Venturi Apparatus With Forced Induction System and Method - Patent application

Abstract

A venturi device having a primary flow path and a secondary flow path introduced into the primary flow path, wherein the flow of one or more flowable media in the primary and secondary flow paths forms a vortex that creates suction at an inlet of the venturi device. The particulate burner system can be used to combust fuel exhaust by-products by injecting fuel and air into a housing having a bottom plate with a circular bottom opening through which the burner injects fuel into a combustion chamber and a top plate with a circular top opening through which the fuel exhaust is exhausted. The thruster system can be used to propel a deep earth penetrating munition by using a thruster system having a transfer cone connected to the munition body.

Description

[Technical field]

[0001] (CROSS REFERENCE TO RELATED APPLICATIONS) This application claims priority to U.S. Provisional Application No. 63 / 282556, filed on November 23, 2021, entitled "Particulate Burner," U.S. Provisional Application No. 63 / 265478, filed on December 15, 2021, entitled "Venturi Thermal Energy Conversion System," U.S. Provisional Application No. 63 / 265483, filed on December 15, 2021, entitled "NPR Hydro Turbine System," U.S. Provisional Application No. 63 / 265489, filed on December 15, 2021, entitled "Phase Shift Thermal Energy Conversion System," and U.S. Provisional Application No. 63 / 265484, filed on December 15, 2021, entitled "Phase Shift Thermal Energy Conversion System." "NPR Motor Cooling System", U.S. Provisional Application No. 63 / 265486, filed December 15, 2021; "NPR Forced Induction Charging and Heating System", U.S. Provisional Application No. 63 / 268053, filed February 15, 2022; "Stealth Ordnance Thruster", U.S. Provisional Application No. 63 / 381905, filed November 1, 2022; "Venturi Device with Forced Induction", U.S. Provisional Application No. 63 / 381906, filed November 1, 2022; "Venturi Device with Forced Induction", and International Patent Application No. PCT / US2022 / 026399, filed April 26, 2022, claims priority to International Patent Application No. PCT / IB2021 / 000237, filed April 27, 2021, entitled "Hybrid Hydro-Aerodynamic Forced Induction System," which claims priority to "Venturi Device with Forced Induction," filed April 27, 2021, each of which is incorporated by reference in its entirety and forms part of this disclosure. Related German Application Nos. DE102019003025.7, filed April 26, 2019, and DE102019006055.5, filed September 4, 2019, are incorporated by reference in their entireties herein and made part of this disclosure. All applications for which a foreign or domestic priority claim is identified in an Application Data Sheet filed with this application are hereby incorporated by reference pursuant to 37 CFR 1.57.

[0002] The present disclosure relates to Venturi devices and applications thereof. [Background technology]

[0003] The demand for cleaner drainage and fluid mechanism equipment has increased dramatically over the past century. With it comes the need for cleaner drainage and fluid mechanism equipment relief methods. Summary of the Invention [Problem to be solved by the invention]

[0004] The foregoing summary and the following detailed description are not intended to limit or define the scope of protection, which is defined by the claims.

[0005] The Venturi device can receive the primary flow of air ejected from the outlet. The fluid flows through the Venturi device through a converging section and a diverging section where a Venturi effect occurs, drawing the primary flow from an inlet of the Venturi device. The first funnel can form an annular space between the funnel and the body that creates a low pressure area relative to the high pressure fluid flow. A reduction in pressure can cause the low pressure in the annular space to flow toward the outlet. The second funnel can be disposed in the diverging section and also extending from the body to form a second low pressure area relative to the high pressure fluid flow. A reduction in pressure can cause the fluid in the low pressure area to flow toward the outlet. The secondary input can be disposed between the converging section and the outlet to direct the secondary flow of fluid into the primary flow and create a vortex that pulls the primary flow through the inlet. Downstream of the secondary input can include a conical surface having a cross-sectional flow area that increases toward the outlet, which can direct the primary flow toward the outlet. [Means for solving the problem]

[0006] The particulate burner system may be used to combust fuel exhaust by-products by injecting fuel and air into a housing having a bottom plate with a circular bottom opening through which the burner injects fuel into the combustion chamber and a top plate with a circular top opening through which the fuel exhaust is exhausted. The circular bottom opening and the top opening may be aligned along a central axis. A sidewall may be disposed between the bottom plate and the top plate and may include an opening for directing air tangentially into the combustion chamber. The air may be centrifugally directed along an inner periphery of the sidewall to entrain fuel into the airflow from the circular bottom opening. A deflector plate may be disposed within the combustion chamber and connected to at least one of the bottom plate or the top plate and disposed between the circular bottom opening and the sidewall opening. The deflector plate may mitigate the flow of fuel from the circular bottom opening to the sidewall and the flow of air from the sidewall to the circular bottom opening. A plurality of fences may be provided within the combustion chamber to direct the airflow along an inner periphery of the circular sidewall to entrain fuel toward the inner periphery. A venturi device may be connected to the sidewall opening to inject compressed air into the combustion chamber.

[0007] The thruster system can be used to propel the deep earth penetrating munition by using a thruster system having a transfer cone connected to the munition body. The transfer cone can direct the fluid flow from the munition body to the inlet of the Venturi device. A storage tank can be located on the munition body to store propellant to be injected into the inlet attached to the Venturi device. The stabilizing fin can extend radially outward of the munition body and can include one or more channels to connect the storage tank to the Venturi device. The movement of the primary flow through the converging and diverging portions of the Venturi device can create a Venturi effect. A secondary input can be located between the converging and the outlet and can induce a fluid flow in the primary flow to create a vortex and create suction at the inlet to draw the primary flow into the inlet. The secondary input can be connected to one or more channels in the stabilizer that can be used to provide thrust. [Brief description of the drawings]

[0008] The above-mentioned and other features of the configurations disclosed herein are described below with reference to the drawings of the configurations. The illustrated configurations are intended to illustrate, but not to limit, the scope of protection. Various features of different disclosed configurations can be combined to form further configurations that are part of the present disclosure. In the drawings, similar elements may be labeled with the same last two digits.

[0009] [Figure 1A] FIG. 1A is a cross-sectional view of an example Venturi device. [Figure 1B] FIG. 1B is an enlargement of a portion of the Venturi device of FIG. 1A. [Figure 1C] FIG. 1C is an enlargement of a portion of the Venturi device of FIG. 1A. [Diagram 2] FIG. 2 is a simplified schematic diagram of the Venturi device shown in FIG. 1A. [Diagram 3] 3 is a side view of a particulate burner for combustion of fuel exhaust by-products. A particulate burner may be incorporated into one or more of the venturi devices of FIG. 1A. [Figure 4] FIG. 4 is a schematic diagram of the particulate burner system shown in FIG. [Diagram 5] FIG. 5 shows the housing of the particulate burner shown in FIGS. [Figure 6] FIG. 6 shows the bottom plate of the particulate burner system. [Figure 7] FIG. 7 shows a detailed combustion chamber of the particulate burner system with deflector plates. [Figure 8] FIG. 8 shows the combustion chamber of a particulate burner system without deflectors. [Figure 9] FIG. 9 shows a fin from a plurality of fins arranged within a combustion chamber. [Figure 10] FIG. 10 shows a top view of the combustion chamber of the particulate burner system. [Figure 11]FIG. 11 shows a perspective view of the combustion chamber of a particulate burner system having protrusions protruding from the circular bottom opening. [Figure 12] FIG. 12 shows a cross-sectional side view of a particulate combustion system. [Figure 13] FIG. 13 shows a cross-sectional side view of the venturi inlet. [Figure 14] FIG. 14 shows a schematic diagram of a particulate burner system and a heat engine. [Figure 15] FIG. 15 shows a schematic diagram of a fuel atomizer. [Figure 16A] FIG. 16A shows the venturi arrangement of the particulate burner shown in FIGS. [Figure 16B] FIG. 16B shows an enlarged view of a portion of the particulate burner of FIG. 16A. [Figure 16C] FIG. 16C shows an enlarged view of a portion of the particulate burner of FIG. 16A. [Figure 16D] FIG. 16D shows an enlarged view of a portion of the particulate burner of FIG. 16A. [Figure 17] FIG. 17 shows the Stealth Ordinance Munitions Munition System. [Figure 18] FIG. 18 shows the Stealth Ordinance Munitions Ammunition System. [Figure 19A] FIG. 19A illustrates various configurations of the Stealth Act Munitions Munitions System. [Figure 19B] FIG. 19B illustrates various configurations of the Stealth Act Munitions Ammunition System. [Figure 19C] FIG. 19C illustrates various configurations of the Stealth Act Munitions Ammunition System. [Figure 19D] FIG. 19D illustrates various configurations of the Stealth Act Munitions Ammunition System. [Figure 20A] FIG. 20A shows an expanded view of a portion of the Stealth Act Munitions Ammunition System of FIGS. 19A-19D. [Figure 20B] FIG. 20B shows an expanded view of a portion of the Stealth Act Munitions Ammunition System of FIGS. 19A-19D. [Figure 20C]FIG. 20C shows an expanded view of a portion of the Stealth Act Munitions Ammunition System of FIGS. 19A-19D. [Figure 20D] FIG. 20D shows an expanded view of a portion of the Stealth Act Munitions Ammunition System of FIGS. 19A-19D. [Figure 21] FIG. 21 is a diagram illustrating thrust vector manipulation of the Stealth Act Munitions Munition System of FIGS. [Figure 22A] FIG. 22A shows a detailed schematic diagram of the Stealth Act Munitions Ammunition System of FIGS. [Figure 22B] FIG. 22B shows a detailed schematic diagram of the Stealth Ordinance Munitions Ammunition System of FIGS. [Figure 22C] FIG. 22C shows a detailed schematic diagram of the Stealth Act Munitions Ammunition System of FIGS. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Although specific configurations and examples are described below, the disclosure extends beyond the specifically disclosed configurations and / or uses, as well as obvious modifications and equivalents thereof. Thus, it is not intended that the scope of the disclosure should be limited by the specific configurations described below. Additionally, although the disclosure describes many configurations in connection with power generation or supercharging of an internal combustion engine, any configurations and modifications or equivalents thereof should not be limited to the above.

[0011] The first theorem of thermodynamics states that energy cannot be created or consumed; it can only be converted from one form of energy to another. Therefore, the total amount of energy in a closed system remains constant.

[0012] Energy forms have different valences. That is, heat does not flow from a cooler body to a warmer body, even if the total amount of energy stored in the body in the form of heat is equal. Conversely, the transfer of heat from a warmer body to a cooler body occurs spontaneously and automatically (Second Theorem of Thermodynamics). Thus, the heat of a warmer body has a higher value than the heat of a colder body. This heat can be converted, at least in part, into mechanical energy in a heat engine that utilizes the automatic flow of heat from a warmer body to a colder body. The proportion of mechanical energy obtained can be expressed as the ratio of the two temperatures according to the following formula:

number

[0013] This ratio can be called the efficiency of the Carnot process.

[0014] As disclosed herein, thermal energy can be converted to mechanical energy by a suction mechanism. Described herein are systems and devices for providing an energy charger to a system. For example, described herein are Venturi devices that form one or more flow-inducing vortices in a fluid (e.g., air, water, gas, etc.) flowing through the Venturi device. The one or more vortices can be generated in the Venturi device at a location where a secondary flow meets (e.g., mixes, merges) with the primary fluid flow through the Venturi device. The one or more vortices can create suction and suck or pull the primary flow into the Venturi device through an inlet. In some configurations, the suction and Venturi effect created by the fluid flow through the Venturi device can provide a high pressure charge to the system and maintain high pressure. In some configurations, the secondary fluid flow can include compressed fluid to aid in the combustion of particulate matter. In some configurations, the thruster system can be configured to attach to a munition to provide a more efficient and less traceable source of propulsion than conventional propulsion systems. The thrust system may include a Venturi device that compresses and expands a fluid to accelerate the charge.

[0015] Venturi device with forced induction FIG. 1A illustrates a cross-sectional view of an exemplary Venturi device 100, which may also be referred to as a vortex fusion charger or VFC. The Venturi device 100 may include a rotationally symmetric inner circumference, which in some configurations may include rotational symmetry about a central axis 112. The Venturi device 100 may be a tubular structure. The inner circumference of the Venturi device 100 may define a primary flow path, which may be an interior region, cavity, lumen, etc., that receives a primary flow of a fluid (e.g., water, gas, air, exhaust gas, etc.). In some configurations, the inner circumference of the Venturi device 100 may be circular. In some variations, the inner circumference may be other shapes, such as elliptical, polygonal, irregular, and / or other shapes. The inner circumference may define a flow path for the primary flow of the fluid in the direction of the arrow in FIG. 1. The inner circumference of the Venturi device 100 may define a cross-sectional flow area for the primary flow of the fluid, which may be circular. The inner circumference can vary such that the size and / or shape of the cross-sectional flow area varies along the length of the Venturi device 100. For example, the inner circumference of the Venturi device 100 can include inner diameters that assume different sizes along its length or central axis 112.

[0016] A primary flow of fluid may enter the Venturi device 100 through the inlet 102. The inlet 102 may be connected to a conduit (e.g., a tube) through which the primary flow may circulate. In some variations, the inlet 102 may be open to ambient air. The inner periphery of the inlet 102 may be circular. In some variations, the inner periphery of the inlet 102 may be elliptical, polygonal, irregular, and / or other. The inlet 102 may include a velocity stack, a trumpet shape, and / or an air horn shape, as shown in FIG. 1C. The inlet 102 may include a converging inner periphery. The inlet 102 may include a converging cross-sectional area. The inlet 102 may include an inner periphery that decreases in size in a flow direction of the primary flow. The inlet 102 may include an inner periphery that continuously decreases in size in a flow direction of the primary flow. The inlet 102 may include a cross-sectional area that decreases in size in a flow direction of the primary flow. The inlet 102 can include a cross-sectional area that continuously decreases in size in the flow direction of the primary flow. The inlet 102 can include a curved perimeter wall, as shown in Figure 1C. The inlet 102 can increase the velocity of the primary flow through the inlet 102 and decrease the pressure of the primary flow.

[0017] The primary flow of fluid may exit the venturi device 100 through the outlet 104. The outlet 104 may be located on the opposite side of the venturi device 100 as the inlet 102. The outlet 104 may be connected to a conduit (e.g., a tube) through which the primary flow may be circulated. In some variations, the outlet 104 may be connected to an engine as described herein to facilitate supercharging the engine with compressed gas. The inner periphery of the outlet 104 may be circular. In some variations, the inner periphery of the outlet 104 may be elliptical, polygonal, irregular, and / or other. The inner periphery of the outlet 104 may diverge. A cross-sectional flow area of ​​the outlet 104 may diverge in a flow direction of the primary flow. The inner periphery of the outlet 104 may increase in a flow direction of the primary flow. The inner periphery of the outlet 104 may continuously increase in a flow direction of the primary flow. The outlet 104 may include a cross-sectional area that increases in size in a flow direction of the primary stream. The outlet 104 may include a cross-sectional area that increases continuously in size in a flow direction of the primary stream. An inner periphery of the outlet 104 may be diverging. The outlet 104 may reduce a flow velocity of the primary stream through the outlet 104 and increase a pressure of the primary stream.

[0018] The Venturi device 100 can include a body (e.g., a tubular body) between the inlet 102 and the outlet 104. The primary flow path can flow through the body between the inlet 102 and the outlet 104. The body can include a converging section 106. The converging section 106 can increase the velocity of the primary fluid flowing through the converging section 106. The converging section 106 can reduce the pressure of the primary fluid flowing through the converging section 106. The inner periphery of the converging section 106 can be circular. In some variations, the inner periphery of the converging section 106 can be elliptical, polygonal, irregular, and / or other. The converging section 106 can include a converging inner periphery. The converging section 106 can include a converging cross-sectional flow area. The converging section 106 can include an inner periphery that decreases in size in the flow direction of the primary flow. The converging section 106 can include an inner periphery that continuously decreases in size in the flow direction of the primary flow. The converging section 106 may include a cross-sectional flow area that decreases in size in a flow direction of the primary flow. The converging section 106 may include a cross-sectional flow area that continuously decreases in size in a flow direction of the primary flow. The converging section 106 may include a flow area having a cone shape. The cross-sectional flow area of ​​the converging section 106 may decrease at a constant rate. The temperature of the primary flow flowing through the converging section 106 may decrease as a result of the increased flow velocity and reduced pressure.

[0019] The venturi device body 100 can include a throat 108, also referred to as a constriction. The throat 108 can be disposed between the converging section 106 and the diverging section 110. The throat 108 can include an inner circumference that is smaller than the inner circumferences of the converging section 106 and the diverging section 110. For example, the throat 108 can include a diameter that is smaller than the diameters of the converging section 106 and the diverging section 110. The throat 108 can include a cross-sectional flow area that is smaller than the converging section 106 and the diverging section 110. In some configurations, the throat 108 can be a junction between the converging section 106 and the diverging section 110. In some configurations, the throat 108 includes a length. In some configurations, the inner circumference of the throat 108 is an inflection point between the converging section 106 and the diverging section 108. In some variations, the converging section 106 converges to the throat 108 and then diverges to the diverging section 110.

[0020] The venturi device body 100 can include a bifurcation 110. The bifurcation 110 can be downstream of the inlet 102 and the convergence 106. The bifurcation 110 can be downstream of the throat 108. The bifurcation 110 can be disposed between the convergence 106 and the outlet 104, the second convergence 114, and / or the secondary input 120. The bifurcation 110 can reduce the velocity of the primary fluid flowing through the bifurcation 110. The bifurcation 110 can increase the pressure of the primary fluid flowing through the bifurcation 110. The inner periphery of the bifurcation 110 can be circular. In some variations, the inner periphery of the bifurcation 110 can be elliptical, polygonal, irregular, and / or other. The bifurcation 110 can include a diverging inner periphery. The bifurcation 110 can include a diverging cross-sectional flow area. The diverging portion 110 may include an inner circumference that increases in size in the flow direction of the primary flow. The diverging portion 110 may include an inner circumference that increases continuously in size in the flow direction of the primary flow. The diverging portion 110 may include a cross-sectional flow area that increases in size in the flow direction of the primary flow. The diverging portion 110 may include a cross-sectional flow area that increases continuously in size in the flow direction of the primary flow. The diverging portion 110 may include a flow area having a shape of a cone. The cross-sectional flow area of ​​the diverging portion 110 may decrease at a constant rate. The diverging portion 110 may be longer than the converging portion 106. The magnitude of the cross-sectional flow area of ​​the converging portion 106 may change more rapidly per unit length than the magnitude of the cross-sectional flow area of ​​the diverging portion 110. The angle of the periphery of the converging portion 106 relative to the central axis 112 and / or the flow direction of the primary flow may be greater than the angle of the periphery of the diverging portion 110 relative to the central axis 112 and / or the flow direction of the primary flow.

[0021] The flow of the primary stream through the converging section 106, the throat 108, and / or the diverging section 110 can create a Venturi effect, which can create a suction at the inlet 102. The flow of the primary stream through the converging section 106 and the throat 108 can create a Venturi effect, which can create a suction at the inlet 102. The flow of the primary stream through the converging section 106 can create a Venturi effect, which can create a suction at the inlet 102. The increase in velocity and decrease in pressure of the primary stream through the converging section 106 and / or the throat 108 can reduce the temperature of the primary stream such that thermal energy (e.g., heat) from the ambient environment outside the body 100 of the venturi device is transferred to the primary stream. In some variations, the body of the venturi device 100, or at least the converging section 106 and / or the throat 108, can include a conductive material (such as a metal) to facilitate efficient transfer of thermal energy through the body.

[0022] The venturi device body 100 can include a second convergent section 114. The second convergent section 114 can be downstream of the inlet 102, the convergent section 106, the throat 108, and the divergent section 110. The second convergent section 114 can be disposed between the divergent section 110, the secondary input section 120, and the outlet 104. The second convergent section 114 can increase the velocity of the primary flow flowing through the second convergent section 114. The second convergent section 114 can reduce the pressure of the primary fluid flowing through the second convergent section 114. The inner periphery of the second convergent section 114 can be circular. In some variations, the inner periphery of the second convergent section 114 can be elliptical, polygonal, irregular, and / or other.

