瑞典专利SE1051308A1 Electrode ignition and control of electrically ignitable materials

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专利摘要:
An apparatus for providing electrically initiated and / or controlled combustion of electrically combustible fuel is provided. In one example, the device comprises a volume of electrically ignitable fuel (liquid and / or gas) capable of sustaining combustion itself, and electrodes capable of igniting the fuel. The device may further comprise a power source and control unit in electrical communication with the electrodes to provide a potential across the electrodes to initiate combustion of the propellant and / or control the combustion rate of the propellant. Different configurations or geometries for the fuel, the electrodes and the device are possible. In one example, a direct current is applied to the electrodes, which causes combustion of the fuel at the positive electrode. In another example, the electrodes are supplied with alternating current, which initiates combustion of the fuel at both electrodes. 2B
公开号:SE1051308A1
申请号:SE1051308
申请日:2009-05-15
公开日:2011-01-21
发明作者:Wayne N Sawka；Charles Grix
申请人:Digital Solid State Propulsion Llc；
IPC主号:

专利说明:

2 20 20 25 30 2 as generally described in "Digital MicroPropulsion", by Lewis et al., Sensors and Actuators A, Physical, 2000, 80 (2), pages 143-154, a grouping of microtrustors is formed, each microtrustor comprising a micro resistor, pressure chamber and rupture membrane. A fuel is present in the pressure chamber and can be ignited by supplying energy (and thus heating) the microresistor to a sufficiently high temperature to ignite the fuel. When the fuel ignites, the pressure in the chamber increases until the diaphragm ruptures, resulting in the expulsion of material from the chamber. Ejection of material produces a shock that is transmitted to the microtrust. Such microtrustors can be made as cubes, chips or chips comprising an array of microtrustors in varying numbers and sizes. Furthermore, the microtrustors can be selectively addressed to fire and influence different numbers of trustors.
Summary In one aspect of this invention, there is provided an apparatus for providing electrically induced and / or controlled combustion of electrically combustible fuels. In one example, the device comprises a volume of electrically ignitable fuel (solid and / or liquid), which in itself can sustain combustion, and two (or more) electrodes which can ignite the fuel. The device may further comprise a power source and control unit in electrical contact with the electrodes to provide a potential across the electrodes to induce combustion of the propellant and / or control the combustion rate of the propellant. By, for example, increasing or decreasing the power and current supplied by the fuel, the combustion rate can be varied.
Various configurations and geometries for fuels, electrodes and devices are described. In one example, the electrodes are in electrical contact with the electrically ignitable propellant and are supplied with direct current, which can cause combustion of the electrically ignitable propellant in the positions where the positive electrode comes into contact with the electrically ignitable propellant. In another example, alternating current is applied to the electrodes, which can cause almost simultaneous combustion of the electrically ignitable propellant in the positions where the electrodes come into contact with the electrically ignitable propellant. In some examples, one or more of the electrodes may comprise an insulating material which insulates a portion of the electrode from the electrically combustible propellant (which may burn off in connection with combustion of the propellant).
In some examples, the volume of electrically combustible propellant includes liquid propellants such as hydroxylammonium nitrate (HAN) type propellants.
The fuel can be advanced (flow, flow or pumped) to the electrodes for ignition. Liquid fuel can be conveyed to the electrodes by pump pressure.
In one example, the device further comprises a pressurizing device for increasing the pressure of the electrically ignitable propellant, where the current required to ignite the electrically ignitable propellant is reduced with increasing pressure. Furthermore, for example, the requirement for current required for ignition cannot (or will not) be met by the device without the increase in pressure from the pressurizing device. Such a device can provide a safe two-stage ignition, which for example requires both the pressurizing device and the electrodes to be activated to induce combustion. The pressurizing device may comprise one or more of an explosive charge, shock, compressed gas, pneumatic pressurization, or valve which can be adjusted to at least temporarily increase the pressure of the fuel. In other examples, multiple volumes of fuel (or "grains") may be included in a standard composition to provide a two- or three-dimensional array of combustion volumes. Such an array may comprise a plurality of core elements, each core element comprising a volume of electrically combustible fuel capable of sustaining combustion, and electrodes associated with the plurality of core elements, the electrodes being designed to selectively ignite at least one core element in the plurality of core elements. . .Éfïl7-1ÅÉ "-lï- 'fjfl.) V' N 'l. Z ﬁ lii; Eïfl: Ålïï ﬁ llšlffi FLítFå TE L Lip .ß-ar ﬁ ßr' 10 15 20 25 30 The understanding of various aspects of this invention is enhanced upon reading the detailed description below together with the accompanying figures and claims.
