 7, respectively, as part of the device 10.
[0074] FIG. 3 shows one vortex generator 10 where the axial channel 301 is shown in dashed lines and allows for the passage of the gas fuel and the ultimate creation of a gaseous fuel composite. A flange 302 shown with a square rim closes a channel 303 where air enters and travels upward via apertures 304 to tangential channels 306 via aerodynamic channel amplifiers 305 shown to be curved inwards to allow for the air within the channel 303 to travel upward in the apertures 304 and then to the tangential channels 306 in a 90 degree bend in an area where the flow is bent and pressure drops are observed because of the change in direction at the bend. FIGS. 3A-3C illustrate the vortex generator 10 of FIG. 3. FIGS. 3D and 3E show in close-up views how the air can travel upward from the channel 303 to the aperture 304 and then bend inwards over the curved aerodynamic channel amplifiers 305.
[0075] Using a dark arrow, FIG. 4 shows how the air moves around and out of the aperture 304 as illustrated 401 and slides 402 into the tangential channel 306 around a curved aerodynamic channel amplifier 305 in a resulting circular motion 403. A different view of this effect is shown in FIG. 5 where air 201 moves up 502 and slides 401 over the aerodynamic channel amplifier before it is released 402 into the circular motion 403.
[0076] As shown in FIG. 5, the ring channel also includes an internal curve that results in a first curvature 501 of the flow before it enters the aperture. As the flow of air travels over the curved aerodynamic channel amplifier and slides 401, the molecules of air have an upward portion of kinetic energy that remains in the air upon release 402 into the cavity for the circular motion 403. Since the incoming gas fuel 112 has also an upward movement, the upward portion of the kinetic energy is conserved and amplifies the upward movement of the gaseous fuel composite. FIGS. 6A-6C illustrate alternative views of the vortex generator 20 of FIG. 6.
[0077] As the tangential channels create a vortex-like movement of the air as it enters the vertical cavity and mixes with the gas fuel 112 it has two vector components: a rotational energy that creates a rotational movement of the gaseous fuel composite and an upward energy that lifts the gaseous fuel composite and increases the speed and energy of the overall gaseous fuel composite. When both of these vectors are merged with the upward movement of the gaseous fuel composite, the resulting upward vortex 701 and 702 is created. FIGS. 7A and 7B illustrate alternative views of the vortex generator 20 of FIG. 7. FIGS. 8 and 9 are different views of the vortex generator 20 of FIG. 7, which illustrates the dynamic flow created by the generator 20 within the gas fuel 112. FIGS. 9A-9C illustrate alternative views of the vortex generator 20 of FIG. 9. Element 901 of FIG. 9 illustrates the upward vertical kinetic energy of the air after it is released within the gas fuel 112.
[0078] Using arrows, FIG. 11 shows how the gaseous composite goes from a first stage 702 upwards in one or two stages 1101 and 1101 where the axial channel is conical and results in the compression of the highly energized gas mixture in a nozzle 1103. As shown in FIG. 12, not all aerodynamic channel amplifiers can be curved or bent with the same radius. Because of the way the plan view is cut in a vortex generator 20 having a good number of apertures and associated tangential channels and aerodynamic channel amplifiers, these appear as different configurations 1201, 1202, 1203, 1204, and 1105. In one embodiment, the dimensions of the apertures and channels are the same across all vortex generators within a device 10, and in other embodiments, the flow of air and the dimensions of apertures and channels differ from one vortex generator to the next to help regulate a multistep process. FIGS. 13-15 are different views of the device 10 illustrating how configurations of the vortex generators 103, 104, 105, 106, and 107, can differ 1403, 1404, 1405, 1406, and 1407, and 1501, 1502, 1503, 1504, and 1505, respectively. Associated ring channels 1506, 1507, 1508, 1509, and 1510 are also shown in FIG. 15.