[0023] The second converging section 114 may include a converging inner periphery. The second converging section 114 may include a converging cross-sectional flow area. The second converging section 114 may include an inner periphery that decreases in size in a flow direction of the primary flow. The second converging section 114 may include an inner periphery that continuously decreases in size in a flow direction of the primary flow. The second converging section 114 may include a cross-sectional flow area that decreases in size in a flow direction of the primary flow. The second converging section 114 may include a cross-sectional flow area that continuously decreases in size in a flow direction of the primary flow. The second converging section 114 may include a flow area having a cone shape. The cross-sectional flow area of ​​the second converging section 114, the converging section 106, and / or the diverging section 110 may change at a consistent rate per unit length. The angle of the periphery of the converging section 114 relative to the central axis 112 and / or flow direction of the primary flow may be greater than the angle of the periphery of the diverging section 110, the converging section 106, and / or the outlet 104 relative to the central axis 112 and / or flow direction of the primary flow.

[0024] The conduit 116, which may also be referred to as a tube, conduit, chamber, lumen, etc., may circulate a secondary flow of a fluid (e.g., water, gas, air, exhaust gas, etc.) to the venturi device 100. As described herein, the conduit 116 may recirculate a portion of the primary flow as a secondary flow back into the primary flow. The conduit 116 may connect to an annular chamber 118 in the body of the venturi device 100 to direct the secondary flow to the annular chamber 118. In some configurations, multiple conduits 116 may connect to the annular chamber 118 at multiple locations to direct the secondary flow to the annular chamber 118.

[0025] The body of the venturi device 100 may include an annular chamber 118. The annular chamber 118 may be ring-shaped. In some configurations, the annular chamber 118 may be torus-shaped. The annular chamber 118 may enclose a primary flow of fluid. The annular chamber 118 may encircle a central axis 112 of the venturi device 100. The annular chamber 118 may circumferentially enclose the primary flow of fluid. A secondary flow of fluid may extend throughout the annular chamber 118. A surface of the annular chamber 118 may include a Coanda surface or profile that facilitates the secondary flow of fluid extending throughout the annular chamber 118. A surface of the annular chamber 118 may be convex to facilitate the secondary flow of fluid extending throughout the annular chamber 118. The secondary flow may adhere (e.g., molecularly adhere) to a surface(s) of the annular chamber 118 to extend throughout the annular chamber 118.

[0026] The body of the venturi device 100 may include a secondary input 120. The secondary input 120 may be located downstream of the inlet 102, the convergence 106, the throat 108, the divergence 110, and / or the second convergence 114. The secondary input 120 may be located between the convergence 106, the throat 108, the divergence 110, and / or the second convergence 114 and the outlet 104. The secondary input 120 may include one or more flow paths from the annular chamber 120 to the primary flow and / or an interior region and / or a primary flow path of the venturi device 100 through which the primary flow passes. The secondary input 120 may be an annular passage, one or more openings, multiple openings, one or more slots, annular gaps, and / or annular gaps.

[0027] The secondary input 120 can surround the primary flow through the body of the venturi device 100. The secondary input 120 can circumferentially surround the primary flow through the body. The secondary input 120 can include one or more openings distributed circumferentially with respect to the flow path of the primary flow. The secondary input 120 can define an annular opening on an inner circumference of the body of the venturi device 100. The secondary input 120 can direct the secondary flow toward the primary flow relative to the flow direction of the primary flow and / or relative to the central axis 112 of the body of the venturi device 100. The angle can be 90 degrees in some variations. The angle can be between 60 degrees and 120 degrees in some configurations. The secondary input 120 can direct the secondary flow at least partially with respect to the flow direction of the primary flow. The introduction of the secondary flow by the secondary input 120 into the primary flow can cause a vortex, swirl(s), one or more vortices, and / or the like in the primary flow. The creation of a vortex can create a suction at the inlet 102 that draws the primary flow through the inlet 102 and into the venturi device 100. The suction of the primary flow into the venturi device 100 can cause an increase in velocity and a decrease in pressure of the primary flow through the convergence 106 and throat 108, which reduces the temperature of the primary flow through the convergence 106 and / or throat 108, and allows thermal energy (e.g., heat) from the ambient environment outside the body of the venturi device 100 to be transferred through the body to the primary flow, charging the primary flow with thermal energy. The temperature and pressure of the primary flow downstream of the throat 108 (e.g., at the divergence 110) can increase before exiting the outlet (H). The opening of the secondary input 120 into an interior region of the body (e.g., the primary flow path) can be smaller than the cross-sectional flow area of ​​the input from the conduit 116 to the annular chamber 118. The secondary input 120 can direct the secondary flow radially toward the primary flow of fluid and / or the central axis 112 of the body.

[0028] In some configurations, the body can include a check valve. The check valve can facilitate flow of the primary flow from the inlet 102 to the outlet 104 and can prevent and / or resist the primary flow from exiting the body via the inlet 102. In some configurations, the check valve can be a one-way check valve. In some configurations, the check valve can be a valved conduit. In some configurations, the check valve can be a fixed passive check valve. In some configurations, the check valve can include a main channel and a series of loops oriented to facilitate flow of the secondary flow towards the venturi device and resist flow away from the venturi device.

[0029] In some configurations, the check valve can be a Tesla valve. In some configurations, the check valve can be located at the convergence 106. In some configurations, the check valve can be located between the convergence 106 and the divergence 110. In some configurations, the check valve can be located at the divergence 110. In some configurations, the check valve can be located at the throat 108. In some configurations, the check valve can be located between the divergence 110 and the second convergence 114. In some configurations, the check valve can be located between the second convergence 114 and the outlet 104. In some configurations, the check valve can be located at the outlet 104. In some configurations, the check valve can be located at the inlet 102.

[0030] As described herein, the venturi device 100 can include three openings at locations 116, 104, and 106. In some variations, these three openings can be open to the environment. The annular chamber 118 can communicate with the interior region of the venturi device 100 (e.g., the primary flow path) through the annular gap 120. The inner region of the body can be tapered at location E, and thus has a smaller inner diameter than locations F and D. The taper (reducing inner diameter) from location F to location E and the extension (expanding inner diameter) from location E to location D can be continuous, such as a cone shape. When the secondary flow is introduced into the opening 116, the secondary flow enters the annular chamber 118 and is distributed therein radially within the annular chamber, which can include the entirety of the annular chamber. From the annular chamber 118, the secondary flow enters the interior region of the venturi device body 100 through the secondary input 120, where it creates a vortex and creates a suction effect at the inlet 102. As a result, the primary flow is drawn in through the inlet 102 and expelled towards the outlet 104. At point E (e.g., throat or constriction 108), the flow velocity of the drawn in air increases due to the Venturi effect. The combination of the suction effect and the Venturi effect allows the temperature in front of the vortex to be lowered, and heat from the surroundings is absorbed by the primary flow, charging it with energy from the surrounding environment.

[0031] In some configurations, the rotationally symmetric design of the Venturi device 100 is not used and the Venturi effect may not be created. In some configurations, a body may be used that creates a flow-induced vortex formation with suction on one side of the vortex and discharge of the flowable medium surrounding the vortex on the other side of the vortex. The flowable medium sucked in during the suction process may be cooled. The sucked in cooled flowable medium may absorb heat (e.g., thermal energy) from the environment, for example, resulting in an increase in the internal energy of the flowable medium. Induction of the flowable medium through a heat exchanger may also be used.

[0032] Figure 2 shows, for ease of illustration, a simplified schematic diagram of the Venturi device 100 of Figure 1A. Reference numerals 116, 102 and 106 in Figure 2 correspond to the openings at locations 116, 102 and 106, respectively, in Figure 1A. Stated differently, inlet 102 corresponds to inlet 102, conduit 116 corresponds to 116, and outlet 104 corresponds to outlet 104.

[0033] Fine particle burner FIG. 3 illustrates a particulate burner system or NOx particulate burner (NPB) for combustion of fuel exhaust by-products herein. Conventional cyclone burners (also called "cyclic burners") suffer from poor boundary layer formation along the inner wall because the boundary layer may disappear before the fuel source is completely burned. The fluid flow may separate from the boundary layer because the energy inserted into the burner is too low to maintain the rotational force of the fluid or the momentum of the fluid cannot be carried to the edge of the combustion chamber. The particulate burner system according to the present disclosure can improve the prevention of boundary layer separation by forcing the fluid moving from the side wall opening into the boundary layer, resulting in more stable and efficient combustion.

[0034] As shown in FIGS. 3-6, the particulate burner system or fuel exhaust burner system 200 can include a housing 202 that forms a combustion chamber 204. The housing 202 and related components discussed herein can be the particulate burner, fuel exhaust burner, or fuel burner of the particulate burner system 200 discussed herein. The housing 202 can be disposed and / or connected to a flare stack (e.g., discussed herein as a fuel supply system 205). The particulate burner system 200 can utilize existing air and gas systems for various flare stack and flue design applications. The combustion chamber 204 can be of a centrifugal type that uses centrifugal force to flow fluid along a surface or boundary layer of the housing 202.

[0035] The housing 202 may include a bottom plate 206 having a circular bottom opening 208 for allowing a burner to inject a fuel and air mixture from a fuel delivery system 205 along a fuel path 201 into the combustion chamber, and a top plate 210 having a circular top opening 212 for exhausting fuel exhaust from the combustion chamber through an exhaust path 237 through a circular top opening 212 that may be aligned with the circular bottom opening 208 along a central axis 207. Fuel may be injected into the housing 202 along the fuel path 201. In some configurations, a funnel 226 may be connected to the top plate 210 above the circular top opening 212, as shown in FIG. 3. The funnel 226 may direct exhaust from the circular top opening 212 through the funnel 226 to a top periphery of the top plate 210 to facilitate retention of heat within the top plate 210 due to combustion of fuel along the top plate 210. Additionally or alternatively, the funnel 226 may have a cross-sectional flow area that narrows in the direction of flow of the exhaust from the circular top opening 212.

[0036] As shown in FIG. 14, the exhaust exiting through the particulate burner system 200, and particularly through the top plate 210, can then be directed to a heat engine 240 to generate work. Energy from the exhaust gases 1 can be used to charge the heat engine 240, which converts thermal energy into mechanical energy. When fuel is introduced into the system via stream 2 and optional stream 4, heat from the combustion of the fuel is transferred through stream 4. Air stream 3 can further assist the combustion process. The particulate burner system 200 can be constructed of 316 stainless steel construction with no moving parts, limiting required maintenance.

[0037] Fuel entering through the circular bottom opening 208 can be premixed with air upstream of the circular bottom opening 208. The bottom plate can have a width between 1 inch and 24 inches, between 3 inches and 18 inches, between 6 inches and 12 inches, between 7 inches and 11 inches, or between 8 inches and 10 inches. The bottom opening can have a width between 0.5 inches and 3.5 inches, between 1 inch and 3 inches, between 1.5 inches and 2.5 inches, or between 1.75 inches and 2.25 inches. The particulate burner housing 202 can also be modified to include multiple fuel burners and / or rack assemblies 209. Vent ports 214 can be located along the perimeter of the bottom opening to allow for control of airflow into the combustion chamber. The vent ports 214 can be curved to extend about a central axis following the curvature of the circular bottom opening 208. In some configurations, the vacuum created by the venturi device 300 can draw the pulverized solid fuel dust through a circular bottom opening 208 in the bottom plate 206, and a mesh screen can be used to meter the pulverized solid fuel.

[0038] The circular sidewall 216 may extend between and be connected to both the bottom and top plates 206, 210 about a central axis 207. The circular sidewall 216 may have a thickness between 0.1 inches and 1 inch, between 0.25 inches and 0.75 inches, or between 0.3 inches and 0.5 inches. The sidewall may have a height between 1 inch and 5 inches, between 1.5 inches and 4.5 inches, between 2 inches and 4 inches, between 2.5 inches and 3.5 inches, or between 2.75 inches and 3.25 inches. The sidewall openings 218 may be located at the openings in the sidewall 216 and are used to direct air into the combustion chamber tangentially to the inner periphery or surface 220 of the circular sidewall 216. The sidewall openings 218 may direct the incoming fluid centrifugally into the combustion chamber 204. The inner periphery 220 may exert a centrifugal force on the air entering through the sidewall openings 218, causing the air to move in a circular direction along the inner periphery 220 and around the combustion chamber 204. The flow of air may create a vortex vacuum that draws fuel from the circular bottom opening 208 toward the inner periphery 220.

[0039] Additionally or alternatively, the sidewall openings 218 may be positioned tangentially to the inner periphery 220 to allow incoming fluid to flow in a direction along the periphery of the circular sidewall 216 to entrain air and fuel from the circular bottom opening 208 into the fluid moving along the inner periphery 220. Additionally or alternatively, the flow of fuel from the circular bottom opening 208 may entrain additional air into the system through the vent ports 214 in the bottom plate 206. The vent ports 214 may be adjusted to increase or decrease the amount of air entrained into the system. Also, the curvature of the vent ports 214 may help direct the air towards specific fins 228 and / or in a specific direction for the air to enter the combustion chamber 204. One or more vent ports 214 may be closed or open depending on the fluid dynamics within the combustion chamber 204. In some configurations, a line 221 extending from the periphery of the sidewall opening 218 along a central axis 223 of the sidewall opening 218 may be tangential to the inner circumference 220 of the circular sidewall 216. As shown in Figures 3 and 4, the sidewall opening 218 may be formed on the input side of the combustion chamber 204 and connected to a venturi device 300 to provide the incoming charge. The sidewall opening may have a height between 0.5 inches and 3.5 inches, between 1 inch and 3 inches, between 1.5 inches and 2.5 inches, or between 1.75 inches and 2.25 inches.

[0040] As shown in FIG. 7, a deflector or deflector 222 may be positioned within the combustion chamber 204 at or near the opening of the sidewall opening 218 to moderate the flow of fuel from the circular bottom opening 208 to the sidewall opening 218 and / or to moderate the flow of air from the sidewall opening 218 to the circular bottom opening 208. Additionally or alternatively, the deflector 22 may help prevent pressure flashback and guide the intake charge through the venturi device 300. Flashback may occur when the combustion chamber 204 is lit and the venturi device 300 is not generating flow to the combustion chamber 204. The deflector 22 may be connected to the bottom plate 206 and / or top plate 210 and extend axially along the central axis 207 and along the circular bottom opening 208. The perimeter of the deflector 222 can be at least partially within the perimeter of the sidewall opening 218 when the perimeter of the deflector 222 is projected radially along a path from the central axis 207 to the perimeter of the sidewall opening 218. In some configurations, the deflector can be removable from the combustion chamber 204, as shown in FIG.

[0041] As shown in Figures 3, 4, 7-10, and 12, the combustion chamber 204 may include a spiral runner 224 inside the combustion chamber 204 that provides an additional boundary layer along the fuel fluid path 233 for the fuel to interact with the flame as the fuel is drawn through the combustion chamber 204 and exits the circular top opening 212. The high velocity flow 235 from the venturi device 300 may generate a vortex along the combustion path 231, creating a vacuum and drawing in the fuel coming through the bottom opening 208 along the fuel fluid path 233. The spiral runner 224 may be comprised of a number of fins, shovels, or blades 228 disposed within the combustion chamber 204 that have a curved shape in the fluid flow direction 229 such that a distal edge 228d extends in the fluid flow direction 229 relative to a proximal edge 228a relative to the circular bottom opening 208. The fuel may flow, at least in part, along fuel fluid paths 233 formed by the Coanda surfaces of the fins 228 discussed herein, where the Coanda effect forms the fuel fluid paths 233, causing the fuel to flow along the surfaces of the fins 228.

[0042] As shown in FIGS. 7-9, each of the fins 228 can have an edge 228a closest to the circular bottom opening 208 relative to the circular inner periphery 220. The fins 228 can have a thickness 228b closest to the circular bottom opening 208 and a second thickness 228c closest to the inner periphery 220 of the sidewall 216. The knuckle thickness 228b can be thicker than the second thickness 228c. The first and second thicknesses 228b, 228c can help define a camber for the fin 228, which can affect the velocity of the fluid stream 233 as the fluid contacts the fin 228. Different cambers can increase or decrease the adhesion of the fluid to the fin, as well as the velocity of the fluid stream 233 as the fluid passes through the fin 228. The fins 228 may further include a Coanda surface and / or a Venturi effect in the fluid path 233 that helps move fuel along the fins 228 (and their surfaces) from the bottom opening 208 to a boundary layer at the inner circumferential surface 220 .

[0043] The fins 228 can have a variety of shapes depending on a variety of factors. The fins 228 can have a teardrop shape, a shape with relatively flat sides away from the fluid flow passages 229 and circular sides in the direction of the fluid flow passages 229, an elliptical shape with relatively symmetric camber on each side of the fin 228, etc. The concave shape and / or sides of the fins 228 can face away from the fluid flow passages 229 to guide fluid along the length of the fin 228 in the direction of the fluid flow passages 229. The convex sides and / or shapes of the fins 228 can face towards the fluid flow passages 299 to direct fluid in the direction of the inner circumferential surface 220. The fluid flow passages 299 can follow a corresponding curved concave or convex path along the surface of the fin 228 due, at least in part, to the Coanda effect and the associated surfaces of the fins discussed herein. The fin 228 can have connection points along the side closest to the base plate 206 and / or hub 230 for attaching the fin 228 to the base plate 206 and / or hub 230. In some configurations, the fin 228 can have connection points along a proximal edge 228a for connecting the fin 228 to the protrusion 234.

[0044] The fins 228 may be connected to the bottom plate 206 of the combustion chamber 204. In some configurations, the fins 228 may be connected to a hub 230, which may in turn be connected to a fastener opening 232 in the bottom plate 206 (shown in FIGS. 5-7). The hub 230 may be removable from the combustion chamber 204 such that one or more hubs having different fin configurations are interchangeable. The different fin configurations may correspond to air / fuel mixture characteristics and / or the use of solid or gaseous fuel fluids.

[0045] In some configurations, the fins 228 can be attached to a hub 230 disposed around a protrusion 234 of the bottom plate opening 208, as shown in FIG. 11. FIG. 11 also shows another configuration without the deflector 222. Instead of including the deflector 222, the one or more first fins F1 can be shorter than the remaining fins 228. The one or more first fins F1 can also be furthest from the boundary layer along the inner circumferential surface 220 and the top plate 210. The first fins F1 can allow the fluid to pass over the one or more first fins F1 without impeding the high velocity flow. In some configurations, the spiral runner 224 can provide at least two additional boundary layers, at least five additional boundary layers, at least ten additional boundary layers, or at least twenty additional boundary layers for the combustion of the fuel along the boundary layer. At the location of the deflector 22, a number of fins 228 can be removed. In some configurations, the deflector 222 can be flat. Additionally or alternatively, the deflector 222 may be curved to follow at least a first radial extent of the first fin F1, which may be smaller than a second radial extent of the last fin.

[0046] As shown in FIGS. 10-12, the plurality of fins 228 may extend radially from the circular bottom opening 208 toward the inner periphery 220 in the direction of the moving air 229 within the combustion chamber 204. A combustion flow passage 231, in which combustion of fuel occurs, may extend along the inner periphery 220. A first radial extent R1 from the central axis 207 of a first fin F1 of the plurality of fins 228 may be smaller than a second radial extent RL from the central axis 207 of a last fin of the plurality of fins. Also, the first axial extent R1 of the first fin F1 may be smaller than a second axial extent RL of a last fin FL along the central axis 207. The first fin F1 may be positioned adjacent and / or closest to an inlet path of the air 235 coming from the sidewall opening 218 and may be positioned downstream of the deflector 222 along the airflow direction 229. The last fin FL may be positioned adjacent and upstream of the deflector 222 in the direction of the fluid flow 229.

[0047] As shown in FIG. 10, the first axial extent A1 of the first fin F1 along the central axis 207 can be smaller than the second axial extent AL of the last fin FL along the central axis 207. Sizing the first fin F1 in this configuration can reduce back pressure or cessation of fluid flow coming from the sidewall opening 218. The radial extent of the fin between the first fin F1 and the last fin FL can be longer relative to the first radial extent R1 of the first fin F1 to further direct the fuel toward the inner circumference 220 of the circular sidewall 216, drawing the fuel toward the inner circumference 220. Directing the fuel along the fluid path 233 toward the inner circumference 220 can combust the fuel exhaust products along the sidewall 216 along the combustion flow path 231.