Brief Description of the Figures Figures 1A and 1B illustrate a cross-sectional side view and a top cross-sectional view, respectively, of a first example of a structure including electrodes and electrically flammable propellant.
Figures 2A - 2C illustrate a fragmentary second exemplary structure, a side perspective view in cross section, and a side cross-sectional view, respectively, of said second exemplary structure comprising electrodes and an electrically ignitable propellant.
Figures 2D and 2E illustrate cross-sectional side views of another exemplary structure including an electrically ignitable propellant and an electrode extending through the nozzle / exhaust region of the structure.
Figures 3A and 3B show examples of ignition processes for electric fuels for different electrode configurations.
Figures 4A and 4B show examples of ignition processes for electric fuels for different electrode configurations.
Figures 5A - 5D show examples of structures and geometries for electrodes and electrically ignitable fuels.
Figure 6 shows perspective views and cross-sectional views for an example of a “central combustion” structure including wire electrodes and electrically ignitable fuel. : Ü i f. Sääf wl- ïlt ﬂ: _f'llr, l: = i'.f ~ '.' 10 15 20 25 30 5 Figure 7 illustrates perspective views and cross-sectional views for an example of a “slit combustion” structure including wire electrodes and electrically ignitable fuel.
Figure 8 illustrates perspective and cross-sectional views of an example of a "star geometry structure" including wire electrodes and electrically combustible fuel.
Figure 9 illustrates an example of a "straw structure" including wire electrodes and electrically combustible fuel.
Figure 10 illustrates examples of a “gable burner structure” including wire electrodes and electrically ignitable fuel.
Figures 11A and 11B show two examples of methods for initiating electrically combustible fuel by utilizing pressure and electric power.
Figure 12 illustrates an example of a structure for initiating electrically combustible fuel.
Figure 13 illustrates an example of a structure and device for an electrically fired projectile or cannon.
Figure 14 shows an example of a structure for initiating electrically combustible fuel.
Detailed Description The following description is provided to enable one of ordinary skill in the art to produce and use various aspects and examples of this invention. Descriptions of specific materials, techniques, and applications are provided by way of example only. Various modifications of the examples contained herein are obvious to those skilled in the art and the general -laf 29% "k". llivïji: # 1 '. l A -ß 'I- _ U.1913' »3TFl 1_l _'._ l lf> Fíl'UH'SF (_É 6 principles defined here can be applied to other examples and applications without deviating from the basis for and Thus, this invention is not intended to be limited to the examples described and shown without conforming to the scope of the appended claims.
In one aspect of the invention, structures and systems for electrical ignition and / or control of solid or liquid fuels are described. In one example, a structure comprises high energy materials that can be broadly described as electrically flammable fuels (e.g., as described in U.S. Patent Applications 10 / 136,786, 10 / 423,072, 11 / 787,001 and 08 / 758,431, and in "Family of Modifiable High Performance"). Electrically Controlled Propellants and Explosives ”and“ Family of Metastable Intermolecular Composites Utilizing Energetic Liquid Oxidizers with NanoParticle Fuels in Gel-Sol Polymer Network ”, 61 / 053,916), which can be at least partially ignited and controlled using electric power as an electrical circuit (and not uncontrolled pyrotechnics). For example, passing electric current through the fuel causes ignition / combustion at or along the electrode surfaces. The use of an electrically combustible fuel eliminates the need for igniters (for example sparks or other thermal igniters such as resistor elements and the like) to initiate combustion of fuel. Thus, in examples here, combustion of a specific volume of propellant (herein referred to as "core" or "core element" of propellant) is initiated and / or controlled by electrical current between electrodes and through the propellant. In general, electric current from a direct current source can be used to induce combustion at or along the positive electrode and electrode polarity can be used to spread the flame front along an end surface of the propellant. In addition, electric current from an AC power source can be controlled to provide combustion at both electrodes.