[0079] FIGS. 16-19 are different illustrations of a vortex generator 1105 as shown in FIG. 12, where a conical internal axial channel is present. In this embodiment, the flange 1505 remains at the same radius as the other vortex generators, creating a ring channel 1510 for the passage of air via the apertures 1602 over the curved aerodynamic channel amplifier 1104 with a first radius or a second type of aerodynamic channel amplifier 1105 with a second radius. FIGS. 16A-16C illustrate alternative views of the vortex generator 20 of FIG. 9. FIG. 17 shows the external radius on the flange 1701 where tangential channels 1607 and apertures 1602 are located in close proximity to the reducing vertical passageway. FIG. 18 shows as 1801 how some apertures can include a first type of aerodynamic channel amplifier 1105 and how a second type of apertures 1407 can include a second type of aerodynamic channel amplifier 1104. FIG. 19 is another illustration of the vortex generator according to a different view and illustrates how the air flows outside of the tangential channels.
[0080] What is shown in FIG. 1 is a device 10 for producing a gaseous fuel composite with an inlet 101 connected a source of gas fuel 112, a housing 102 between the inlet 101 and an outlet 108 for the passage a gas fuel 112 from the inlet 102 to the outlet 108 from the source of gas fuel, and a plurality of vortex generators 103, 104, 105, 106, and 107, each with an axial channel 301 as shown in FIG. 3, the generators 103, 104, 105, 106, and 107 being in a stacked configuration in relation with the other vortex generators in the housing 102 between the inlet 101 and the outlet 108, where each of the vortex generators 103, 104, 105, 106, and 107 include a flange 302 defining a ring channel 303 in fluid connection as shown by the arrows 201, 202, 203, 204, and 205 in FIG. 2 with at least a source of air and a plurality of apertures 304 and associated tangential channels 306 for the passage of air from the ring channel 303 through the apertures 304 and the associated tangential channel 306 as shown in FIG. 4 for release of the air from the ring channel 303 into the axial channel 301 to form a gaseous fuel composite made of the gas fuel 112 and at least air from the at least one source of air 201, 202, 203, 204, and 205. Further, at least a connection between one of the apertures 304 and the associated tangential channels 306 includes a first curved aerodynamic channel amplifier 305 having a first curvature as shown in FIG. 3.
[0081] In one embodiment, the outlet 108 is a nozzle as shown in FIG. 1. In another embodiment, the gas fuel 112 is natural gas made of, for example, methane. In another embodiment, the device 10 is used in a commercial burner (not shown). As shown in FIG. 1, the inlet 101 is a cylindrical gas inlet. In another embodiment shown in FIG. 18, at least another connection between one of the apertures and the associated tangential channel includes a second curved aerodynamic channel amplifier having a second curvature 1105 when compared with 1104. FIG. 17 also shows an embodiment where at least one of the plurality of vortex generators includes a conical 111 axial channel.
[0082] What is also described is a system for the production of a gaseous fuel composite comprising the process of transforming a gas fuel into a gaseous fuel composite by successive steps of connecting a device for the production of a gaseous fuel composite to an inlet connected to a source of gas fuel as shown by the black arrows at the bottom of FIG. 2, the system having a plurality of vortex generators each with an axial channel as shown, and aerating the gas fuel 112 as shown, for example, in FIG. 7 with a stream of air 402 traveling from the ring channel via at least one of the plurality of apertures 501 and associated tangential channels into the axial channel for mixture of a first quantity of air with the gas fuel 701, 702 using one of the plurality of vortex generators as shown. The stream of air includes an upward motion created by the first curvature 401 and a circular motion 403 as shown in FIG. 5 to form a gaseous fuel composite as shown by the arrows in the upper portion of FIG. 2.
[0083] There may be a subsequent step of using at least a second vortex generator for further aerating the gaseous fuel composite in a multistage process. Finally, a gaseous fuel composite as shown by the arrows in black in the upper portion of FIG. 2 is made of a first gas fuel 112 traveling linearly as shown by the arrows in the bottom of FIG. 2 and aerated by a series of at least two streams at different staggered distances along a linear axial chamber where each stream includes kinetic energy in the form of a circular motion 403 of FIG. 5 and kinetic energy in the form of an upward motion 402 of FIG. 6, and where the stream is further compressed and accelerated in the axial chamber as shown by the arrows 1101 in FIG. 11 by a conical reduction of the axial chamber and a nozzle release.
[0084] It is understood that the preceding is merely a detailed description of some examples and embodiments of the present invention and that numerous changes to the disclosed embodiments can be made in accordance with the disclosure made herein without departing from the spirit or scope of the invention. The preceding description, therefore, is not meant to limit the scope of the invention but to provide sufficient disclosure to one of ordinary skill in the art to practice the invention without undue burden.