[0048] In some configurations, the first fin F1 may be the smallest and / or shortest of the fins 228. Also, the last fin FL may be the tallest and / or longest compared to the other fins 228. The radial extent R of the multiple fins may increase toward the inner circumference along the airflow 229 direction to direct the fuel along the fluid path 233 toward the inner circumference 220 and entrain the fuel. In some configurations, the radial extent R may gradually increase toward the inner circumference 220 in the airflow direction. In some configurations, the radial extent R of the two or more first fins may be the shortest compared to the other fins. The two or more shortest fins include the first fin F1. In some configurations, the radial extent R of the two or more last fins may be the longest compared to the other fins. The two or more longest fins include the last fin FL.

[0049] The fins can be positioned such that the gap between the end of the fin closest to the inner periphery and the inner periphery is 0.1 inches to 1 inch, 0.25 inches to 0.75 inches, or 0.4 inches to 0.6 inches. As the fluid contacts the fins 228 along the path 233, at least a portion of the fluid is redirected toward the boundary layer, improving combustion efficiency and completion. Increasing the size of the fins 228 and / or decreasing the gap between the sidewall 216 and the top plate 210 also increases the velocity of the fluid. In some configurations, the radial extent R of the fins 228 can be the same along the airflow direction toward the inner periphery 220 after the first fin F1.

[0050] In some configurations, the first axial length A1 of the first fin F1 may be shortest compared to the other fins 228. In some configurations, the second axial length AL of the last fin FL may be longest compared to the other fins 228. The height of the fins may be 1 inch to 4 inches, 1.5 inches to 3.5 inches, 2 inches to 3 inches, or 2.25 inches to 2.75 inches. In some configurations, the axial extent A of the fins 228 increases toward the top plate along the direction of air flow to direct the fuel and / or air toward the inner circumference 220. Also, by angling the fins 228 toward the inner circumference 220 and closing the gap toward the top plate 210, the air flow is more effectively directed toward the inner circumference 220 and improves fuel entrainment along the fins 228. The axial extent A of the fins 228 may gradually increase toward the top plate 210 along the fluid flow passages 229. In some configurations, the axial extent A of the two or more first fins may be shortest compared to the other fins of the plurality of fins 228. The two or more first fins may include a first fin F1.

[0051] Additionally or alternatively, the axial extent A of the two or more last fins may be the longest relative to the other fins 228, including the last fin FL of the plurality of fins 228. In some configurations, the axial extent of the plurality of fins may be the same toward the top plate after the first fin along the airflow direction. In some configurations, the axial extent A of the other fins of the plurality of fins 228 is longer relative to the first axial extent A1 of the first fin F1 to direct fuel toward the inner circumference 220 of the sidewall 216. A line 225 along the radial extent of the plurality of fins from the central axis 207 may extend to the outside of the periphery of the sidewall opening 218 for each of the plurality of fins 228. In some configurations, the axial extent A of the fin 228 may increase while the radial length R remains constant.

[0052] 10 and 12 show the fluid dynamics of the particulate burner system 200 for illustration. As the fuel and air mixture enters the circular bottom opening 208 and around the deflector plate 222, the fuel and air mixture can travel along the fluid path 233 and along the surface of the fins 228 towards the combustion path 231. The fuel and air mixture can travel along the combustion path 231 over the deflector plate 222 as the vacuum in the combustion chamber draws the fuel and air mixture to the inner periphery 220. The fuel and air mixture can travel within the air passage 229 until the burned fuel and air mixture is exhausted from the circular top opening 212 along the exhaust path 237. As the air-fuel mixture travels along the combustion path 231, the fuel and air mixture can be compressed as the gap between the fins 228 and the top plate 210 and inner periphery 220 decreases. The intake charge from the venturi device 300 can enter the sidewall opening 218 centrifugally along the fluid flow path 235 in the direction of the fluid flow path 229. Each flow passage 233 between the fins 228 can separate and transport fuel to the combustion path 231. The fins 228 can divide the flow of fuel fluid into various compression zones along the flow passages 233 between the fins 228, facilitating the fuel to travel along the Coanda surfaces of the fins 228 toward the inner periphery 220 and burn more efficiently (including combustion of particulates). Additionally or alternatively, combustion of the fuel and particulates can occur along the fluid flow passages 233 along the fins 228.

[0053] 4 and 13 show a venturi inlet 236 of the venturi device 300, which may be attached to and / or in fluid communication with the sidewall opening inlet 218 to provide a source of high pressure fluid to the combustion chamber 204. In some configurations, the venturi inlet 236 may be connected to the sidewall opening 218 by a tube, conduit, or the like. In some configurations, the venturi device 300 may be fluidly and directly connected to the sidewall opening 218. The venturi device inlet 236 may be connected to a compressed fluid source 238 that provides a primary flow to the venturi device 300. The compressed fluid source 238 and / or a conduit 316 emerging from the fuel supply system 205 may be connected to a secondary input 320 of the venturi device 300 to create a suction effect that draws the primary flow into the venturi device 300.

[0054] In some configurations, the secondary flow may include fuel injected into the secondary flow upstream of the secondary input 320. The fuel injected into the secondary flow may be the same type or different than the fuel injected into the circular bottom opening 208 of the combustion chamber 204. In some configurations, the venturi device 300 is also used to mix the fuel and air before the fluid enters the combustion chamber. The fuel supply system 205 may utilize the Coanda effect to supply fuel to the sidewall opening 218 via the annular chamber 318 connected to the venturi device 300. The fluid (e.g., air and / or fuel) is supplied to the combustion chamber 204 via the sidewall opening 218 at a specific velocity and flow rate (without assistance) using hybrid fluid aerodynamics and is then mixed with the fuel from the fuel supply system 205. The fuel supply system 205 may premix a predetermined and / or desired fuel-to-air ratio before supplying to the combustion chamber 204. The flow rate and velocity of air supplied to the combustion chamber 204 through the sidewall openings 218 may be calculated to provide sufficient oxygen to the combustion chamber 204 for substantially clean combustion of the fuel supplied by the fuel supply system 205. This provides kinetic energy to the system 200 and introduces turbulence, thereby providing proper mixing of the air and fuel.

[0055] The fuel can be ignited and the particulate burner system 200 can be allowed to warm up for a suitable period of time. The velocity and / or flow rate of the air-fuel mixture can be adjusted to achieve a desired temperature and / or burn rate. Once the particulate burner system 200 reaches a peak temperature and / or burn operating rate, the particulate burner system 200 can burn exhaust by-products injected into the combustion system. The centrifugal housing shape of the combustion chamber 204 allows the flame in the particulate burner to be recirculated and recycled, promoting complete combustion of the injected fuel. By maintaining high heat in the housing 202, particulate material can be burned cleanly. For example, an acetylene torch requires a temperature of 5500°C to operate, which causes long-term and short-term thermal damage to the torch. Based on the type of fuel and various implementations, the minimum operating temperature that can produce a clean burn may be around 800°C. The dimensions of the particulate burner system 200 can vary depending on the intended application. The width can be larger than the height (ranging from 2:1 to 4:1). Height can range from 6 inches to 6 feet depending on the application.

[0056] The particulate burner system 200 can burn several different types of fuels with minor modifications to the manufacturing and operating process. In some configurations, the primary fuel source that may be used to achieve a clean burn can include coke, fuel oil, and / or bunker oil. Besides the fuel source, the particulate burner system 200 can reduce and / or eliminate harmful emissions. In some configurations, the emissions can be converted into usable materials. The particulates can be disposed of, while in some configurations, the particulates can be collected. For example, when burning used bitumen, the particulate burner can collect vanadium oxide. As shown in FIG. 4, the particulate burner system 200 can include a collector 260 that can store the by-products of the combustion process. The collector can have a chute 262 attached to the combustion chamber at a bottom plate at one end and a storage vessel 264 at the opposite end. The bottom plate is provided with a chute opening that is connected to the chute. As the fluid moves around the combustion chamber, the by-products can accumulate or move to a lower pressure portion of the combustion chamber depending on the density of the remaining fluid. The by-products are then conveyed through tubes to a storage vessel 264. In some configurations, the combustion chamber may have multiple collection screens and tubes corresponding to particular by-products. By-products captured on one of the collection screens may be deposited in a storage vessel 264 for that by-product. In some configurations, when the combustion chamber is burning bitumen, vanadium oxide may become a non-combustible particle.

[0057] The housing design allows for openings on both sides of the combustion chamber 204 (circular bottom opening 208 and circular top opening 212) by utilizing a veined path for combustion. This design allows a new dimension in utilizing the pressure differential of the flame vortex to create a vacuum for flare gas stacks and other flue-based systems that vent harmful pollutants into the atmosphere. The housing design increases the overall system efficiency and reduces the energy costs of the existing foundation structure, thus reducing the real estate footprint for future designs and significantly reducing overall maintenance costs.

[0058] As shown in FIGS. 4 and 15, the venturi device 300 of the particulate burner system 200 can be connected and / or in fluid communication with the fuel atomizer 242 to mix the fuel with the primary flow passing through the venturi device 300. The fuel atomizer 242 can be in fluid communication with a secondary input upstream of the secondary input 320. Atomization of the fuel can be achieved by using an ultrasonic resonator using high pressure and / or vibration and / or electricity. The particulate burner system 200 can include an ultrasonic resonator atomizer 242 that uses high frequency vibrations applied to a distribution plate 244, which vibrate a piezoelectric ring and / or transducer 246, causing an electrostatic shock. The compressed piezoelectric device, such as when subjected to vibration, can release an electric charge. The factor that shapes the droplet size of the fuel is the frequency of the vibration.

[0059] Ultrasonic resonance atomizers can operate with solid fuels (e.g., liquids such as diesel, gasoline, kerosene, etc.) with high efficiency. By atomizing the incoming fuel fluid, the fuel can be burned more efficiently and thoroughly. The ultrasonic resonance atomizer 242 can be fitted to the sidewall input 218 and can function in other configurations as well.

[0060] The ultrasonic resonance atomizer 242 may include a distribution ring 244 (also referred to herein as a "distribution plate"), an RF frequency generator or oscillator 248 that vibrates the distribution ring 244, a mesh screen 250 having microtapered apertures 251 disposed along a surface of the mesh screen 250, one or more piezoelectric ceramic rings 246 stacked on top of the distribution ring 244 as an atomizer and / or connected to the distribution ring 244 to discharge electricity into a fluid stream passing through the mesh screen 250, one or more copper washers 252 disposed between each piezoelectric ceramic ring 246, and a controller 254 that controls the RF frequency generator 248. The mesh screen 250 may be disposed in the center of the distribution plate 244 and / or the piezoelectric ring 246. The RF frequency generator 248 may be powered using a 120 volt and / or 110 volt system. The RF frequency generator 248 may be powered using a 120 volt system. An RF frequency generator 248 is connected to the distribution plate 244 with negative and positive connections to apply a frequency to the distribution ring 244, causing it to vibrate and therefore the piezoelectric ceramic ring 246. Depending on the frequency applied to the distribution ring 244 and the piezoelectric ceramic ring 246, the atomization rate increases or decreases depending on the frequency applied. The mesh screen 250 acts like a nozzle to disperse the fuel source for atomization.

[0061] The controller 254 can switch the oscillator 248 between a low resonant frequency and a high resonant frequency by a switchable excitation circuit. The low resonant frequency is for a cold start condition of the system. The high resonant frequency is for a hot operating condition of the system. The controller 254 can be connected to a temperature sensor or other sensor in the system that determines the operating condition of the system, such as the temperature of the housing 202. The controller 254 can switch between the low resonant frequency and the high resonant frequency based on a predetermined threshold, such as a predetermined temperature threshold, to increase system efficiency and minimize system start-up time from a cold to a hot operating condition. The excitation circuit can represent a phase-locked loop circuit with a voltage controlled oscillator and a frequency filter that switches between a low resonant excitation frequency or a high resonant excitation frequency.

[0062] The controller 254 can be part of a computer system that operates the devices and systems described herein. The computer system includes a processor or controller, a main memory, storage, a bus, and an input. The processor is one or more processors. The processor executes instructions communicated to the processor via the main memory. The main memory sends instructions to the processor. The main memory is also connected to the bus. The main memory can communicate with other components of the computer system via the bus. Instructions for the computer system are sent to the main memory via the bus. These instructions are executed by the processor. The executed instructions are returned to the main memory and distributed to other components of the computer system. The storage can hold large amounts of data and can hold that data even while the computer system is not powered. The storage is connected to the bus and can communicate the data it holds to the main memory via the bus. The sensor can communicate with the computer system via an input that receives data from the sensor related to the operation of the system described herein.

[0063] A typical fuel atomizer produces a fuel mist by applying high pressure in front of the atomizing nozzle. The pressure can range from 10 to 20 bar. For the nozzle bore, increasing pressure increases the fuel throughput and heating power. For safety reasons and the risk of clogging due to dirt, the nozzle diameter cannot be reduced. As a result, the power limit of a pressure atomizer burner is reduced to around 15 kW.

[0064] In the case of ultrasonic atomizing burners, an ultrasonic atomizer can be used with an ultrasonic oscillator equipped with an ultrasonic transducer coupled to an amplitude converter. The amplitude converter can be provided on the atomizer plate or on the free end of the transducer equipped with the atomizer plate. The surface of the atomizer plate can be supplied with the liquid fuel to be sprayed through holes or channels. These holes or channels can be large in size, so that there is no risk of them becoming clogged with dirt. The transfer of the fuel supply can be done through a metering pump that operates almost without back pressure, which is simpler and cheaper than a high-pressure pump with a pressure regulator, which is necessary for a pressure atomizer.

[0065] When spraying solid fuel, the piezoelectric ring 246 also vibrates when a resonant frequency is applied to the distribution plate 244. As the piezoelectric ring 246 vibrates, it discharges a static charge. The static charge destabilizes the molecular structure of the fluid flowing through the mesh screen 250, making it more susceptible to complete combustion. The resonant atomizer 242 may have one or more stacked piezoelectric rings 246. A copper ring 252 (also referred to herein as a "copper washer") is placed between each piezoelectric ring 246 (and the distribution plate 244 assembly) to act as a damper and prevent the piezoelectric rings 246 from vibrating against each other. The copper ring 252 may inhibit or prevent transmission or resonance between the piezoelectric rings 246.

[0066] In some configurations, the particulate burner system 200 can also have the ability to ionize the incoming fuel stream to improve the overall combustibility of low yield waste gases such as ammonia (NH3) gas, allowing for more efficient and wider industrial applications using the fuel or gas ionizer 256. Additionally, the ionization function can limit the primer fuel required for ignition and sustaining temperatures. Due to the physical interaction of the ionization with the pressurized gas stream, the particulate burner system 200 can utilize NH3 gas, which can be used in place of or in conjunction with similar hydrogen-based primer reaction systems. The gas ionizer 256 can include a structure similar to the solid fuel atomizer 242. The gas ionizer 256, which is in fluid communication with the secondary input 320, can include a distribution plate 244 and one or more piezoelectric rings 246 connected to the distribution plate 244.

[0067] The piezoelectric ring 246 can ionize fuel passing through the openings in the piezoelectric ring 246 by discharging an electric charge into the fuel path. In some configurations, the gas ionizer 256 can include up to 10 piezoelectric rings, up to 8 piezoelectric rings, up to 5 piezoelectric rings, up to 4 piezoelectric rings, up to 2, or 1 piezoelectric ring. The number of piezoelectric rings is based on a system configuration that allows for ionization while mitigating pre-ignition of the gas. The number of piezoelectric rings is based on achieving a desired molecular destabilization of the fuel.

[0068] A copper ring 252 can be placed between each pair of piezoelectric rings 246, similar to the configuration of the solid fuel atomizer 242. The copper ring 252 can dampen resonance between the piezoelectric rings 246. In some configurations, the gas ionizer 256 can include one or more dispersion plates 244 connected to one or more piezoelectric rings 246. Rather than using a resonant frequency generator to induce vibrations to atomize the fluid, a static pressure is generated between one or more layers of the mesh screen 250 to generate static electricity, destabilizing the gas and lowering the required ignition energy. A first mesh 250a can be attached to the ring opening of the first piezoelectric device 246a, and a mesh of a second screen 250b can be attached to the second ring opening of the second piezoelectric device 246b, etc.

[0069] Additionally or alternatively, the first mesh screen 250a can have a plurality of mesh openings with a larger cross-sectional area than the second plurality of mesh openings on the second mesh screen 250b. By reducing the cross-sectional area, the flow of fuel through the first mesh screen 250a and the second mesh screen 250b creates a pressure difference between the fuel flowing downstream of the first mesh screen 250a and the fuel flowing upstream of the second mesh screen 250b. The fuel flowing downstream of the second mesh screen 250b can resonate at least one of the piezoelectric rings 246 of the fuel ionizer 256 and discharge an electric charge into the fuel path. The mesh screen 250 can include a finer mesh relative to the input gas density. Energy from a compression cylinder can inject gas through one or more openings in the mesh screen 250 and one or more piezoelectric ceramic rings 246. The gas cylinder can be plugged into a reservoir 258 with appropriate gas fittings. A low pressure regulator can be attached to the gas cylinder to manage the flow rate of gas to be ionized. A high pressure regulator can also be installed for larger capacity systems. The more times the fluid passes through the mesh screen 250, the more time the fluid has to interact with the static discharge and become ionized.

[0070] Particulate burners may be forced-induced swirl burners operating on the air and fuel lines of an existing flare stack. The system utilizes hybrid fluid aerodynamics and circular geometry engineering to create three-dimensional efficiency, resulting in virtually complete combustion fuel burn. Three-dimensional systems contrast with the current inefficient two-dimensional approach, which involves high levels of particulate matter and harmful compartmentalized gas emissions.

[0071] The particulate burner can be bolted onto the existing flare gas stack pipe after removing the existing pilot burner system. The combustion chamber design and non-mechanical forced induction system allow for more efficient utilization of the existing energy in the system without requiring additional energy input. The flame vortex formed can rotate in the cone-shaped exhaust outlet. As the flame heats up, it can recycle waste gases before being exhausted into the atmosphere, resulting in a clear blue flame with minimal pollutants or particulate matter at the flare stack exit.

[0072] The suction effect of the vortex formed in the system chamber housing also creates a vacuum above the stack, which improves gas flow through the stack, increasing efficiency. Venting gas faster without adding an electric pumping mechanism increases the net productivity gain for current cost conversion. Venting gas can also reduce the size of new stack builds, resulting in significant savings in material costs, maintenance, and space.

[0073] The configuration of the Venturi device 300 is shown diagrammatically in Figures 16A-16D. Figure 16A shows a cross-sectional view of the Venturi device 300. The Venturi device 300 can have a similar layout to the Venturi device 100, but modified as shown below. The distinct locations of the axes are indicated by the arrows and the letters B, C, D, E, and F. As previously mentioned, gas can be introduced into the interior of the Venturi device 300 from the conduit 316 through the secondary input 320, which can include the annular chamber 318 and the ring gap 330. In some configurations, once the selected fluid is identified, the ring gap 330 can be fixed. In some cases, no field adjustment is required to adjust the ring gap 330. In some configurations, a tapered machine union can be applied to the ring gap 330 to seal the Venturi device 300. In the D region of the charging element (e.g., the Venturi device 300), a vortex can form, as described with reference to Figure 1A. This vortex creates a vacuum at the inlet 302 (location F), which results in ambient air being drawn into the Venturi device 300 via the inlet 302 and throat 308 (e.g., a constriction).

[0074] The air is compressed on the opposite side of the vortex (direction C), so the region of the pipe between B and E may be referred to as the compression chamber. In sizing the Venturi device 300, the volume of the annular chamber 318 may be equal to the product of the circumference and the area of ​​the ring gap 330. The annular chamber 318 may be configured to receive and direct the secondary flow to the secondary input 320. In some configurations, the Venturi device 300 may include a single point annular chamber 318 for compressible fluid. In some configurations, the annular chamber 318 may include multiple uniform chamber inputs for incompressible fluid. In some configurations, the annular chamber 318 may surround the primary flow within the body 311 of the Venturi device 300. The annular chamber 318 may include a Coanda surface (configured to distribute the incoming secondary flow throughout the annular chamber 318 by the secondary fluid flowing along the Coanda surface).