In some examples, electrical ignition of materials present along one or more of your electrodes can be modified or controlled by using combustible electrical insulation materials, such as Teflon, polyethylene and the like. eiw; 4v; wl »qn ~ * ~ 5 LLFn @; TEr ﬁ * _ N @ F @ w ~ o_H lä» lí1fñ ﬁ ~ s =: «_,: ^; f- i-» ;: ﬁ i «.t» »r ._rwl '+ «10 15 20 25 30 7 By further varying the number of ignition electrodes, polarities, and / or their geometry, the combustion rate of the propellant can be changed up to and including explosive yield, efficiency or velocity. Examples of geometries include, but are not limited to, coaxial cores, layers and washers, roll-shaped layers, central combustion cores, slit-burning cores, star-burning cores, straw-burning cores, single or multiple electrode-burning cores, wire-fired and end-burning cores. similar.
Furthermore, in some examples, a control unit or power source may be designed to control the electrodes to ignite the propellant as well as to control the combustion rate of the propellant. For example, by varying the electrical power and current that passes through the propellant, the combustion rate can be varied and increased over the self-sustaining combustion rate of the propellant up to and including supersonic explosive velocity. Furthermore, stored electrical charge supplied from the electrodes can be used to vary the combustion rate up to and including explosive yield, efficiency or speed of the energy-rich material.
In some examples, the exemplified structures and propellant may be used in combination with a compression device / device such as a pyro-technical / explosive charge (eg, electric lighters, electric matches, spark plugs, detonators, or the like), shock, pneumatic pressurization with compressed gas and / or valve including pressure burst disks to increase reaction pressure and cause faster ignition of the high energy material at and along the electrodes. For example, the threshold current decreases to induce combustion of some of the exemplified fuels with increasing pressure. The structure including the propellant can be included together with a compression device to form a safe ignition system in two stages for the propellant. For example, a power source can provide the fuel with insufficient electrical power to ignite at normal ambient pressure, but with sufficient power for ignition when the compression device is also activated. Likewise, the increase in pressure (and / or heat) l § - L, ', - lí = LLGu' .- "ï .__ Nf * -f kiwi 'LLF' P,» äTFÉülT __ l * l «; Fi: fr ' _ '1. ». 1ffif: r ~ i / lCJF -”, F'l: pil FíÜfšF T ~ iffiif ._ Ii _': i -i, z =>, rion__l * = lf 10 15 20 25 30 8 from the compression device does not ignite the energy-rich material when the electrical power is applied.
Structures exemplified here may find applications in various fields including, but not limited to, defense, aerospace, liquid (a fuel) rocket engines, car engines, airbags, electronics, blasting (mining, oil extraction, eg submersible gas generators for oil wells). for the purpose of breaking stone and improving the recovery of gas and oil), electric firearms, industrial tools, fire-fighting, special effects for entertainment and the like. In a special example, the structures can be used to ignite, choke, extinguish and restart the combustion of high-performance solid or liquid rocket propellants. Furthermore, exemplary methods and systems can be used as gas generators in a variety of applications. Various examples described here can be used in rockets, missiles, spacecraft, aircraft, seagoing vessels, in oil and gas extraction and in land vehicles for propulsion or as a gas generator if necessary. The ability to control the combustion rate of the propellant further makes it possible to tailor pressure waves for specific cutting lithology for maximum fracture propagation as described in Schmidt et al., In Situ Evaluation of Several Tailored-pulse Well-shooting Concepts, SPE / DOE 8934 pages 105-116 , Symposium on Unconventional Gas Recovery, Pittsburgh, PA, USA May 18-21, 1980.
The devices described here comprising an electrically ignitable propellant can be advantageous because they can be electrically controlled and in many examples lack moving parts. Nuclear elements can also be stored in three-dimensional groupings without the need to separate or channel hot combustion gases away from adjacent unused fuel cores. The manufacturing method scales range from those suitable for the semiconductor industry and microchips, such as photoetching and deposition of chemical vapor up to drilling, punching and compression molding in several layers for larger devices. These manufacturing methods can enable mass production of these devices for relatively low cost compared to conventional trustor devices. Figures 1A and 1B illustrate side cross-sectional views and cross-sectional views, respectively, from above, for a first exemplary structure 100 including an electrically ignitable fuel 102. In this example, structure 100 includes a single core element or volume of electrically ignitable propellant 102 to be ignited and / or controlled by the electrodes 101a and 101b. In operation, the electrodes 101a and 101b conduct current through the electrically ignitable propellant 102 and cause combustion thereof. In this particular example, the center electrode 101b includes an insulator 103 for controlling the combustion of the propellant 102; in particular, the application of voltage across the electrodes 101a and 101b initiates combustion at the end of structure 100 (right in Figure 1A). When the combustion of fuel 102 begins, the insulation 103 burns up. As described in more detail below, the polarities and configuration of the electrodes 100a, b, and insulation 103 can be varied to ignite and control the combustion in various ways.