[0075] The secondary input 320 may be an annular passage, one or more openings, a plurality of openings, one or more slots, an annular gap, and / or a ring gap fluidly connected to the annular chamber 318. The annular passage 331 may be configured to direct the secondary flow from the annular passage 331 to the primary flow. The ambient air and exhaust gases are merged at a location corresponding to B and forced into the combustion chamber by passing through the outlet 304 at location C. The diameter of the outlet 304 may be similar and / or equal to the distance between the inlet 302 and the throat 308, creating a ratio that determines the size of the venturi device 300. Also, the cross-sectional area of ​​the outlet 304 may be smaller than the cross-sectional area of ​​the inlet 302.

[0076] As previously mentioned, the body of the Venturi device 300 may also include a throat 308, also referred to as a constriction. The throat 308 may be disposed between the converging section 306 and the diverging section 310. The cross-sectional area of ​​the converging section 306 may be circular. In some configurations, the converging section 306 may define a cone-shaped flow area. Additionally, the cross-sectional flow area of ​​the diverging section 310 may be circular. In some configurations, the diverging section 310 may define a cone-shaped flow area. The converging section 306 may be configured to increase the velocity of the main flow and reduce the pressure of the main flow. The diverging section 310 may be configured to reduce the velocity of the main flow and increase the pressure of the main flow. The magnitude of the cross-sectional flow area of ​​the converging section 306 may change more rapidly than the magnitude of the cross-sectional flow area of ​​the diverging section 310 per unit length.

[0077] The venturi device 300 may include a body wall 305 that defines a converging section 306 and a diverging section 310. The outer shell of the body wall 305 may utilize a fixed angle reduction ratio between 1.25:1 and 5:1, between 1.5:1 and 4:1, between 1.75:1 and 3:1, or between 2:1 and 2.5:1. The restriction 308 may include a diameter that is smaller than the diameter of the converging section 306 and the diameter of the diverging section 310. The converging section 310 may include a cross-sectional flow area that is continuously smaller in the flow direction of the primary flow. The diverging section 310 may have a cross-sectional flow area that is continuously larger in the flow direction of the primary flow. The length of the diverging section 310 may be greater than the length of the converging section 306. The outer wall of the diverging section 310 of the venturi device 300 may be smaller than the outer wall of the converging section 306. The outer wall of the diverging section 310 of the Venturi device 300 can be 1%-50%, 5%-45%, 10%-40%, 15%-35%, 20%-30%, or 22.5%-27.5% smaller than the outer wall of the converging section 306. The outer wall of the diverging section 310 can be attached to the outer layer of the converging section 306. Additionally or alternatively, the internal nozzle reduction angle between the throat 308 and the second converging section 314 can be variable to increase the fluid flow rate and create a vacuum at the first fluid dynamic check valve.

[0078] The first funnel 307 can be at least partially disposed in the converging portion 306. The first funnel 3307 can be configured to be attached to the converging portion 310. In some configurations, the first funnel 307 can be welded to the converging portion 310. An end of the first funnel 307 can also be configured to be attached to the inlet 302 as well as along the converging portion 310. In some configurations, section 1 and the first funnel 307 can comprise a single piece that is attached to sections 3 and 4. The first funnel 307 can form a first annular space 309 between the first funnel 307 and the body wall 305.

[0079] The first funnel 307 can provide high and low pressure stages to capture back pressure from the engine pulse wave in the exhaust. The captured back pressure can be circulated back to the high pressure primary flow. The high pressure fluid flow can push low pressure back pressure against the boundary layer along the inside of the body wall 305 to exist in the first annular space 309, the fluid behavior acting as a hydrodynamic check valve. The low pressure fluid can then be utilized to fill the primary flow once there is a pulse and the high pressure fluid flow is reduced through the first funnel 307, allowing the low pressure fluid to exit the first annular space 309 to fill the fluid flow when the high pressure fluid flow is reduced through the first funnel 307 due to the primary flow pulse. The first funnel 307 can provide a higher tuned intake resonance to help amplify the intake charge (e.g., substantially continuous intake intake draw / pull of the primary flow through the inlet 302). The first funnel 307 can extend from the body wall 305 toward a central axis 312 of the body 311 .

[0080] In some configurations, the venturi device 300 can include a pseudo-spherical inlet constituting a first funnel 307 that can improve impulse resonance, fluid velocity, and / or internal geometry by functioning a first hydrodynamic check valve. The first funnel 307 can be configured to generate a first low pressure fluid in the first annular space 309 against the primary high pressure fluid flow through the first funnel 307 to draw the primary flow through the inlet 302 and into the body 311. In some configurations, the first funnel 307 can be connected to the body wall 305 at the inlet 302. The reduction in the primary high pressure fluid flow through the first funnel 307 can cause the first low pressure fluid to at least partially exit the first annular space 309 for flow toward the outlet 304. The cross-sectional flow area of ​​the first funnel 307 can be continuously smaller toward the central axis 312 in the primary fluid flow direction.

[0081] The second funnel 313 can be at least partially disposed within the diverging portion 310. The second funnel 313 can function as an internal expansion transition that forms a second low pressure gap. In some configurations, sections 1 and 3 of FIG. 16D can be constructed from one, single, and / or monolithic continuous piece of material that is attached to section 4. Section 4 can be welded to sections 1 and 3. The space between sections 1 and 3 and section 4 can form the second funnel 313. In some configurations, sections 3 and 4 can be constructed from one, single, and / or monolithic continuous piece of material that is configured to be attached to sections 1 and 2. The second funnel 313 can extend from the body wall 305 toward the central axis 312 of the body 311, the second funnel 313 forming a second annular space 315 between the second funnel 313 and the body wall 305. The second funnel 313 can also function as a dynamic check valve similar to the first funnel 307 .

[0082] The first funnel 307 and the second funnel 313 amplify the suction created by the intake charge forming a high velocity jet of fluid as well as recycle any back pressure created by the intake pulse wave, for example from a combustion process in an internal combustion engine or other pulses in the primary flow. The second funnel 313 may be connected to the body wall 305 at the junction between the converging section 306 and the diverging section 310. The second funnel 313 may be configured to generate a second low pressure fluid in the second annular space 315 relative to the high pressure fluid flow of the primary flow through the second funnel 313 to draw the primary flow through the inlet 302 and into the body 311. The reduction in the high pressure fluid flow of the primary flow through the second funnel 313 may cause the second low pressure fluid to at least partially exit the second annular space 315 such that the second low pressure fluid flows towards the outlet 304. The cross-sectional flow area of ​​the second funnel 313 may continuously decrease in size toward the central axis 312 in the flow direction of the primary fluid. Additionally or alternatively, the cross-sectional flow area at the outlet of the first funnel 307 may be substantially the same as the cross-sectional flow area at the outlet of the second funnel 313. The second annular space 315 may function as a second dynamic check valve. The second annular space 315 may be larger than the first annular space 309. The axial extent of the first funnel 307 may be substantially equal to the axial extent of the converging portion 306 along the central axis 312. The axial extent of the second funnel 313 is less than the axial extent of the diverging portion 310 along the central axis 312.

[0083] The secondary input 320 can be disposed between the converging section 306 and the outlet 304. The secondary input 320 can be disposed downstream of the diverging section 310. The secondary input 320 can be configured to direct the secondary flow of fluid into the primary flow to form a vortex and draw the primary flow through the inlet 302 and into the body 311. The secondary input 320 can further include a Coanda surface. In some configurations, the secondary input 320 can be configured to direct the secondary flow of fluid into the primary flow at an angle relative to the flow direction of the primary flow. The angle can be between 10 degrees and 170 degrees, between 20 degrees and 160 degrees, between 30 degrees and 150 degrees, between 40 degrees and 140 degrees, between 50 degrees and 130 degrees, or between 60 degrees and 120 degrees. In some configurations, the secondary input 320 can include one or more openings 332. In some configurations, the secondary input 320 can include multiple openings 332. One or more of the openings 332 can direct the secondary flow to the annular chamber 318. The annular chamber 318 can distribute the secondary flow throughout the annular chamber 318, for example, via a Coanda surface, as discussed herein.

[0084] The secondary input 320 may include an annular gap 329 similar or identical to the annular gap 120. The annular gap 329 may be in fluid communication with the annular chamber 318. The annular gap 329 may distribute the secondary flow through the annular gap, for example via a Coanda surface, and direct the secondary flow to the primary flow. The secondary input 320 may also include an annular gap 330, which may be the annular gap 329. The secondary input 320 may be configured to surround the primary flow through the body 311. In some configurations, the secondary input 320 may be configured to circumferentially surround the primary flow through the body 311. The secondary input 320 may also include one or more openings (e.g., one or more gaps 329) distributed circumferentially about the flow path of the primary flow, and the secondary input 320 is configured to direct the secondary flow radially inward toward the primary flow. In some configurations, the venturi device 300 may include multiple secondary inputs 320.

[0085] The conical inner surface 319 may be disposed downstream of the secondary input 320 relative to the primary flow of fluid. The conical inner surface 319 may be configured to direct the primary flow towards the outlet 304. The conical inner surface 319 may also include a cross-sectional flow area that increases towards the outlet 304.

[0086] A cross-sectional flow area of ​​the inner conical surface 319 may increase until the outlet 304. The inner conical surface 319 may be a first inner conical surface 319, and the venturi device 300 may include a second inner conical surface 321 disposed between the diverging portion 310 and the first inner conical surface 319. The second inner conical surface 321 may be part of the second converging portion 314. The second inner conical surface 321 may be configured to direct the primary flow toward the outlet 304. The second inner conical surface 321 may include a cross-sectional flow area that decreases in size toward the outlet 304. The secondary input 320 may be configured to direct the secondary flow through the second inner conical surface 321. The secondary input 320 may be configured to direct the secondary flow between the first inner conical surface 319 and the second inner conical surface 321.

[0087] The cross-sectional flow area of ​​the second inner conical surface 321 can converge to a size smaller than the cross-sectional flow area of ​​the converging section 306 and the cross-sectional flow area of ​​the diverging section 310. The first inner conical surface 319 and the second inner conical surface 321 can converge to form a throat 323 having a minimum diameter and a minimum cross-sectional flow area for the first inner conical surface 319 and the second inner conical surface 321.

[0088] As shown in FIG. 16A, a combustion chamber 328 can be disposed at the outlet 304. The combustion chamber 328 can include one or more fuel burners and / or racks for combusting the incoming primary and secondary streams as discussed herein. The centrifugal housing shape of the combustion chamber 328 can allow for the flame in the combustion chamber 328 to be recirculated and recycled so that there is complete combustion of the injected streams. The combustion chamber can be configured to maintain high heat that allows for clean combustion of the particulate matter. Once the primary and secondary streams pass through the combustion chamber and are completely combusted, the primary and secondary streams can enter an internal combustion chamber. The combustion chamber can reach temperatures between 400° C. and 1200° C., between 1600° C. and 1900° C., between 600° C. and 1000° C., or between 700° C. and 900° C., resulting in clean combustion of the particulate matter.

[0089] The diameter of the inlet opening 302 may vary depending on the driving speed (if the particulate burner is used in a vehicle). If the driving speed is high, the inlet opening 302 can be smaller. If the driving speed is low, the inlet opening can be larger. The size of the inlet can also be adjusted in relation to the engine size, horsepower, and maximum speed of the vehicle. The diameter of the inlet opening 302 can be differentiated depending on the driving speed (if the particulate burner is used in a vehicle) to optimize the flow rate of the primary fluid and aid in the combustion of the exhaust. The geometry of the inlet opening 302 can be directly related to the mathematical volumetric induction of the engine or machine to which the particulate burner is connected. These measurements can be adjusted in relation to the engine size, horsepower, and maximum speed of the vehicle. For example, if the overall maximum speed is 180 mph, induction forces can be utilized to magnify the power effect of the particulate burner. For example, if the maximum speed is 30 miles per hour, a smaller point inlet opening 302 with a less aggressive deceleration angle is required to achieve the desired results.

[0090] Additionally, the ambient air inlet (FIG. 16C, FIG. 16A) can be shaped like a velocity stack that allows for a smooth and uniform entry of the air at high velocities. Here, resonance effects are also observed that promote the generation of vortices. Additionally, the inner wall of the Venturi device 300 can include radius inlets and / or "plenums". Velocity stacks, trumpets, or air horns are trumpet-shaped designs with different lengths that can be used at the inlet 302. These designs allow for a smooth and uniform entry of the air at high velocities with wall-attached flow known as laminar flow. Additionally or alternatively, the dynamic tuning range of the intake pipe can be changed by making it act as a resonating pipe that can adjust the frequency of the pressure pulse depending on its length within the intake pipe. Modern engines are designed to allow the intake pipe volume and its associated resonant frequency to be adjusted, resulting in an intake pressure higher than atmospheric pressure while the intake valve is open. These intake pipe volumes can increase the density of the trapped air in the combustion chamber providing higher compression.

[0091] The system, particulate burner, particulate burner system, and venturi device 300 can be made in a variety of dimensions. Some non-limiting exemplary dimensions for a particulate burner according to FIG. 16A are given below: Length between (D) and (C) = between 6.00 inches and 7.00 inches Ring Gap 120 = 0.001 inch to 0.003 inch B=Inner diameter (also called "ID") at 1.57 to 1.68 inches The contraction angle between (D) and (B) is between 35° and 55°. The contraction angle between (C) and (B) is between 55° and 65°. Inside diameter at (C) = between 1.63 inches and 2.05 inches Inner diameter (D) = between 3.25 inches and 4.01 inches Length between (D) and (E) = 4.50~6.00 inches Contraction angles in (D) and (E) = 30° and 53° (E) Inner diameter = between 1.25 inches and 2.35 inches Contraction angle between (F) and (E) = 33° or more and less than 41° Length between (F) and (E) = between 4.00 inches and 6.00 inches The conduit is a steel pipe with an inside diameter of 0.75" to 1.00". Converging section 306 is a modified pressure actuated heat riser butterfly valve Inlet port 302, (F), can be made of an elastic polymer or a programmable metal polymer to adjust its opening in response to the input suction pressure. The area between (E) and (F) can be made of an elastic polymer or a programmable metal polymer to adjust its opening in response to the applied input pressure (e.g., different dynamic pressures at different driving speeds if the particulate burner is to be installed on a vehicle). The ring gap 330 can have a Coanda effect profile of 35° to 80°. The ring gap 330 may be angled at 70 degrees to the edge of the ring.

[0092] The venturi device 300 can be constructed of dissimilar metals, which can create friction at the internal points of compression, and can reduce friction to create a more efficient boundary layer for the fluid acceleration of the compressed fluid into the intake charge.

[0093] A method for converting thermal energy into electrical energy or another form of energy, characterized in that a heat engine based on the suction effect is used to convert heat into electrical energy or another form of energy. The suction effect can be generated by vortices in a flowing medium. The generation of vortices can also be caused directly by the flow of a free-flowing medium. Due to the suction effect, the flowing medium is sucked in, the temperature of the sucked in flowing medium decreases, the sucked in flowing medium absorbs energy in the form of heat, and the internal energy increases. The energy absorbed in the flowing medium can be extracted again from the flowing medium. The energy stored in the flowing medium can be extracted by a combination of a turbine and a generator. The extracted energy can be extracted in the form of electrical energy. The generation of vortices is carried out in a part (hereinafter referred to as "VFC"), which resembles a tube and whose internal diameter can have different values ​​along its axis. This part can be provided with openings into which the flowing medium can be introduced. A vortex can be generated inside the part, resulting in a suction effect. The flowing medium is sucked in on one side of the vortex and expelled on the other side of the vortex. A flowable medium can flow through the component by entering at the front and exiting at the rear. Thermal energy can be transferred to the flowing fluid medium by one or more VFCs, increasing the internal energy of the fluid medium, a process called "charging". Internal energy can be extracted from the flowing fluid medium, which is called "discharging". A portion of the energy extracted by discharging can be supplied to the device to compensate for energy losses so that the cycle of charging and discharging the flowing medium is maintained.

[0094] A method using energy from the exhaust gases of an internal combustion engine to charge with ambient air or a mixture of ambient air and fuel (particulate burners). Some configurations may not use any mechanically moving parts or mechanically moving equipment compartments. A vortex can be generated in the equipment by the gas flow. This vortex can create a vacuum or negative pressure on one side. This negative pressure draws in ambient air or a mixture of ambient air and fuel. This ambient air or a mixture of ambient air and fuel is expelled or compressed on the other side of the vortex and directed into the internal combustion engine. The vortex can be induced by the exhaust gases from the internal combustion engine.

[0095] The systems, devices, and components thereof can be made from a variety of materials, such as metals (such as steel, aluminum, and / or the like), metal alloys, polymers (such as plastics), ceramics, shape memory materials, and / or other suitable materials. The systems, devices, and components thereof can be galvanized, painted, zinc coated, powder coated, vinyl coated, plastidrip, textured, and / or finished with other materials or methods.

[0096] Although the systems and methods have been disclosed in the context of particular configurations and examples, those skilled in the art will appreciate that the systems and methods extend beyond the specifically disclosed configurations to the use of other alternative configurations and / or configurations, as well as certain modifications and equivalents thereof. Various features and aspects of the disclosed configurations may be combined with one another or substituted for one another to form various aspects of the conveyor. The scope of the present disclosure should not be limited by the particular disclosed configurations described herein.

[0097] Certain features described in this disclosure in the context of separate implementations can also be implemented in combination in a single implementation. Conversely, various features described in the context of a single implementation can also be implemented separately in multiple implementations or in any suitable subcombination. Furthermore, although features are described above as acting in a particular combination, in some cases one or more features can be excluded from a claimed combination, and the combination can be claimed as any subcombination or a variation of any subcombination.

[0098] Stealth Weapon Thruster System Figures 17-18 show cross-sectional views of a thruster system 700 configured to propel a deep earth penetrating munition, which may also be referred to as a stealth weapon thruster system, Figures 19A-20D illustrate different configurations of the stealth weapon munitions system of Figures 17 and 18, Figure 21 illustrates thrust vector manipulation, and Figures 22A-22C illustrate schematics of a Venturi device 710. The thruster system 700 and Venturi device 710 may utilize a combination of the Coanda effect, the Venturi effect, and improvements in boundary layer dynamics in closed and / or open systems to improve propulsion and power generation by non-mechanical means.

[0099] The thruster system 700 may be configured to integrate with a charge 701 having an aerodynamic body 702. The thruster system 700 may include a transfer cone 704 connected to the charge body 702, directing a primary flow of fluid from a surface of the charge body 702 along a surface of the transfer cone 704, one or more stabilizing fins 708 having a leading edge 708a and a trailing edge 708b, and a venturi device 710 (which may be similar and / or identical to the venturi device 100 described in FIG. 1A and / or similar and / or identical to the venturi device 300 described in FIGS. 16A-16C). One or more side inlets 712, an outlet nozzle 714, one or more valves 716, a storage tank 718, one or more propellant passages 720 (also described herein as "channels"), and one or more pipes 729 disposed downstream of the transfer cone 704. In some configurations, the Venturi device 710 is connected to the stabilizing fins 708. In some configurations, the Venturi device 710 is connected to at least one of the transfer cone 704 and / or the munitions body 702 via the stabilizing fins 708. In some configurations, the Venturi device 710 is connected to at least one of the transfer cone 704 and / or the munitions body 702 without being connected to the stabilizing fins 708.

[0100] The stabilizing fins 708 can be connected to at least one of the transfer cone 704 and / or the munitions body 702. The stabilizing fins 708 can extend radially outward relative to at least one of the surface of the transfer cone 704 or the surface of the munitions body 702 to stabilize the munitions body 702. The stabilizing fins 708 can be of any shape and / or size to provide control and / or maneuverability of the munitions 701 relative to the intended target. Any number of stabilizing fins 708 can be used to steer the munitions 701, such as two stabilizing fins, four stabilizing fins, six stabilizing fins, etc. The control surfaces can be located along the leading and / or trailing edges to aid in longitudinal and / or directional steering of the munitions as well as provide precise adjustments to the flight path. The control surfaces can be powered by a fuel cell integrated into the thruster system 700 at any suitable location. While airborne, the stabilizing fins 708 can provide additional lift while retracted into the host aircraft which can assist in increasing the range and / or flight performance of the host aircraft. The stabilizing fins 708 can also be located on the forward portion of the munitions body 702 to provide additional stability and control.

[0101] The thruster system 700 may also include another stabilizing fin 709 coupled to at least one of the transfer cone 704 and / or the munitions body 702, which may be similar or identical to the stabilizing fin 708. The other stabilizing fin 709 may extend radially outward relative to at least one of the surfaces of the transfer cone 704 and / or the munitions body 702 to stabilize the munitions body 702. The other stabilizing fin 709 may include one or more channels 720 along the other stabilizing fin 709. The one or more channels 720 of the other stabilizing fin 709 may be connected to the storage tank 718 to direct propellant (e.g., nitrogen) from the storage tank 718 along the extent of the other stabilizing fin 709. The secondary flow may include propellant (e.g., nitrogen) directed from the storage tank 718 through the one or more channels 720 of the other stabilizing fin 709 to the secondary input 740 along the other stabilizing fin 709 to provide thrust to the munitions 701.

[0102] In some configurations, the propellant stored in the storage tank may be a liquid that vaporizes to a gas before the liquid reaches the side inlet 712. In some configurations, the propellant flowing from the storage tank may be a gas that remains gaseous and is exhausted from the exit nozzle 714. In some configurations, the other stabilizing fin 709 may be positioned 180 degrees away from the stabilizing fin 708 with respect to the central axis of the ammunition body 702.

[0103] The storage tank 718 can be located in a recessed portion of the ammunition body 702 in the forward and / or aft regions. In some configurations, the storage tank 718 can be in at least one of the transfer cone 704 and / or the ammunition body 702. The storage tank 718 can store pressurized propellant, such as gas and / or liquid, which can be discharged from the storage tank 718. By releasing a propellant, such as nitrogen or an inert gas, through the thruster system 700, the thruster system can disappear in a thermal image as the ammunition 701 approaches the target. When storing propellants that are not combustible elements, as in a typical combustion propellant weapon, it is possible to avoid the detonation of unused combustible material before the ammunition 701 reaches its intended depth of the target. In some configurations, the storage tank 718 can be a bladder type that changes shape as the propellant is transferred from the storage tank.

[0104] Additionally or alternatively, the storage tank 718 can be compartmentalized such that different compartments can simultaneously store different propellants. The storage tank 718 can be pressurized prior to loading onto the host vehicle and / or while the munitions 701 are attached to the host aircraft. The storage tank 718 can store propellants that can be used to propel the munitions 701 stealthily toward a target at high speeds. The thruster system 700 can increase the speed of the munitions 701 by 1x, at least 2x, at least 3x, at least 4x, at least 5x, or at least 10x the normal operating speed. The storage tank 718 can contain a sufficient amount of propellant to propel the munitions 701 for at least 5 seconds, at least 10 seconds, at least 30 seconds, at least 60 seconds, at least 90 seconds, at least 180 seconds, or at least 600 seconds. The storage tank 718 can store various propellants such as inert gases (e.g., nitrogen), liquids (e.g., liquid nitrogen), and / or solid propellants. The munitions 701 can reach maximum velocity between 20 and 30 seconds after ejection from the host aircraft before propellant is released. Releasing propellant just prior to impact can isolate the event and reduce the chance of collateral damage. In some configurations, the storage tank 718 can store liquid nitrogen that undergoes a phase change to a gas for injection into the primary flow from the secondary input.

[0105] The stabilizing fin 708 may include one or more channels 720 along the stabilizing fin 708. The channels 720 may be connected to the storage tank 718 such that the channels 720 may direct propellant from the storage tank 718 along the extent of the stabilizing fin 708. The channels 720 may branch into multiple channels from one main channel. This advantageously allows propellant to branch into different channels to affect the amount of propellant that reaches the thruster system 700. In some configurations, the channels 720 may connect to the side inlet 712 by passing the propellant (e.g., nitrogen) through a pipe 729. The pipe 729 may be circular, elliptical, square, rectangular, or other shape depending on its location along the stabilizing fin 708. In some configurations, the one or more channels 720 include one or more tubes 721 that extend along the extent of the stabilizing fin 708. The one or more tubes 721 may be within the stabilizing fin 708.

[0106] Also, one or more channels 720 can be disposed in the stabilizing fin 708 to reduce turbulent forces at hypersonic speeds. In some configurations, the channels 720, tubes 721, tubes 729, and / or inlets 712 can be disposed in the stabilizing fin 708 to reduce turbulent forces at high speeds. By positioning the channels 720, tubes 721, tubes 729, and / or inlets 712 in the stabilizing fins 708, 709, the stabilizing fins 708 can maintain a consistent profile with limited irregularities and turbulence along the surface of the munitions 701. Containing components within the stabilizing fins 708 and / or the munitions barrel 702 can help maintain laminar flow along the surface of the munitions 701 and limit turbulent effects or separation of the airflow from the surface of the stabilizing fins 708 and / or any control surfaces connected to the stabilizing fins. Additionally or alternatively, encasing the channel 720, tube 721, tube 729, and / or inlet 712 in stabilizing fins 708, 709 can reduce turbulence at Mach 2, Mach 3, Mach 4, Mach 5, and above, where slight movements can cause large changes in direction or orientation. Mach ranges above Mach 2 can be achieved by ejecting the munition 701 at altitudes of 100,000 feet or greater, thereby achieving sufficient speeds to classify the munition 701 as a hypersonic weapon.

[0107] The pipe 729 may include an inlet opening 732 that draws in ambient air as well as the propellant transported through the channel 720. The secondary flow through the secondary input may include ambient air that is directed from a surface of the stabilizing fin 708 to the secondary input 740. In some configurations, the secondary input 740 may include one or more pipes 729 that extend from the body 711 of the venturi device 710 to the trailing edge 708b of the stabilizing fin 708, each of the one or more pipes 729 including an opening 732. The trailing edge 708b of the stabilizing fin 708 draws ambient air into the one or more pipes 729, which direct the ambient air into the secondary input 740. In some configurations, each of the one or more pipes 729 of the secondary input 740 includes a funnel 734 at a location. A funnel 734 is connected to the trailing edge 708b of the stabilizing fin 708, and the funnel 734 is configured to draw ambient air around the surface stabilizing fin 708 into one or more pipes 729. The funnel 734 may have a diameter larger than the diameter of the pipes 729 of the corresponding secondary input 740 of the stabilizing fin 708.

[0108] FIG. 21 illustrates thrust vectoring operation with munitions 701. In some configurations, four sets of inlets 712 spaced 90 degrees apart can be used for thrust vectoring, although any number can be used. A valve 716 can be disposed in each of one or more channels 720 in the stabilizing fins 708 and / or other stabilizing fins 709. The valve 716 can be configured to control the flow of propellant from the storage tank 718 to the secondary input 740. In some configurations, the propellant can be nitrogen and / or liquid nitrogen. In some configurations, the valve 716 can be disposed on the secondary input 740 so as to be configured to control the flow of the secondary stream through the secondary input 740.

[0109] By adjusting the flow of the secondary stream through the secondary input 740, the direction and force of the thrust of the munitions 701 can be controlled. The valves 716 can be opened and closed to adjust the flow of propellant to the venturi device 710. When the flow of propellant from one side of the thruster system 700 is stopped and / or restricted, a low pressure area forms a low pressure side and the flow of propellant from the high pressure side starts to flow to the low pressure side. The flow of pressure from the high pressure side to the low pressure side changes the direction of the thrust flowing through the exit nozzle 714. Depending on the amount of propellant required for a particular maneuver, the valves 716 can be adjusted by opening and closing. The thrust vectoring function can act in a pitch direction or a yaw direction depending on which valves are open and / or closed and the orientation of the munitions 701. In one configuration, the secondary thrust can be reduced. The flow through the secondary input 740 closest to the other stabilizing fin 709 can create a low pressure area in the venturi device 710 on the side of the other stabilizing fin 709 compared to the pressure in the venturi device 710 at the stabilizing fin 708. The propellant flowing through the venturi device 710 flows toward the other stabilizing fin 709, resulting in a greater propellant flow through the exit nozzle 714 proximal to the other stabilizing device 709, imparting thrust to the charge 701 in the direction of the stabilizing fin 708.

[0110] As described above, propellant is introduced into the Venturi device 710 from the conduit 736 via the secondary input 740, which may include the annular chamber 738 and the ring gap 750. When the Venturi device 710 is used, a vortex may be formed, as described with reference to FIG. 7. This vortex creates a vacuum at the inlet 722 (location F). As a result, ambient air may be drawn into the Venturi device 710 via the inlet 722 and the throat 728 (e.g., a constriction).

[0111] The region of the pipe between B and E may be referred to as the compression chamber, since the air is compressed on the opposite side of the vortex (direction C). The annular chamber 738 may be configured to receive the secondary flow and direct it to the secondary input 740. In some configurations, the Venturi device 710 may include a single-point annular chamber 738 for compressible propellant. In some configurations, the annular chamber 738 may include multiple uniform chamber inputs for incompressible propellant. In some configurations, the annular chamber 738 may surround the primary flow within the body 711 of the Venturi device 710. The annular chamber 738 may include a Coanda surface configured to distribute the incoming secondary flow throughout the annular chamber 738 with the secondary fluid flowing along the Coanda surface.

[0112] The secondary input 740 may be an annular passage, one or more openings, a plurality of openings, one or more slots, annular gaps, and / or a ring gap fluidly connected to the annular chamber 738. The annular passage 741 may be configured to direct the secondary flow from the annular passage 741 to the primary flow. Fluids entering from the inlet 712 and the conduit 736 merge at a location corresponding to B and exit the thruster system 700 through the outlet 724 at location C.

[0113] As previously mentioned, the body of the venturi device 710 also includes a throat 308, also referred to as a constriction. The throat 728 may be disposed between the converging section 726 and the diverging section 730. The cross-sectional flow area of ​​the converging section 726 may be circular. In some configurations, the converging section 726 may define a cone-shaped flow area. Additionally, the cross-sectional flow area of ​​the diverging section 730 may be circular. In some configurations, the diverging section 730 may define a cone-shaped flow area. The converging section 726 may be configured to increase the velocity of the main flow and reduce the pressure of the main flow. The diverging section 730 may be configured to reduce the velocity of the main flow and increase the pressure of the main flow. The magnitude of the cross-sectional flow area of ​​the converging section 726 may change more rapidly than the magnitude of the cross-sectional flow area of ​​the diverging section 730 per unit length.

[0114] The venturi device 710 may include a body wall 711 that defines a converging section 726 and a diverging section 730. The outer shell of the body wall 711 may utilize a fixed reduction angle ratio of 1.25:1 to 5:1, 1.5:1 to 4:1, 1.75:1 to 3:1, or 2:1 to 2.5:1. The throat 728 may include a diameter that is smaller than the diameter of the converging section 726 and the diameter of the diverging section 730. The converging section 726 may include a cross-sectional area that continuously decreases in size in the direction of flow of the primary stream. The diverging section 730 may have a cross-sectional area that continuously increases in size in the direction of flow of the primary stream. The length of the diverging section 730 may be greater than the length of the converging section 726.

[0115] A secondary input 740 may be disposed between the converging section 726 and the outlet 724. The secondary input 740 may be disposed downstream of the diverging section 730. The secondary input 740 may be configured to direct a secondary flow of fluid into the primary flow and generate a vortex at the inlet that creates a suction to draw the primary flow through the inlet 722 into the body 711 and increase the primary flow through the outlet to penetrate the weapon deep into the earth. The secondary input 740 may be connected to one or more channels 720, with the secondary flow being comprised of nitrogen directed from the storage tank 718 to the secondary input 740 via one or more channels 720 along the stabilizing fins 708 to provide thrust to the munitions 701. In some configurations, the secondary flow is comprised of nitrogen directed from the storage tank 718 to the secondary input 740 via one or more channels 720 along the stabilizing fins 708 and no other fluid passes through the secondary input 740. In some configurations, the stabilizing fins 708 extend axially along the body 711 of the venturi device 710 to the secondary input 740 and connect to the body 711 of the venturi device 710 at the secondary input 740, and one or more channels 720 connect to the secondary input 740 at a connection between the stabilizing fins 708 and the body 711 of the venturi device 710.

[0116] The secondary input 740 can further include a Coanda surface. In some configurations, the secondary input 740 can direct the secondary flow of fluid into the primary flow at an angle relative to the flow direction of the primary flow. The angle can be between 10 degrees and 170 degrees, between 20 degrees and 160 degrees, between 30 degrees and 150 degrees, between 40 degrees and 140 degrees, between 50 degrees and 130 degrees, or between 60 degrees and 120 degrees. In some configurations, the secondary input 740 can include one or more openings 752. In some configurations, the secondary input 740 can include multiple pipes 752. The one or more openings 752 can direct the secondary flow into the annular chamber 738. The annular chamber 738 can distribute the secondary flow throughout the annular chamber 738, for example, via a Coanda surface, as described herein. The one or more openings 752 can be fluidly connected to the one or more channels 720 such that the secondary input 740 is in closed fluid communication with the one or more channels 720. In some configurations, the one or more openings 752 can provide an increased cross-sectional flow area from the one or more channels 720 in the direction of the secondary flow through the secondary input 740.

[0117] The secondary input 740 can include an annular gap 742, which can be similar or identical to the annular gaps 120 and / or 320. The annular gap 742 can be in fluid communication with the annular chamber 738. The annular gap 742 can distribute the secondary flow through the annular gap, for example via a Coanda surface, and direct the secondary flow to the primary flow. The secondary input 740 also includes a ring gap 750, which can be the annular gap 742. The secondary input 740 can be configured to surround the primary flow through the body 711. In some configurations, the secondary input 740 can be configured to circumferentially surround the primary flow through the body 711. The secondary input 740 also includes one or more openings (e.g., one or more gaps 742) distributed circumferentially around the flow path of the primary flow. The secondary input 740 is configured to direct the secondary flow radially inward toward the primary flow. In some configurations, the venturi device 710 includes multiple secondary inputs 740.

[0118] The use of the Venturi device 710's precision circular shape, non-Euclidean engineering, and ring gap 740 design (corresponding to the ring gap 120 in the Venturi device 100) allows the thruster system 700 to recover pressure when blocking back pressure, producing higher output speeds and densities. Non-Euclidean engineering uses ellipses or hyperbolic curves instead of straight or parallel lines. The use of non-Euclidean lines can improve or limit turbulence in the flow.

[0119] The Coanda effect combined with the Venturi effect occurring in the Venturi device 710 improves the transfer of momentum and density of the fluid and reduces energy losses using the thruster system 700. The flow of the primary stream through the converging section 726, the throat 728, and / or the diverging section 730 creates a Venturi effect, creating a suction force at the inlet 722. The suction force at the inlet 722 accelerates the fluid entering the Venturi device 710, accelerating the charge 701. The flow of the primary stream through the converging section 726 and the throat 728 creates a Venturi effect, creating a suction force at the inlet 722. The flow of the primary stream through the converging section 726 creates a Venturi effect, creating a suction force at the inlet 722.

[0120] The increase in velocity and decrease in pressure of the primary flow through the convergence 726 and / or throat 728 reduces the temperature of the primary flow and transfers thermal energy (e.g., heat) from the surrounding environment outside the body of the Venturi device 710 to the primary flow. As the charge travels through the fluid, the Venturi device 710 can absorb thermal energy and transfer the thermal energy to the primary flow to increase the thrust provided through the Venturi device 710. Additionally or alternatively, the absorbed thermal energy can be dissipated through the walls of the Venturi device 710 before the primary flow exits the exit nozzle 714. On the suction side, the combination of the suction of the primary flow and the Venturi effect cools the primary flow and absorbs thermal energy from the environment in the form of heat. Additionally or alternatively, a fluid such as nitrogen can be transferred from the pressurized storage tank 718 through the channel 720 and the inlet opening 732 to the side inlet 712 to further cool the primary flow through the Venturi device 710. The pressure may continue to increase due to the energy absorbed on the pressure side. With respect to the Coanda effect, the surfaces of the annular chamber 738 may include a Coanda effect surface or profile that may promote a secondary flow of the fluid throughout the annular chamber 738. As discussed herein, the Coanda effect is the tendency of a fluid to remain attached to curved surfaces, particularly convex surfaces.

[0121] The surface of the annular chamber 738 can be convex to facilitate a secondary flow of fluid spreading throughout the annular chamber 738. The secondary flow can adhere (e.g., molecular adhesion) to the surface of the annular chamber 738 and spread throughout the annular chamber 738. The thruster system 700 can also reduce and / or minimize the thermal signature of the munition 701 since the thruster system 700 of the munition 701 uses little or no combustion propulsion. This can further reduce the likelihood of detection by radar systems. Additionally, application of the thruster system 700 can reduce the weight of the munition 701 and improve flight time to location and / or target. Additionally or alternatively, application of the thruster system 700 can reduce the drag effect of the munition 701 during transportation through the use of the Venturi device 710 and the Coanda effect, increasing the deployment range and longer flight time that the vehicle can achieve.

[0122] The thruster system 700 can increase the impact velocity by 1-20, 1-15, 1-10, or 3-8 times without the use of a combustible fuel source. The thrust and velocity of the thruster system 700 can be increased by transferring a fluid (such as nitrogen) from a pressurized fuel store 718 to the side inlet 712 of the venturi device 710 prior to impact to further pressurize the system. Thus, the thruster system 700 can avoid detection by current radar systems due to their thermal signature by using an inert gas such as nitrogen to further propel the munitions 701. The nitrogen cools the main flow through the venturi device 710. In addition to or instead of this, the use of an inert gas can reduce the chance of the munitions 701 detonating prematurely. The thruster system 700 can also achieve bunker penetration with a reduced weight of a given weapon since combustible fuel may not be required. In some configurations, the thruster system 700 can reduce the overall payload weight, thereby reducing the flight time to the target. Additionally or alternatively, thruster system 700 can improve the highly hydrodynamic shape of munitions 701 to reduce drag during transit to the target via the Venturi-Coanda effect enabled by the munitions transport, thereby increasing the range and critical endurance of the deployed aircraft.

[0123] The power output achieved by the thruster system 700 can produce much more energy than a direct air inlet, resulting in a denser and faster flow of fluid exiting the thruster system. For example, the increase in pressure as the fluid passes through the throat 728 of the venturi device 710 and combines with the secondary flow from the side inlet 712 increases with the density and velocity of the incoming fluid as it exits the exit nozzle 714.

[0124] Figures 19A-20D show configurations of the stealth weapon system of Figures 17 and 18. The stealth weapon system of Figures 17 and 18 can be an open system capable of drawing in ambient air through inlet 712, or a closed system in which inlet 712 is fluidly connected to a nitrogen tank by one or more tubes, conduits, pipes, etc.

[0125] The Venturi device 710 of Figures 17 and 18 is shown diagrammatically in Figures 22A-22C. Fluid is introduced into the Venturi device 710 from the front inlet 722 and the side inlet 712 through the conduit 736, via the annular chamber 738 and the secondary input 740 (e.g., ring gap). In the region D of the Venturi device 710, a vortex may be formed. This vortex creates a vacuum at the inlet 722 (location F). As a result, fluid may be sucked into the Venturi device 710 through the inlet 722 and the throat 728 (e.g., constriction). This air is compressed on the opposite side of the vortex (direction C), so the region between B and E of the pipe may be referred to as the compression chamber. The surrounding air and exhaust gases are merged at the location corresponding to B and are discharged from the outlet nozzle 714.

[0126] The diameter of the inlet 722 opening may vary depending on the size and shape of the munitions body 702 and / or whether a flammable system is present. If a flammable system is present, the size of the inlet 722 opening may be reduced. The inlet opening 722 may be sized to suit mission parameters.

[0127] Additionally, as shown in FIG. 22C, the fluid inlet 722 can be shaped as a velocity stack to allow air to enter smoothly and uniformly at high speeds. A resonance effect can be observed to aid in inducing vortex generation. Additionally, the inner wall of the venturi device 710 can include a radial inlet and / or "plenum." Velocity stacks, trumpets, and / or air horns can be trumpet-shaped designs of various lengths that can be used at the inlet 712. These designs allow air to enter smoothly and uniformly at high speeds with a wall-attached flow pattern known as laminar flow.