Propellant 102 may be placed with electrode 101a (or a suitable enclosure, not shown) in any manner, for example molded, optionally poured into vacuum or the like, into electrode 101a or other suitable enclosure. The separation between the electrodes 101a and 101b can be varied for efficient combustion of fuel 102, which may include a HIPEP (High Performance Electric Propellant) fuel. HIPEP fuels are described, for example, in AFRL-PR-ED-TR-2004-0076, "High Performance Electrically Controlled Solution Solid Propellant," Arthur Katzakian and Charles Grix. Furthermore, suitable fuels include those described in U.S. Patent Application ___ [U.S. Attorney Reference No. 280.03], "Family of Metastable Intermolecular CompositesUtilizing Energetic Liquid Oxidizers with NanoParticle Fuels In Gel-Sol Polymer Network," and PCT Application __ [U.S. Ombudsman Reference No. 280,071, "Family of Modifiable High Performance Electrically Controlled Propellants and Explosives". In some examples, the propellant is generally flexible when cured and can be used with flexible foils or thin metal layers to form various configurations, such as spiral or roll shapes. F-Qâl -t '-13' _. *. * . F ~ V 'TQ- »f ﬁ l LLF' F ﬁ ÄTf-ÉllT _i" | f * ~ l "'aïr'il (/' ~. _ É} 10 15 20 25 30 10 , can ferb is used in the combustion of propellant 102 and thereby increase the specific force in the equipment device or other type of device. In other examples, the electrodes 101a and 101b may comprise stainless steel or the like which is not consumed during combustion. Furthermore, insulation layer 103, which layer may include Teflon or phenolic coatings, may also be burned with propellant 102. As shown in Figure 1A, insulation 103 does not extend to the end of electrode 101a so that a portion of propellant 102 comes into contact with opposite electrodes. 101a and 101b near the axial surface of structure 100. Insulating layer 103 burns up before the flame front which maintains a contact between the electrodes 101a and 101b and the propellant. The power applied to the electrodes 101a and 101b may be stopped or varied as described herein to control the combustion rate of propellant 102.
An exhaust port may generally be located at the axial top and / or lower axial surface of structure 100. In one example, an enclosure (not shown) may be included to cover the lower axial surface of structure 100 so that propellant 102 is ignited and burned from the upper axial surface and continues downwards. Furthermore, several structures 100 can be grouped or assembled together by utilizing a common electrical ground connection to provide individual combustion control (via control device 120, which may include a power source) with fewer lines. Such groupings can be placed in a suitable matrix to form a uniform solid phase device.
In other examples, as described below in relation to ﬂ gLQ, the fuel may comprise a liquid fuel. Such a device can function in a similar manner as described for solid fuel. Furthermore, in some examples, the liquid propellant may flow, flow, be pumped or otherwise forced into the pre-combustion electrodes 101a and 101b.
Figures 2A - 2C show a fragmentary second exemplary structure, a side perspective view in cross section, and a side cross-sectional view, respectively, of a second exemplary structure 200 including electrodes and an electrically flammable arc _ _ - l ï-x ﬂ- lf '' _.1.f- il .ll} í = ï '134, »LI ÄFF!: _É ^ l * t: .- ER: VlEfr ~ w UC” F ^.' 3TFÄI “É" _ flfïFçr J! QÉÉÉ '"TJ ufvlëffß' i1 *: 'Élf-í__ ~ _" = "15453" _ Ü É fl Wi' i ileff. 10 15 20 25 30 11 bare fuel. In this example, structure 200 includes stainless steel electrodes 201a and 201b, wherein electrode 201b is made of a stainless steel housing that encloses an aluminum housing containing propellant 202.