[0128] Below is a list of numbered examples. The features described in the list of examples below can be combined with additional features disclosed herein. Additionally, additional inventive combinations of features are disclosed herein that are not specifically described in the list of exemplary examples below and do not include the same features as the examples listed below. For the sake of brevity, the list of examples below does not identify all inventive aspects of the present disclosure. The list of examples below is not intended to identify key features or essential features of any subject matter described herein. 1. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, the body includes a body wall, a first funnel, a second funnel, a secondary input portion, and a conical interior surface; the body wall includes a converging portion and a diverging portion, and movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect to entrain the primary flow through the inlet; the first funnel is at least partially disposed in the convergence and extends from the body wall toward a central axis of the body, forming a first annular space between the first funnel and the body wall, configured to generate a first low pressure fluid in the first annular space relative to a high pressure fluid flow of the primary stream through the first funnel and to draw the primary stream into the body through the inlet, and configured to cause the first low pressure fluid to at least partially exit the first annular space due to a reduction in the high pressure fluid flow of the primary stream through the first funnel such that the first low pressure fluid flows toward the outlet; the second funnel is at least partially disposed in the diverging portion and extends from the body wall toward a central axis of the body, forming the second annular space between the second funnel and the body wall, configured to produce the second low pressure fluid in the second annular space against a high pressure fluid flow of the primary flow through the second funnel and to draw the primary flow into the body through the inlet, and configured to at least partially exit the second low pressure fluid from the second annular space such that the second low pressure fluid flows toward the outlet upon a reduction in the high pressure fluid flow of the primary flow through the second funnel, the second annular space being larger than the first annular space; the secondary input section is disposed between the convergence section and the outlet, the secondary input section being configured to direct a secondary flow of the fluid into the primary flow to create a vortex and to draw the primary flow into the body via the inlet; 1. A venturi device comprising: an inner conical surface disposed downstream of the secondary input with respect to the primary flow of the fluid and configured to direct the primary flow towards the outlet, the inner conical surface having a cross-sectional flow area that increases towards the outlet. 2. The Venturi device of claim 1, wherein a cross-sectional flow area of ​​the inner conical surface increases to the outlet. 3. The Venturi device of example 1 or 2, wherein the conical inner surface is a first conical inner surface, and further comprising a second conical inner surface disposed between the diverging portion and the first conical inner surface, the second conical inner surface configured to direct the primary flow toward the outlet, the second conical inner surface having a cross-sectional flow area that decreases toward the outlet. 4. The venturi device of example 3, wherein the secondary input is configured to direct the secondary flow through the second conical inner surface. 5. The venturi device of any one of claims 3 to 4, wherein the secondary input is configured to direct the secondary flow between the first conical inner surface and the second conical inner surface. 6. The venturi device of any one of embodiments 3 to 5, wherein a cross-sectional flow area of ​​the second conical inner surface converges to a size smaller than the cross-sectional flow area of ​​the converging portion and the cross-sectional flow area of ​​the diverging portion. 7. The Venturi device of any one of Examples 1 to 6, wherein the axial extent of the first funnel is substantially equal to the axial extent of the converging portion along the central axis. 8. The Venturi device of any one of Examples 1 to 7, wherein the axial extent of the second funnel is smaller than the axial extent of the diverging portion along the central axis. 9. The Venturi device of example 8, wherein the axial extent of the second funnel is half the axial extent of the diverging portion along the central axis. 10. The Venturi device of any one of Examples 1 to 9, wherein the first funnel is connected to the body wall at the inlet. 11. The Venturi device of any one of Examples 1 to 10, wherein the second funnel is connected to the body wall between the converging section and the diverging section. 12. The venturi device of any one of claims 1-11, wherein the secondary input is configured to direct the secondary flow of the fluid into the primary flow at an angle relative to a flow direction of the primary flow. 13. The Venturi device of example 12, wherein the angle is 90 degrees. 14. The Venturi device of example 12, wherein the angle is between 60 degrees and 120 degrees. 15. The venturi device according to any one of the first to fourth embodiments, wherein the secondary input section comprises an annular passage. 16. The venturi device of any one of embodiments 1 to 15, wherein the secondary input comprises one or more openings. 17. The Venturi device according to any one of the first to sixteenth embodiments, wherein the secondary input portion comprises a plurality of openings. 18. The venturi device according to any one of embodiments 1 to 17, wherein the secondary input portion comprises an annular gap. 19. The venturi device according to any one of embodiments 1 to 18, wherein the secondary input portion comprises an annular gap. 20. The venturi device of any one of Examples 1 to 19, wherein the secondary input is configured to surround the primary flow via the body. 21. The venturi device of any one of Examples 1 to 20, wherein the secondary input is configured to circumferentially surround the primary flow through the body. 22. A venturi device as described in any of Examples 1 to 21, wherein the secondary input section has one or more openings arranged circumferentially surrounding the flow path of the primary flow, and the secondary input section is configured to direct the secondary flow radially inward toward the primary flow. 23. The venturi device of any one of Examples 1 to 22, further comprising a throat disposed between the converging section and the diverging section, the throat having a diameter smaller than a diameter of the converging section and a diameter of the diverging section. 24. The venturi device of any of Examples 1-23, further comprising an annular chamber configured to receive and direct the secondary flow to the secondary input. 25. The Venturi device of example 24, wherein the annular chamber is configured to surround the primary flow within the body. 26. The Venturi device of embodiment 24 or 25, wherein the annular chamber is provided with a Coanda surface configured to distribute the incoming secondary flow throughout the annular chamber. 27. The venturi device of any of Examples 24-26, further comprising an annular passage fluidly connected to the annular chamber, the annular passage configured to direct the secondary flow from the annular passage to the primary flow. 28. The venturi device of any one of embodiments 1 to 27, wherein the secondary input portion comprises a Coanda surface. 29. The venturi device of any one of Examples 1 to 28, further comprising a plurality of secondary inputs. 30. The venturi device of any one of embodiments 1 to 29, wherein the secondary input section is disposed downstream of the diverging section. 31. The venturi device according to any one of embodiments 1 to 30, wherein the convergent section has a cross-sectional flow path area that continuously decreases in a flow direction of the primary flow. 32. The Venturi device according to any one of embodiments 1 to 31, wherein the diverging section has a cross-sectional flow path area that increases continuously in the flow direction of the primary flow. 33. The venturi device according to any one of embodiments 1 to 32, wherein the length of the diverging section is greater than the length of the converging section. 34. The venturi device of any one of embodiments 1 to 33, wherein a cross-sectional flow area of ​​the outlet is smaller than a cross-sectional flow area of ​​the inlet. 35. A venturi device described in any of Examples 1 to 34, wherein the converging section is configured to increase the velocity of the primary flow and decrease the pressure of the primary flow, and the diverging section is configured to decrease the velocity of the primary flow and increase the pressure of the primary flow. 36. The venturi device according to any one of embodiments 1 to 35, wherein the cross-sectional flow area of ​​the convergent portion is circular. 37. The venturi device of any one of embodiments 1 to 36, wherein the converging portion defines a flow area having a conical shape. 38. The venturi device of any one of embodiments 1 to 37, wherein the cross-sectional flow area of ​​the diverging portion is circular. 39. The venturi device of any one of embodiments 1 to 38, wherein the diverging portion defines a flow area having a conical shape. 40. The venturi device of any one of embodiments 1 to 39, wherein the cross-sectional flow area of ​​the converging portion changes more rapidly per unit length than the cross-sectional flow area of ​​the diverging portion. 41. The venturi device of any one of embodiments 1 to 40, wherein the length of the diverging section is greater than the length of the converging section. 42. The Venturi device according to any one of Examples 1 to 41, wherein the cross-sectional flow area of ​​the first funnel decreases continuously toward the central axis in the flow direction of the first fluid. 43. The Venturi device according to any one of Examples 1 to 42, wherein the cross-sectional flow area of ​​the second funnel decreases continuously toward the central axis in the flow direction of the primary fluid. 44. The Venturi device of any one of Examples 1 to 43, wherein a cross-sectional flow area at the outlet of the first funnel is substantially the same as a cross-sectional flow area at the outlet of the second funnel. 45. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, the body includes a body wall, a first funnel, a second funnel, and a secondary input; the body wall includes a converging portion and a diverging portion, and movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect to entrain the primary flow through the inlet; the first funnel is disposed at least partially in the convergence and extends from the body wall toward a central axis of the body, defining a first annular space between the first funnel and the body wall, configured to generate a first low pressure fluid in the first annular space in response to a flow of high pressure fluid of the primary flow through the first funnel, and configured such that a reduction in the flow of high pressure fluid of the primary flow through the first funnel causes the first low pressure fluid to at least partially exit the first annular space and flow towards the outlet; the second funnel is at least partially disposed in the bifurcation and extends from the body wall toward a central axis of the body, defining a second annular space between the second funnel and the body wall, configured to generate the second low pressure fluid in the second annular space against a flow of high pressure fluid of the primary flow through the second funnel, and configured such that a reduction in the flow of high pressure fluid of the primary flow through the second funnel causes the second low pressure fluid to at least partially exit the second annular space and flow towards the outlet; The secondary input section is disposed between the convergence section and the outlet and configured to direct the secondary flow of the fluid into the primary flow to form a vortex, the secondary input section drawing the primary flow into the body via the inlet. 46. ​​The venturi device of embodiment 45, further comprising a conical inner surface disposed downstream of the secondary input with respect to the primary flow of the fluid, the conical inner surface configured to direct the primary flow toward the outlet, the conical inner surface having a cross-sectional flow area that increases toward the outlet. 47. The Venturi device of embodiment 45 or 46, wherein the second annular space is larger than the first annular space. 48. The venturi device of any of examples 45-47, further comprising any of the features of examples 1-44. 49. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, the body includes a body wall, a funnel, and a secondary input; the body wall includes the converging portion and the diverging portion, wherein movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect to draw the primary flow through the inlet; the funnel extends from the body wall towards a central axis of the body, defining a space between the funnel and the body wall, configured to create a low pressure fluid in the space relative to a high pressure fluid flow of the primary flow through the funnel, and configured to move the low pressure fluid at least partially out of the space such that the low pressure fluid flows towards the outlet upon reduction of the high pressure fluid flow of the primary flow through the funnel; the secondary input section is disposed between the convergence section and the outlet and configured to induce the secondary flow of the fluid into the primary flow to form a vortex and to draw the primary flow into the body through the inlet. 50. The Venturi device of embodiment 49, wherein the funnel is at least partially disposed in the converging portion. 51. The venturi device of embodiment 49 or 50, further comprising an other funnel extending from the body wall toward a central axis of the body, the other funnel forming another space between the other funnel and the body wall, the other funnel configured to generate another low pressure fluid in the other space in response to a high pressure fluid flow of the primary flow through the other funnel, and configured to at least partially expel the other low pressure fluid from the other space by a reduction in the high pressure fluid flow of the primary flow through the other funnel such that the other low pressure fluid flows toward the outlet. 52. The venturi device of embodiment 51, wherein the other funnel is at least partially disposed in the diverging portion. 53. The Venturi device of embodiment 51 or 52, wherein the other space is annular. 54. The Venturi device of any one of embodiments 49 to 53, wherein the space is annular. 55. The venturi device of any one of examples 49-54, further comprising any one of the features of examples 1-44. 56. A particulate burner system for combusting fuel exhaust by-products, comprising: a housing defining a combustion chamber, a deflector, and a plurality of fins; The housing includes a bottom plate, a top plate, a circular side wall, and a Venturi device; the bottom plate having a circular bottom opening for a burner configured to inject fuel into said combustion chamber; the top plate has a circular top opening for exhausting fuel exhaust from the combustion chamber, the circular bottom opening and the circular top opening being aligned along a central axis of the housing; The circular sidewall extends between the bottom plate and the top plate about the central axis, and includes a sidewall opening connected to the bottom plate and the top plate for directing air into the combustion chamber, and the circular sidewall and the circular sidewall opening are open in a tangential direction of an inner circumferential surface of the circular sidewall to inject air into the combustion chamber in a tangential direction of an inner circumferential surface of the circular sidewall, centrifugally guide the air in an airflow direction along the inner circumferential surface of the circular sidewall, and entrain fuel from the circular bottom opening into the air moving in the airflow direction along the inner circumferential surface. the deflector plate is disposed within the combustion chamber, coupled to at least one of the bottom plate or the top plate, extends axially along the central axis, extends along the circular bottom opening, is disposed between the circular bottom opening and the sidewall opening, and mitigates fuel flow from the circular bottom opening to the sidewall opening and mitigates air flow from the sidewall opening to the circular bottom opening; the plurality of fins are disposed within the combustion chamber and connected to the bottom plate and extend radially within the combustion chamber proximate the circular bottom opening toward an inner circumference of the circular sidewall, a first radial extent from a central axis of a first fin of the plurality of fins is less than a second radial extent from a central axis of a last fin of the plurality of fins and a first axial extent of the first fin along the central axis is less than the second axial extent of the last fin along the central axis, the first fin is disposed adjacent to the deflector plate downstream of the deflector plate along an airflow direction and the last fin is disposed adjacent to the deflector plate upstream of the deflector plate along an airflow direction, the first radial extent of the first fin of the plurality of fins is less than the second radial extent of the last fin of the plurality of fins and the first axial extent is less than the second radial extent of the last fin of the plurality of fins; The first radial extent of the first fin of the plurality of fins is less than the second radial extent of the last fin of the plurality of fins to permit air flow from the sidewall opening to minimize back pressure from the first fin on the air flow from the sidewall opening. a radial extent of another fin of the plurality of fins is longer relative to the first radial extent of the first fin to further direct fuel toward an inner periphery of the circular side wall as air moves in an airflow direction along the inner periphery and entangle fuel along the plurality of fins toward the inner periphery for combustion of fuel exhaust by-products along the circular side wall; the venturi device is in fluid communication with the sidewall opening and includes an inlet, an outlet, and a body; the inlet is configured to receive a primary flow of compressed air; the outlet is in fluid communication with the sidewall opening and directs the primary flow through the sidewall opening into a combustion chamber; the body is disposed between the inlet and the outlet and includes a converging section, a diverging section, and a secondary input section, wherein movement of the primary flow through the converging section and the diverging section creates a Venturi effect to entrain the primary flow through the inlet; The secondary input section is disposed between the convergence section and the outlet and is configured to direct the secondary flow of the fluid into the primary flow to form a vortex to create suction at the inlet to increase the primary flow through the outlet and to draw the primary flow into a body through the outlet. 57. A system as described in Example 56, wherein the first radial extent of a first fin of the plurality of fins is shortest compared to the other fins of the plurality of fins. 58. A system described in embodiment 56 or 57, wherein the second radial extent of the last fin of the plurality of fins is longest compared to the other fins of the plurality of fins. 59. A system described in any of embodiments 56-58, wherein the radial extent of the plurality of fins increases along the airflow direction toward the inner circumference, directing fuel further toward the inner circumference as the air moves in the airflow direction along the inner circumference, engulfing fuel along the plurality of fins toward the inner circumference, and combusting fuel exhaust by-products along the circular sidewall. 60. The system described in Example 59, wherein the radial extent of the plurality of fins gradually increases toward the inner circumference along the airflow direction. 61. A system described in any of Examples 56 to 60, wherein the radial length of two or more of the first fins of the plurality of fins is shortest compared to other fins of the plurality of fins, and the two or more first fins constitute initial fins of the plurality of fins. 62. A system described in any of Examples 56 to 61, wherein the radial length of two or more final fins of the plurality of fins is the longest compared to other fins of the plurality of fins, and the two or more final fins constitute the final fins of the plurality of fins. 63. The system described in any one of Examples 56 to 62, wherein the length of the first fin of the plurality of fins in the first axial direction is the shortest compared to the other fins of the plurality of fins. 64. A system described in any one of embodiments 56 to 63, wherein the length of the last fin of the plurality of fins in the second axial direction is the longest compared to the other fins of the plurality of fins. 65. A system as described in any of embodiments 56-64, wherein the axial length of the plurality of fins increases along the airflow direction toward the upper plate to direct the fuel further toward the inner periphery as air moves along the inner periphery in the airflow direction to entangle fuel along the plurality of fins and combust fuel exhaust by-products along the inner periphery. 66. The system described in Example 65, wherein the axial length of the multiple fins gradually increases along the airflow direction toward the upper plate. 67. A system described in any of Examples 56 to 66, wherein the axial length of two or more of the first fins of the plurality of fins is shortest compared to other fins of the plurality of fins, and the two or more first fins constitute the first fins of the plurality of fins. 68. A system described in any of Examples 56 to 67, wherein the axial length of two or more final fins of the plurality of fins is longest compared to other fins of the plurality of fins, and the two or more final fins constitute the final fins of the plurality of fins. 69. The system of any of examples 56 or 57 and / or examples 63-68, wherein the radial length of the plurality of fins directs fuel toward the inner periphery as air moves in an airflow direction along the inner periphery, swirling the fuel along the plurality of fins toward the inner periphery, and combusting fuel exhaust by-products along the circular sidewall. 70. A system described in any of embodiments 56-63, wherein the axial lengths of the multiple fins are the same along the airflow direction toward the upper plate after the first fin, directing the fuel toward the inner periphery, as the air moves in an airflow direction along the inner periphery and entangles the fuel along the multiple fins to combust fuel exhaust by-products along the inner periphery. 71. A system as described in any of Examples 56-70, wherein the air moves in an airflow direction along the inner circumference, and the fuel is swirled along the plurality of fins to the inner circumference for burning fuel exhaust by-products along the inner circumference, so that the axial length of other fins of the plurality of fins is longer relative to the first axial length of the first fin to direct fuel toward the inner circumference of the sidewall. 72. A system described in any of embodiments 56-71, wherein a line extending from the central axis along a radial direction of the plurality of fins extends outside the perimeter of the sidewall opening for each of the plurality of fins. 73. A system described in any of embodiments 56-72, wherein each of the plurality of fins has a curved shape, the curved shape being curved in the air flow direction along an inner circumference. 74. A system described in any of Examples 56 to 73, wherein each of the plurality of fins has a first thickness near the circular bottom opening and a second thickness near an inner circumference of the circular side wall, the first thickness being greater than the second thickness. 75. A system described in any of embodiments 56-74, wherein the plurality of fins have circular ends, the ends being proximate to the circular bottom opening relative to an inner circumference of the circular side wall. 76. A system described in any of embodiments 56-75, wherein the plurality of fins comprise a Coanda surface configured to direct the fuel from the circular bottom opening along the Coanda surface toward the inner circumference of the circular side wall. 77. A system described in any of Examples 56 to 76, wherein the deflection plate is flat. 78. A system described in any of Examples 56 to 76, wherein the deflection plate is curved to follow at least one of the curvature of the periphery of the circular bottom opening or the curvature of the inner circumference of the circular side wall. 79. A system described in any of Examples 56-78, wherein the perimeter of the deflection plate is at least partially contained within the perimeter of the side wall opening when projected radially along a path from a central axis to the perimeter of the side wall opening. 80. The system of any one of embodiments 56-79, wherein the secondary flow is directed from the primary flow to the secondary input of a venturi device. 81. The system of any of embodiments 56-80, wherein the secondary flow is directed to the secondary input of a venturi device from the flow of fuel injected into the combustion chamber. 82. The system of any of embodiments 56-81, wherein the secondary flow includes fuel injected into the secondary flow upstream of the secondary input. 83. The system of embodiment 82, wherein the fuel injected into the secondary stream is the same type of fuel as the fuel injected into the combustion chamber. 84. The system of embodiment 82, wherein the fuel injected into the secondary stream is a different type of fuel than the fuel injected into the combustion chamber. 85. The system of any of Examples 56-84, further comprising a fuel ionizer in fluid communication with the secondary input upstream of the secondary input, the fuel ionizer comprising a distributor and a piezoelectric ring in contact with the distributor, the piezoelectric ring of the fuel ionizer configured to pass fuel through a ring opening of the piezoelectric ring of the fuel ionizer, and the piezoelectric ring of the fuel ionizer configured to emit an electrical discharge to fuel passing through the ring opening of the piezoelectric ring of the fuel ionizer. 86. The fuel ionizer comprises a further distributor and a further piezoelectric ring in contact with the further distributor, the further piezoelectric ring of the fuel ionizer configured to pass fuel through the further ring opening of the further piezoelectric ring of the fuel ionizer, the further piezoelectric ring of the fuel ionizer configured to emit an electrical discharge to fuel passing through the further ring opening of the further piezoelectric ring of the fuel ionizer, the further distributor and the further piezoelectric ring being downstream of the distributor and the piezoelectric ring with respect to a direction of fuel flow through the fuel ionizer, the fuel ionizer further comprising a first mesh screen and a second mesh screen, the first mesh screen being at the ring opening of the piezoelectric ring of the fuel ionizer and the second mesh screen being at the other ring opening of the further piezoelectric ring of the fuel ionizer; 86. The system of example 85, wherein the first mesh screen comprises a first plurality of mesh openings through which fuel passes, and the second mesh screen comprises a second plurality of mesh openings through which fuel passes, and a cross-sectional flow area of ​​the first plurality of mesh openings is greater than a cross-sectional flow area of ​​the second plurality of mesh openings, such that a flow of fuel through the first mesh screen and the second mesh screen creates a pressure difference between the fuel flowing downstream of the first mesh screen and upstream of the second mesh screen and the fuel flowing downstream of the second mesh screen, causing at least one of the piezoelectric ring or other piezoelectric rings of the fuel ionizer to resonate and release an electric discharge into the fuel flowing through the fuel ionizer, and the fuel ionizer comprises a copper ring disposed between the piezoelectric ring and the other piezoelectric ring of the fuel ionizer, and the copper ring is configured to dampen the resonance between the piezoelectric ring and the other piezoelectric ring of the fuel ionizer. 87. The system of example 86, wherein the piezoelectric ring of the fuel ionizer includes a first mesh screen. 88. The system of example 86 or 87, wherein the other piezoelectric ring of the fuel ionizer includes a second mesh screen. 89. The system of any of embodiments 85-88, wherein the fuel passing through the ring opening of the fuel ionizer is a gas. 90. The system of any of Examples 85-89, wherein the fuel passing through the ring opening of the fuel ionizer comprises ammonia (NH3). 91. The system of any of Examples 85-90, further comprising a fuel atomizer in fluid communication with the secondary input upstream of the secondary input, the fuel atomizer comprising a distributor and a piezoelectric ring in contact with the distributor, the distributor of the fuel atomizer configured to resonate to resonate the piezoelectric ring of the fuel atomizer, the piezoelectric ring of the fuel atomizer configured to pass fuel through a ring opening of the piezoelectric ring of the fuel atomizer, and the piezoelectric ring of the fuel atomizer configured to emit an electrical discharge to fuel passing through the ring opening of the piezoelectric ring of the fuel atomizer. 92. The system of embodiment 91, wherein the fuel through the ring opening of the fuel sprayer is liquid. 93. The system of embodiment 91 or 92, wherein the fuel sprayer comprises a mesh screen, the mesh screen having a plurality of mesh openings through which fuel passes, the mesh screen being located at the ring openings of a piezoelectric ring of the fuel sprayer. 94. The system of embodiment 93, wherein the piezoelectric ring of the fuel sprayer comprises a mesh screen. 95. The system of any of Examples 85-94, further comprising a controller and an oscillator connected to a fuel sprayer or a distributor of an ionizer, the oscillator configured to resonate the fuel sprayer or the distributor of the ionizer, and the controller configured to switch the oscillator between a low resonant frequency and a high resonant frequency, the low resonant frequency being for a cold start condition of the system and the high resonant frequency being for a hot operating condition of the system. 96. A system described in any of embodiments 85 to 95, wherein the inner periphery is configured to exert a centrifugal force on air directed from the sidewall opening, the air moving circularly around the combustion chamber along the inner periphery of the circular sidewall, creating a vortex vacuum to draw fuel from the circular bottom opening toward the inner periphery. 97. A system described in any of embodiments 85-96, wherein a line extending from the periphery of the side wall opening along the central axis of the side wall opening is tangent to the inner circumference of the circular side wall. 98. A system described in any of embodiments 85-97, wherein the bottom plate is provided with an air vent configured to direct air into the fuel flowing through the circular bottom opening. 99. The system of example 98, wherein the vent is curved to extend around a central axis following the curvature of the circular bottom opening. 100. A system described in any of embodiments 85 to 99, wherein the plurality of fins are connected to a hub, and the hub is configured to connect to the base plate and to connect the plurality of fins to the base plate. 101. The system of embodiment 100, wherein the base plate has a plurality of fastener openings for connecting the hub to the base plate. 102. A system as described in any of embodiments 85-101, wherein the fuel entering through the circular bottom opening is premixed with air upstream of the circular bottom opening. 103. The system described in any of Examples 85-102, wherein the housing is connected to a flare stack for burning volatile compounds into the atmosphere. 104. The system described in any of embodiments 85-103, wherein exhaust from the circular top opening is directed to the heat engine to produce work. 105. The system described in any of Examples 85 to 104, further comprising a chute connected to the bottom plate, the chute configured to capture non-combustible particles from fuel combusted in the combustion chamber, and the chute configured to direct the non-combustible particles from the bottom plate to a container that stores the non-combustible particles. 