Furthermore, structure 200 includes an exhaust port / nozzle 212, which may be made of graphite. Those skilled in the art will appreciate that the exhaust port 21 nozzle 212 may be designed and used to control combustion or gas generation of structure 200. Furthermore, two or more exhaust ports may be used in configurations where combustion occurs at two or more ports. In another example not shown, electrode 201a may extend within the exhaust port / nozzle 212 which may facilitate combustion of any fuel particles which are ejected without igniting and which come into sufficient electrical contact with electrode 201a and exhaust port / nozzle 212 and / or electrode 210b so that electric current can be generated.
Figures 2D and 2E illustrate cross-sectional side views of another exemplary structure 201, which includes an electrically flammable propellant 202 and an electrode 201a extending through a nozzle or exhaust region of the structure, for example, through an afterburning chamber region.
The extension of electrode 201a through the end region can prevent or reduce clogging (and any subsequent explosion) by inducing (re) ignition of any incompletely burned fuel.
Figures 3A and 3B illustrate examples of ignition processes for electric propellant in various device configurations. Figure 3A illustrates the combustion process for a structure similar to that in ﬁgLL with an isolated central anode configuration. This special structure and configuration means that the combustion of the fuel is spread over the core ends of the outer cathode. The combustion of the propellant spreads to the left along the axis of the structure in a generally uniform manner as shown. ri ,, ._ t, ~ .llwil-isislcllr.¿- ﬁ r: ;; rl: r.- rip a: Tim gi; riff. f; : E '> if ~' ~ l _ '= fišl ~ f:' ~ ï! lfšl i 3_ É '' ïfßf l Ä ff »-, §1lš 'i iilåf f 10 15 20 25 30 12 In contrast, and with reference to Figure 3B, the fuel ignites widely along much of the entire length of the positive electrode with an inverted polarity and with an uninsulated axial electrode, as shown in the figure (it is noted that only one side of the outer casing / electrode is shown for clarity).
Thus, by varying the polarity and the device (for example with or without combustible insulation) different combustion processes can be achieved.
Figures 4A and 4B show examples of ignition processes for electric fuel for different polarities of the electrodes (it is again noted for clarity that only one side of the outer casing / electrode is shown). Reversing the polarity of the electrodes for an exemplary structure including burn-off base insulation changes the combustion geometry from end combustion to nuclear combustion.
Figures 5A - 5D illustrate exemplary structures including electrodes 501a and 501b and electrically combustible fuel for different polarities and physical configurations. In these examples, electrode 501a is positive and electrode 501b is connected to ground, where electric current is conducted through the ignition fuel at the positive electrode. gr times_6 shows an exemplary "core combustion structure" 600 comprising the wire electrodes 601a, b and electrically combustible fuel 602 with a core region 604 to be provided by combustion gases (it is noted that insulation on the positive electrode 601a, for example, has been omitted here for clarity). other examples, the electrodes 601a, b may also be in the form of flat layers or foils to create a larger ignition surface (not shown) The core region 604 may be formed after the propellant is placed in the structure by drilling, etching, milling, laser milling or any Furthermore, those skilled in the art will recognize that a casing or enclosure, nozzles or exhaust ports, controls, power supplies, compression devices, and other structures may be included in the exemplary structures shown.The core region 604 may -a /: Rais 1 .fw F -ria =: s “ra; tuff / l * .i, _r-liïsr _.:="._ 10 15 20 25 30 13 at least in part lie next to an opening in an enclosure to facilitate channeling of gas and heat to a port or nozzle. ﬁ gL7 illustrates an exemplary "slit combustion structure" 700 including the wire electrodes 701a, b and electrically combustible propellant 702 including a slit 704 formed therein. Slot 704 can allow combustion gases to leave the structure. Slot 704 may be formed after the propellant has been placed in the structure by drilling, etching, milling, laser milling or any other suitable method of removing material. Furthermore, those skilled in the art will appreciate that an enclosure, housing, control unit, power unit, compression device, and other structures may be included in the exemplary structure shown. ﬂ gLß illustrates an exemplary "star geometry structure" 800 including wire electrodes 801a, b and electrically combustible fuel 802 with an open "star region" formed therein. The exemplified geometry may utilize one or more ignition electrodes, for example one or more positive electrodes 801a, together with a single grounded electrode 801b.