106. The system of embodiment 105, wherein the bottom plate includes a chute opening connected to the chute for directing non-combustible particles from the combustion chamber to the chute. 107. The system of any one of embodiments 105 to 106, wherein the non-combustible particles include vanadium oxide. 108. The system described in any of Examples 85-107, further comprising a funnel connected to the top plate above the circular top opening, the funnel configured to direct exhaust from the circular top opening through the funnel, the funnel configured to retain heat within the top plate from combustion of fuel to facilitate burning fuel exhaust by-products along the top plate. 109. The system described in embodiment 108, wherein the funnel has a cross-sectional flow area that narrows in the direction of exhaust flow from the circular top opening. 110. A particulate burner for combustion of fuel exhaust by-products, comprising: The housing includes a deflector and a plurality of fins. The housing includes a bottom plate, a top plate, and a circular side wall; the bottom plate includes a circular bottom opening for a burner configured to inject fuel into the combustion chamber; the top plate includes a circular top opening for exhausting the fuel exhaust from the combustion chamber, the circular bottom opening and the circular top opening being aligned along a central axis of the housing; the circular sidewall extends between the bottom plate and the top plate about a central axis and includes a sidewall opening connected to the bottom plate and the top plate for directing air into the combustion chamber, the circular wall opening being tangential to an inner periphery of the circular sidewall for injecting air into the combustion chamber, tangential to an inner periphery of the circular sidewall for centrifugally directing air in an airflow direction along the inner periphery of the circular sidewall, and entraining fuel from the circular bottom opening in air moving in an airflow direction along the inner periphery; the deflector is disposed within the combustion chamber, connected to at least one of the bottom plate or the top plate, extending axially along a central axis, extending along the circular bottom opening, disposed between the circular bottom opening and the sidewall opening, and mitigating fuel flow from the circular bottom opening to the sidewall opening and mitigating air flow from the sidewall opening to the circular bottom opening; the plurality of fins are disposed within the combustion chamber and connected to the bottom plate, the plurality of fins extending radially within the combustion chamber from the circular bottom opening toward an inner circumference of the circular sidewall, a first radial extent from a central axis of a first fin of the plurality of fins is less than a second radial extent from a central axis of a last fin of the plurality of fins, the first axial extent of the first fin along the central axis is less than the second axial extent of the last fin along the central axis, the first fin is disposed adjacent to the deflector plate downstream of the deflector plate along an airflow direction, and the last fin is disposed adjacent to the deflector plate upstream of the deflector plate along an airflow direction; a first radial extent of a first fin of the plurality of fins is less than the second radial extent of a last fin of the plurality of fins, and a first axial extent of a first fin along the central axis is less than a second axial extent of a last fin, such that air flows through the sidewall opening to minimize back pressure from the first fin on the flow of air through the sidewall opening; A particulate burner, wherein the radial extent of other fins of the plurality of fins is longer relative to the first radial extent of the first fin, further directing fuel toward the inner circumference of the circular side wall as air moves in an airflow direction along the inner circumference, drawing fuel toward the inner circumference along the plurality of fins for burning the fuel exhaust by-products along the circular side wall. 111. A venturi device in fluid communication with the sidewall opening; The venturi device includes an inlet, an outlet, and a body; the inlet is configured to receive a primary flow comprising air; the outlet is in fluid communication with the sidewall opening and directs the primary flow through the sidewall opening into a combustion chamber; the body is disposed between the inlet and the outlet, the body including a converging portion, a diverging portion, and a secondary input portion; movement of the primary flow through the converging and diverging sections creates a Venturi effect, drawing the primary flow through the inlet; A particulate burner as described in Example 110, wherein the secondary input section is disposed between the convergence section and the outlet, and the secondary input section is configured to direct a secondary flow of the fluid into the primary flow, generate a vortex that generates a suction force at the inlet, draw the primary flow from the inlet into the body, and increase the primary flow through the outlet. 112. The particulate burner of example 111, wherein the primary flow comprises compressed air. 113. The particulate burner of any of Examples 110-112, further comprising any of the features of Examples 56-109. 114. A fuel exhaust burner for combusting fuel exhaust by-products, comprising: A housing and a plurality of fins, the housing defines a combustion chamber and comprises a first plate, a second plate, and a sidewall, the first plate comprising a first plate opening for a burner configured to inject fuel into the combustion chamber, the second plate comprising a second plate opening for exhausting fuel from the combustion chamber, the first plate opening and the second plate opening being aligned along a central axis of the housing, the sidewall extending between the first plate and the second plate about the central axis and connected to the first plate and the second plate, the sidewall comprising a sidewall opening for directing air into the combustion chamber, the sidewall opening being adapted to inject air into the combustion chamber against an inner surface of the sidewall and to direct air in an airflow direction along the inner surface of the sidewall, the sidewall opening being adapted to entrain fuel from the first plate opening in air moving in the airflow direction along the inner surface, the plurality of fins are disposed within the combustion chamber and connected to the first plate and extend radially into the combustion chamber from the first plate opening toward an inner surface of the sidewall, a first radial extent from a central axis of a first fin of the plurality of fins is less than a second radial extent from a central axis of a last fin of the plurality of fins, the first axial extent of the first fin along the central axis is less than the second axial extent of the last fin along the central axis, the first fin is disposed downstream of the sidewall opening along an airflow direction and the last fin is disposed upstream of the sidewall opening along an airflow direction; the first radial extent of a first fin of the plurality of fins is less than the second radial extent of a last fin of the plurality of fins, and the first axial extent of a first fin along a central axis is less than the second axial extent of a last fin along a central axis, causing air to flow from the first plate toward an inner surface of the first plate and minimizing back pressure from the first fin as air flows through the sidewall opening; a radial extent of another of the plurality of fins is greater than the first radial extent of the first fin to further direct fuel toward the inner surface of the sidewall as air moves along the inner surface in an airflow direction and to entrain fuel along the plurality of fins toward the inner surface for combustion of fuel exhaust by-products along the sidewall. 115. The fuel discharge burner of example 114, further comprising a deflector plate disposed within the combustion chamber and connected to at least one of the first plate or the second plate, the deflector plate extending axially along a central axis and extending along the first plate opening, the deflector plate being disposed between the first plate opening and the sidewall opening to mitigate the flow of fuel from the first plate opening to the sidewall opening and to mitigate the flow of air from the sidewall opening to the first plate opening. 116. The fuel exhaust burner of example 114 or 115, further comprising any of the features of examples 56-109. 117. A fuel burner for combustion of fuel exhaust by-products, comprising: A housing and a plurality of fins, the housing includes a first plate defining a combustion chamber, the first plate having a first plate opening for a burner configured to inject fuel into the combustion chamber, a second plate having a second plate opening for exhausting fuel from the combustion chamber, and a sidewall, the first plate opening and the second plate opening being aligned along a central axis of the housing, the sidewall extending between the first plate and the second plate about the central axis and connected to the first plate and the second plate, the sidewall opening having a sidewall opening for directing air into the combustion chamber, the sidewall opening being adapted to inject air into the combustion chamber against an inner surface of the sidewall and to direct the air in an airflow direction along the inner surface of the sidewall, the sidewall opening being adapted to entrain fuel from the first plate opening in air moving in the airflow direction along the inner surface, the plurality of fins are connected to the first plate and extend radially within the combustion chamber from the first plate opening toward an inner surface of the sidewall; The fuel burner, wherein the plurality of fins are configured to direct fuel against an inner surface of the sidewall as air moves along the inner surface in an airflow direction, swirling fuel against the inner surface and combusting fuel exhaust by-products along the sidewall. 118. A fuel burner as described in Example 117, wherein a first radial range from the central axis of a first fin of the plurality of fins is smaller than a second radial range from the central axis of a last fin of the plurality of fins, the first fin being positioned downstream of the sidewall opening along the airflow direction, and the last fin being positioned upstream of the sidewall opening along the airflow direction. 119. A fuel burner as described in example 118, wherein a first radial extent of a first fin of the plurality of fins is less than a second radial extent of a last fin of the plurality of fins, minimizing backpressure by the first fin on the flow of air from the sidewall opening. 120. The fuel burner of example 118 or 119, wherein the radial extent of other fins of the plurality of fins is greater than the first radial extent of the first fin to direct fuel against the inner surface of the sidewall as air moves along the inner surface in an airflow direction, swirling fuel along the plurality of fins toward the inner surface, and combusting the fuel exhaust by-products along the sidewall. 121. A fuel burner as described in any of Examples 117-120, wherein a first axial extent of the first fin along the central axis is smaller than a second axial extent of the last fin along the central axis, the first fin is positioned downstream of the sidewall opening along the airflow direction, and the last fin is positioned upstream of the sidewall opening along the airflow direction. 122. A fuel burner as described in example 121, wherein the first axial extent of a first fin along the central axis is less than the second axial extent of the last fin along the central axis, allowing air to flow from the sidewall opening and minimizing backpressure by the first fin on the flow of air from the sidewall opening. 123. The fuel burner of any of examples 117-122, further comprising the features of any of examples 56-109. 124. A particulate burner system for combusting fuel exhaust by-products, comprising: a housing, a plurality of fins, and a venturi device; The housing includes a bottom plate, a top plate, and a circular side wall; the bottom plate includes a circular bottom opening for a burner configured to inject fuel into the combustion chamber; the top plate includes the top opening for exhausting fuel exhaust from the combustion chamber, the circular bottom opening and the circular top opening being aligned along a central axis of the housing; the circular sidewall extends between the bottom plate and the top plate about a central axis, the circular sidewall having a sidewall opening connected to the bottom plate and the top plate for directing air into the combustion chamber, the circular sidewall opening being tangent to an inner periphery of the circular sidewall for injecting air into the combustion chamber, and tangent to an inner periphery of the circular sidewall for directing air in a direction along the inner periphery of the circular sidewall, and for entraining fuel from the burner in the air moving in a direction along the inner periphery; The plurality of fins are disposed within the combustion chamber and connected to the bottom plate and extend radially within the combustion chamber from the circular bottom opening toward an inner circumference of the circular sidewall, a radial extent of the plurality of fins increases along a direction along the inner circumference of the circular sidewall toward the inner circumference, a first radial extent of a first fin of the plurality of fins is shorter than a second radial extent of a last fin of the plurality of fins, a first line along the first radial extent of the first fin extends radially within a perimeter of the sidewall opening and a second line along the second radial extent of the last fin extends radially outside a perimeter of the sidewall opening, the first fin is adjacent to the last fin, and a first axial extent along a central axis of the first fin is greater than a first radial extent of the first fin and is spaced apart from the central axis. a first radial extent of a first fin of the plurality of fins is shorter than a second radial extent of a last fin of the plurality of fins, a first axial extent of a first fin along the central axis is shorter than a second axial extent of a last fin of the plurality of fins along the central axis, a first axial extent of a first fin along the central axis is shorter than a second axial extent of a last fin along the central axis, minimizing back pressure against the flow of air from the sidewall openings, the radial extent of the plurality of fins increasing along a direction along an inner circumference of the circular sidewall toward the inner circumference, as the air moves in a direction along the inner circumference and entrains the fuel, the fuel is directed further toward the inner circumference, spraying the fuel along the plurality of fins toward the inner circumference and combusting the fuel exhaust by-products along the circular sidewall; the venturi device is in fluid communication with the sidewall opening and includes an inlet, an outlet, and a body; the inlet is configured to receive a primary flow comprising compressed air; the outlet is in fluid communication with the sidewall opening and directs the primary flow through the sidewall opening into the combustion chamber; the body is disposed between the inlet and the outlet and includes a converging section, a diverging section, and a secondary input section, wherein movement of the primary flow through the converging section and the diverging section creates a Venturi effect, drawing the primary flow through the inlet; The secondary input section is disposed between the convergence section and the outlet and configured to direct a secondary flow of fluid towards the primary flow, generating a vortex that creates a suction force at the inlet to draw the primary flow from the inlet into the body and increase the primary flow through the outlet. 125. The system described in embodiment 124, wherein a first radial extent of a first fin of the plurality of fins is shortest compared to other fins of the plurality of fins. 126. The system described in embodiment 124 or 125, wherein the second radial range of the last fin of the plurality of fins is longest compared to the other fins of the plurality of fins. 127. A system described in any of Examples 124 to 126, wherein the radial extent of two or more initial fins of the plurality of fins is shortest compared to other fins of the plurality of fins, and the radial extent of two or more final fins of the plurality of fins is longest compared to other fins of the plurality of fins, the two or more initial fins constitute initial fins of the plurality of fins, and the two or more initial fins are adjacent to the two or more final fins. 128. A system described in any of Examples 124 to 127, wherein a first axial length of a first fin of the plurality of fins is shortest compared to other fins of the plurality of fins, and a second axial length of a last fin of the plurality of fins is longest compared to other fins of the plurality of fins. 129. A system described in any of 124 to 128, wherein an axial length of two or more first fins of the plurality of fins is shortest compared to other fins of the plurality of fins, and an axial length of two or more last fins of the plurality of fins is longest compared to other fins of the plurality of fins, the two or more first fins constitute first fins of the plurality of fins, and the two or more first fins are adjacent to two or more last fins. 130. A system described in any of embodiments 124-129, wherein the radial lengths of the multiple fins gradually increase toward the inner circumference along a direction along the inner circumference of the circular side wall. 131. A system described in any of embodiments 124-130, wherein the axial lengths of the multiple fins gradually increase along the central axis toward the upper plate. 132. A system described in any one of embodiments 124 to 131, wherein each of the multiple fins has a curved shape, and the curved shape is curved in a direction along the inner circumference. 133. A system described in any of Examples 124 to 132, wherein each of the plurality of fins has a first thickness near the circular bottom opening and a second thickness near an inner circumference of the circular side wall, the first thickness being greater than the second thickness. 134. A system described in any of embodiments 124-133, wherein each of the plurality of fins has a rounded end relative to the inner circumference of the circular side wall near the circular bottom opening. 135. A system as described in any of 124 to 134, wherein the secondary flow is directed from the primary flow to the secondary input portion. 136. The system of any of examples 124-135, wherein the secondary stream includes additional fuel injected into the secondary stream upstream of the secondary input. 137. A system described in any of embodiments 124-136, wherein the inner periphery exerts a centrifugal force on air directed from the sidewall opening, the air being configured to move circularly around the combustion chamber along the inner periphery of the circular sidewall, creating a vacuum to draw fuel from the circular bottom opening along the plurality of fins toward the inner periphery. 138. A system described in any of embodiments 124-137, wherein a line extending from the side wall opening along the central axis of the side wall opening is tangent to the inner circumference of the circular side wall. 139. The system described in any of Examples 124-138, further comprising any of the features described in Examples 56-109. 140. A thruster system for propelling a deep earth-penetrating munition, comprising: a transfer cone, a nitrogen storage tank, a stabilizing fin, and a Venturi device; the transfer cone is connected to a munitions body and configured to direct a primary flow of fluid from a surface of the munitions body along a surface of the transfer cone; the nitrogen storage tank is provided on at least one of the transfer cone or the munitions body and configured to store nitrogen; the stabilizing fin is connected to at least one of the transfer cone or the ammunition body and extends radially outward relative to at least one of the surface of the transfer cone or the surface of the ammunition body to stabilize the ammunition body, the one or more channels along the stabilizing fin are connected to the nitrogen storage tank and direct nitrogen from the nitrogen storage tank along the extent of the stabilizing fin; the venturi device is fluidly disposed downstream of the transfer cone and includes an inlet, an outlet, and a body; the inlet is configured to receive the primary flow from a surface of the transfer cone, an apex of the transfer cone directed toward the inlet; the outlet is configured to discharge the primary flow; the body is disposed between the inlet and the outlet and includes a converging section, a diverging section, and a secondary input section, wherein movement of the primary flow through the converging section and the diverging section creates a Venturi effect, drawing the primary flow through the inlet, the secondary input section is disposed between the converging section and the outlet and is configured to direct the secondary flow into the primary fluid, generate a vortex that creates a suction force at the inlet, drawing the primary fluid through the inlet and into the body, and increase the primary fluid through the outlet to thrust the munition deep into the earth, the secondary input section being in fluid communication with one or more channels; the secondary flow including nitrogen channeled from the nitrogen storage tank through one or more channels along the stabilizing fins to the secondary input for providing thrust to a munitions charge. 141. The system of embodiment 140, wherein the nitrogen storage tank is configured to store liquid nitrogen that undergoes a phase change to a gas for injection into the primary fluid from the secondary input. 142. The system of embodiment 140 or 141, wherein the secondary flow consists of nitrogen directed from the nitrogen storage tank to the secondary input through one or more channels along the stabilizing fins, and the other fluid does not pass through the secondary input. 143. A system described in any of Examples 140 to 142, wherein the secondary input comprises one or more pipes fluidly connected to one or more channels, and the secondary input is in fluid-closed communication with the one or more channels. 144. The system of embodiment 143, wherein the one or more pipes have an increasing cross-sectional flow area from one or more channels in a direction in which the secondary fluid passes through the secondary input. 145. A system described in any of Examples 140 to 144, wherein the stabilizing fin extends axially along the body of the venturi device to the secondary input and connects to the body of the venturi device at the secondary input, and the one or more channels are fluidly connected to the secondary input at a connection between the stabilizing fin and the body of the venturi device. 146. The system of embodiment 140 or 141, wherein the secondary flow includes ambient air directed from a surface of the stabilizing fin to the secondary input. 147. The system of embodiment 146, wherein the secondary input section includes one or more pipes extending from a body of the venturi device to a trailing edge of the stabilizing fin, each of the one or more pipes having an opening at the trailing edge of the stabilizing fin for drawing ambient air into the one or more pipes and directing the ambient air to the secondary input section. 148. The system described in Example 147, wherein each of the one or more pipes of the secondary input section has a funnel at the trailing edge of the stabilization fin, the funnel being configured to draw ambient air around the surface stabilization fin into the one or more pipes, and the diameter of the funnel is larger than the diameter of the corresponding pipe of the secondary input section. 149. A system described in any of Examples 140 to 148, wherein the one or more channels include one or more tubes extending along the extent of the stabilizing fin. 150. The system described in Example 149, wherein the one or more tubes are within the stabilizing fin. 151. A system described in any of Examples 140 to 150, wherein the one or more channels are within the stabilizing fin. 152. A system described in any of Examples 140 to 151, further comprising a valve in each of the one or more channels, the valve configured to control the flow of nitrogen from the nitrogen storage tank to the secondary input. 153. The system of any of Examples 140-152, further comprising a valve at the secondary input, the valve configured to control the flow of the secondary flow through the secondary input. 154. A system described in any of embodiments 140 to 153, wherein the flow of the secondary flow through the secondary input section controls thrust to the munition. 155. The system of any of Examples 140-154, further comprising an other stabilizing fin connected to at least one of the transfer cone or the munitions body, the other stabilizing fin extending radially outward relative to at least one of the surface of the transfer cone or the surface of the munitions body to stabilize the munitions body, the other stabilizing fin comprising one or more channels along the other stabilizing fin, the one or more channels of the other stabilizing fin connected to the nitrogen storage tank to direct nitrogen from the nitrogen storage tank along the extent of the other stabilizing fin, the secondary flow of fluid comprising nitrogen directed from the nitrogen storage tank to the secondary input via one or more channels along the other stabilizing fin to provide thrust to the munitions. 156. The system of embodiment 155, wherein the other stabilizing fin is positioned 180 degrees away from the stabilizing fin about the central axis of the ammunition body. 157. The system of embodiment 155 or 156, wherein reducing the secondary flow rate through the secondary input proximate the other stabilizing fin reduces the pressure in the venturi device proximate the other stabilizing fin compared to the pressure in the venturi device proximate the other stabilizing fin, causing the fluid flow rate through the venturi device to flow toward the other stabilizing fin, thereby increasing the fluid flow rate proximate the other stabilizing device through the outlet, and providing thrust to the munition in the direction of the stabilizing fin. 158. The system of any of Examples 140-157, wherein reducing the secondary flow rate through the secondary input near the stabilizing fin reduces the pressure in the venturi device near the stabilizing fin relative to the pressure distal to the stabilizing fin, causing fluid flow through the venturi device to flow toward the stabilizing fin, resulting in an increased fluid flow near the stabilizing fin through the outlet, imparting thrust to the ammunition in a direction away from the stabilizing fin. 159. A system described in any of embodiments 140 to 158, wherein the periphery of the transfer cone is outside the inlet. 160. The system described in any one of embodiments 140 to 159, wherein the apex of the transfer cone is outside the inlet. 161. A system described in any one of embodiments 140 to 159, wherein the apex of the transfer cone is inside the inlet. 162. A system described in any of embodiments 140 or 161, wherein the venturi device is connected to the stabilizing fin. 163. The system of embodiment 162, wherein the Venturi device is connected to at least one of the transfer cone or the ammunition body via the stabilizing fin. 164. A system described in any of Examples 140 to 163, wherein the secondary input section is adjustable to adjust the input of the secondary flow to the primary flow to control thrust to the munitions. 165. A thruster system for propelling munitions, comprising: a cone, a storage tank, fins, and a Venturi device; the cone is connected to the charge body and configured to direct a primary flow of fluid from a surface of the charge body along a surface of the cone; The storage tank is provided on at least one of the cone or the charge body and is configured to store a propellant fluid; the fin is connected to at least one of the cone or the charge body and extends radially outward relative to at least one of the cone surface or the charge body surface to stabilize the charge body, the fin having one or more channels along the fin, the one or more channels being connected to the storage tank and directing propellant fluid from the storage tank along the extent of the fin; the venturi device is fluidly disposed downstream of the cone and includes an inlet, an outlet, and a body; the inlet is configured to receive the primary flow from a surface of the cone; the outlet is configured to discharge the primary flow; the body is disposed between the inlet and the outlet and includes a converging section, a diverging section, and a secondary input section, the movement of the primary flow through the converging section and the diverging section creates a Venturi effect, drawing the primary flow through the inlet, the secondary input section is disposed between the converging section and the outlet and configured to direct the secondary flow toward the primary flow, creating a vortex that creates a suction at the inlet to draw the primary flow from the inlet into the body and increase the primary flow through the outlet to penetrate the munitions deep into the earth, and is in fluid communication with one or more channels; The secondary flow includes propellant fluid directed from the storage tank through one or more channels along the fins to the secondary input to provide thrust to the charge. 166. The system of embodiment 165, wherein the apex of the cone is directed toward the inlet. 167. The system of embodiment 165 or 166, wherein the storage tank is pressurized. 168. A system described in any one of embodiments 165 to 167, wherein the propellant fluid is a liquid or a gas. 169. The system described in any one of embodiments 165-168, wherein the propellant fluid is nitrogen. 170. A system described in any of Examples 165 to 169, further comprising any of the features described in Examples 140 to 164. 171. A thruster system for propelling munitions, comprising: a cartridge body, a fin, and a Venturi device; the fins are connected to the charge body and extend radially outward relative to a surface of the charge body to stabilize the charge body; the venturi device is fluidly disposed downstream of the ammunition body and includes an inlet, an outlet, and a body; the inlet receives the primary flow; the outlet discharges the primary flow; 1. The thruster system of claim 1, wherein the body is disposed between the inlet and the outlet and comprises a converging section, a diverging section, and a secondary input section, wherein movement of the primary flow through the converging section and the diverging section creates a Venturi effect, drawing the primary flow from the inlet, the secondary input section is disposed between the converging section and the outlet and is configured to direct the secondary flow of the fluid into the primary flow, generating a vortex that creates a suction at the inlet, drawing the primary flow from the inlet into the body, and increasing the primary flow through the outlet to propel a munitions charge and perform deep earth penetration, and the secondary flow includes ambient air that is directed to the secondary input section. 172. The system of embodiment 171, wherein the secondary flow includes ambient air directed from a surface of the stabilizing fin to the secondary input. 173. The system of any one of claims 171 to 172, further comprising a storage tank within the ammunition body, the storage tank configured to store the propellant fluid. 174. The system of example 173, wherein the fin comprises one or more channels along the fin, the one or more channels connected to the storage tank and directing the propellant fluid from the storage tank along the extent of the fin, and the secondary flow includes propellant fluid directed from the storage tank to the secondary input via one or more channels along the fin to provide thrust to the munition. 175. A system described in any of Examples 171 to 174, further comprising any of the features described in Examples 140 to 164. 176. The system described in any of Examples 56-109, further comprising any of the features described in Examples 1-55. 177. The particulate burner of any of Examples 110-113, further comprising any of the features of Examples 1-55. 178. The fuel exhaust burner of any of Examples 114-116, further comprising any of the features of Examples 1-55. 179. The fuel burner of any of examples 117-123, further comprising any of the features of examples 1-55. 180. The system of any of Examples 124-139, further comprising any of the features of Examples 1-55. 181. The system of any of Examples 140-164, further comprising any of the features of Examples 1-55. 182. The system described in any of Examples 165-170, further comprising any of the features of Examples 1-55. 183. The system of any one of Examples 171-174, further comprising any one of the features of Examples 1-55.

[0129] Included are methods of using the system(s) (including device(s), apparatus(es), assembly(es), structure(s), and / or the like) of the aforementioned examples. The methods of using may include using or assembling any one or more of the features disclosed herein to achieve the functions and / or features of the system(s) as discussed in this disclosure. Included are methods of manufacturing the aforementioned system(s) disclosed herein; the methods of manufacturing may include providing, making, connecting, assembling, and / or installing any one or more of the features of the system(s) disclosed herein to achieve the functions and / or features of the system(s) as discussed in this disclosure.

[0130] term Furthermore, although operations may be depicted in the drawings or described in the specification in a particular order, such operations need not be performed in the particular order shown, or in sequential order, to achieve the desired results, and not all operations need to be performed. Other operations not shown or described may also be incorporated into the illustrated methods and processes. For example, one or more additional operations may be performed before, after, simultaneously with, or between any of the described operations. Furthermore, operations may be rearranged or reordered in other embodiments. Also, the separation of various system components in the above-described embodiments should not be understood as requiring such separation in all embodiments, and it should be understood that the described components and systems may generally be integrated together in a single product or packaged in multiple products. Moreover, other embodiments are within the scope of the present disclosure.

[0131] Conditional language such as "can," "potential," "might," or "may," unless specifically stated otherwise or understood otherwise within the context in which it is used, is generally intended to convey that a particular configuration includes or does not include certain features, elements, and / or steps. Thus, such conditional language is generally not intended to imply that the features, elements, and / or steps are in any way required for one or more configurations.

[0132] Conjunctions such as the phrase "at least one of X, Y, and Z," unless specifically stated otherwise, are understood differently with context as being commonly used to convey that an item, term, etc. may be either X, Y, or Z. Thus, such conjunctions are not generally intended to imply that a particular configuration requires the presence of at least one of X, Y, and Z.

[0133] Several configurations have been described with reference to the accompanying drawings. Components may be added, removed, and / or rearranged. For example, directional references such as "top" and "bottom" are for ease of discussion and may be rearranged so that features at the top are proximate the bottom and features at the bottom are proximate the top. Furthermore, any particular features, aspects, methods, properties, qualities, attributes, elements, etc. disclosed herein in connection with various configurations may be used in all other configurations defined herein. Furthermore, it will be recognized that any method described herein may be implemented using any apparatus suitable for performing the referenced steps.

[0134] In summary, various configurations and examples of energy conversion devices and methods have been disclosed. Although the systems and methods have been disclosed in the context of those configurations and examples, those skilled in the art will appreciate that the disclosure extends beyond the specifically disclosed configurations to other alternative configurations and / or other uses of the configurations, as well as certain modifications and equivalents thereof. The disclosure expressly contemplates that various features and aspects of the disclosed configurations may be combined with each other or substituted for each other. Thus, the scope of the disclosure should not be limited by the specific disclosed configurations described above, but should be determined only by a fair reading of the claims that follow.

Claims

1. 1. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, The body includes a body wall, a first funnel, a second funnel, a secondary input portion, and a conical inner surface. Equipped with the body wall includes a converging portion and a diverging portion, and movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect to draw the primary flow through the inlet; the first funnel is at least partially disposed in the convergence portion, extending from the body wall toward a central axis of the body, defining a first annular space between the first funnel and the body wall, configured to generate a first low-pressure fluid in the first annular space relative to a high-pressure fluid flow of the primary stream through the first funnel and draw the primary stream into the body through the inlet, and configured to cause the first low-pressure fluid to at least partially exit the first annular space with a reduction in the high-pressure fluid flow of the primary stream through the first funnel such that the first low-pressure fluid flows toward the outlet; the second funnel is at least partially disposed in the diverging portion, extending from the body wall toward the central axis of the body, defining the second annular space between the second funnel and the body wall, configured to generate the second low-pressure fluid in the second annular space relative to the high-pressure fluid flow of the primary flow through the second funnel and draw the primary flow into the body through the inlet, and configured to at least partially exit the second annular space with a reduction in the high-pressure fluid flow of the primary flow through the second funnel such that the second low-pressure fluid flows toward the outlet, the second annular space being larger than the first annular space; the secondary input section is disposed between the convergence section and the outlet, the secondary input configured to direct a secondary flow of the fluid into the primary flow to create a vortex and to draw the primary flow into the body through the inlet; 1. A venturi device comprising: an inner conical surface disposed downstream of the secondary input with respect to the primary flow of the fluid and configured to direct the primary flow toward the outlet, the inner conical surface having a cross-sectional flow area that increases toward the outlet.

2. 2. The venturi apparatus of claim 1, wherein the inner conical surface is a first inner conical surface, further comprising a second inner conical surface disposed between the diverging portion and the first inner conical surface, the second inner conical surface configured to direct the primary flow toward the outlet, the second inner conical surface having a cross-sectional flow area that decreases toward the outlet.

3. 3. The venturi apparatus of claim 2, wherein the secondary input has an opening to the second inner conical surface and directs the secondary flow through the second inner conical surface, the secondary flow being directed toward the primary flow at the second inner conical surface along the central axis.

4. 4. The venturi apparatus of claim 2 or 3, wherein the secondary input has an opening to the second inner conical surface and directs the secondary flow between the first inner conical surface and the second inner conical surface, the secondary flow being directed toward the primary flow between the first inner conical surface and the second inner conical surface.

5. 4. The venturi device of claim 2 or 3, wherein a cross-sectional flow area of ​​the second inner conical surface converges to a magnitude that is smaller than the cross-sectional flow area of ​​the converging portion and the cross-sectional flow area of ​​the diverging portion.

6. A venturi device as described in claim 1 or 2, wherein the axial extent of the first funnel from end to end is substantially equal to the axial extent of the converging portion along the central axis.

7. 3. The venturi device of claim 1, wherein the axial extent of the second funnel is less than the axial extent of the diverging portion along the central axis.

8. 8. The venturi device of claim 7, wherein the axial extent of the second funnel is half the axial extent of the diverging portion along the central axis.

9. 3. The venturi device of claim 1, wherein the first funnel is connected to the body wall at the inlet.

10. 3. The venturi device of claim 1, wherein the second funnel is connected to the body wall between the converging portion and the diverging portion.

11. 3. The venturi device of claim 1 or 2, wherein the secondary input is configured to direct the secondary flow of the fluid into the primary flow at an angle relative to a flow direction of the primary flow.

12. 3. The venturi device of claim 1 or 2, wherein the secondary input is configured to surround the primary flow through the body.

13. 3. The venturi apparatus of claim 1, wherein the secondary input comprises two or more openings arranged circumferentially around a flow path of the primary flow, the secondary input being configured to direct the secondary flow radially inward toward the primary flow.

14. The venturi device according to claim 1 or 2, wherein a cross-sectional flow area of ​​the first funnel continuously decreases toward a central axis in a flow direction of the primary flow.

15. A venturi device as described in claim 1 or 2, wherein the body is sealed around a central axis between the inlet and outlet of the second funnel, and the body seals the first annular space and the second annular space around the central axis.

16. 1. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, the body comprises a body wall, a first funnel, a second funnel, and a secondary input; the body wall includes a converging portion and a diverging portion, and movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect to draw the primary flow through the inlet; the first funnel is at least partially disposed in the convergence portion, extending from the body wall toward a central axis of the body, defining a first annular space between the first funnel and the body wall, and configured to generate a first low-pressure fluid in the first annular space relative to a high-pressure fluid flow of the primary flow through the first funnel, and configured such that a reduction in the high-pressure fluid flow of the primary flow through the first funnel causes the first low-pressure fluid to at least partially exit the first annular space and flow toward the outlet; the second funnel is at least partially disposed in the bifurcation, converging from the body wall toward a central axis of the body, forming a second annular space between the second funnel and the body wall, and configured to generate the second low-pressure fluid in the second annular space relative to the high-pressure fluid flow of the primary flow through the second funnel, and configured such that a reduction in the high-pressure fluid flow of the primary flow through the second funnel causes the second low-pressure fluid to at least partially exit the second annular space and flow toward the outlet; the secondary input section is disposed between the convergent section and the outlet and configured to direct the secondary flow of the fluid into the primary flow to form a vortex, and to draw the primary flow into the body through the inlet.

17. 17. The venturi apparatus of claim 16, further comprising an inner conical surface disposed downstream of the secondary input relative to the primary flow of the fluid, the inner conical surface configured to direct the primary flow toward the outlet, the inner conical surface having a cross-sectional flow area that increases toward the outlet.

18. A venturi device as described in claim 16 or 17, wherein the second funnel converges from the body wall toward the central axis of the body within the diverging section along the central axis, and the outlet of the second funnel is located at the end of the diverging section or upstream of it along the direction of the primary flow.

19. 1. A Venturi device comprising: an inlet configured to receive a primary flow of fluid; an outlet configured to discharge the primary flow; a body disposed between the inlet and the outlet, the body includes a body wall, a funnel, and a secondary input; the body wall includes a converging portion and a diverging portion, and movement of the primary flow through the converging portion and the diverging portion creates a Venturi effect, drawing the primary flow through the inlet; the funnel extends from the body wall toward a central axis of the body, defining a space between the funnel and the body wall, configured to create a low-pressure fluid in the space relative to a high-pressure fluid flow of the primary flow through the funnel, and configured to cause a reduction in the high-pressure fluid flow of the primary flow through the funnel to at least partially expel the low-pressure fluid from the space such that the low-pressure fluid flows toward the outlet; the secondary input section is disposed between the convergent section and the outlet and is configured to induce a secondary flow of the fluid into the primary flow to form a vortex and to draw the primary flow into the body through the inlet.

20. 20. The venturi device of claim 19, wherein the funnel is at least partially disposed in the convergence portion.

21. 21. The venturi apparatus of claim 19 or 20, further comprising an other funnel extending from the body wall toward a central axis of the body, the other funnel defining an other space between the other funnel and the body wall, the other funnel configured to generate an other low-pressure fluid in the other space relative to a flow of high-pressure fluid of the primary flow through the other funnel, and configured to cause the other low-pressure fluid to at least partially exit the other space upon a reduction in the flow of high-pressure fluid of the primary flow through the other funnel such that the other low-pressure fluid flows toward the outlet.

22. 22. The venturi device of claim 21, wherein the other funnel is at least partially disposed in the diverging portion.

23. A venturi device as described in claim 19 or 20, wherein the body is sealed around the central axis between the inlet and outlet of the funnel, and the body seals the space around the central axis.

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