Region 804 may be formed after the propellant has been placed in the structure by drilling, etching, milling, laser milling, or any other suitable method of removing material. Furthermore, those skilled in the art will appreciate that a housing, an enclosure, control unit, power unit, compression device, and other structures may be included in the exemplified structure. urg gurg illustrates an exemplary “straw structure” 900 including wire electrodes 901a, b (901a positive and 901b negative in this example) and a plurality of electrically ignitable fuel cores 902. Positive electrodes 901a are illustrated so as to extend substantially or completely along the side of a strip 902 so that combustion begins at the farthest end of the positive electrode 901b (where electrode 901b includes insulation extending almost to its end). One or more core cores 902 may include electrodes where ignition of a core during operation may cause the remaining cores to burn. A number of positive and negative electrodes can be used iii-I l - Tcïï-lu '' _.- '. ::. L .f' ._l líf "'f' '' illffšlïiiïlllï ﬂ fšlu 'FÖEF ti Li F "F -" '«” ï' "fFí l“ - '_.f “-l« i> l>' ¥ 3'i * i: =, '_-. __. F' É i '"f ~ ^ ~ rif = lz »1_¿1 = _“. »1. @ f ~ s J. .ft i lïifåf -lß. 10 15 20 25 30 14 to vary the combustion process and ensure uniform and complete combustion of the cores 902.
Figure 10 illustrates an exemplary "end burner structure" 1000 including the wire electrodes 1001a, b (1001a positive and 1001b negative in this example) and electrically ignitable fuel 1002. In this example, the structure may include only a single grounded electrode 1001b and one or more positive electrodes 1001a. The wired end burner design also contains fewer wires as only one ground connection is needed. For example, with reference to gr times_9, each core 902 may be separately enclosed or isolated from other cores 902 so that each may be selectively and individually ignited and burned.
Figures 11A and 11B illustrate two exemplary methods for initiating combustion of solid electric fuel 1100, which may include a structure described herein, utilizing pressure and electric power. For example, the exemplary structures and the propellant can be used in combination with a compression device such as a pyrotechnic / explosive charge (eg electric lighters, electric matches, match caps, detonators or the like) shock effect, pneumatic pressurization with compressed gas and / or valve, including blasting discs ( pressure burst disk) to increase reaction pressure and induce faster ignition of the energy-rich material at and along the electrodes. For example, the threshold current decreases to induce combustion of some of the exemplified fuels with increased pressure. The structure including the propellant may include a compression device to form a safe two-stage ignition system for the propellant. For example, a power source may provide the propellant with insufficient electrical power for ignition at normal pressures but be sufficient for ignition when the compression device is also activated. Likewise, the pressure increase (and / or heat) from the compression device does not cause ignition of the energy-rich material when the electric power is applied. When the pressure increases at a pressure wave (Figure 11A) or increases in a pressure chamber (Figure 11B), combustion is induced. iv = .1l = ﬂ. f »-TE: ~ i1'_f.l.F -wlalrl .vi r: är l ~ 10 15 20 25 30 15 Figure 12 shows an exemplary structure for activating electrically ignitable liquid fuels. In this particular example, liquid propellant 1202 is contained within structure 1200 and is forced to float past electrodes 1201a and 1201b. Electrode 1201a may further comprise an insulator 1203 placed thereon which does not burn, in an example, so that the liquid propellant 1202 is burned only when it is forced past the electrodes 1201a and 1201b at the far end or at the exhaust end of structure 1200.
In one example, pressure may be introduced into structure 1200 to force or pump the liquid propellant 1202 to and past the electrodes 1201a and 1201b. The liquid propellant may be forced to flow to the electrodes 1201a and 1201b in various ways including mechanical (e.g. a piston or other mechanical devices) methods, gravity, pressure differences, magnetic fields or the like. Furthermore, the speed at which liquid propellant 1202 is forced to the electrodes 1201a and 1201b can be controlled or stopped by means of a control device to vary its combustion speed. In some examples, the volume of electrically flammable propellant includes liquid propellants such as hydroxylammonium nitrate propellant (HAN), propellants described in the applications referred to herein and other pyroelectric materials such as polyvinylidene fluoride, polyvinylidene fluoride-trifluoroethylene copolymers and the like.
Electrically combustible solid and liquid fuels can have various beneficial uses in applications in gas and oil extraction. For example, the use of small electrically controllable explosives can provide advantages when mining in gas and oil sources in terms of safety and predictability, and without extensive borehole damage compared to when using traditional highly explosive substances such as nitroglycerin or gelatin. Furthermore, the use of ﬂ surface fuels, as described here, can be used to enter small diameter cracks and cavities and detonate to form reservoirs. In particular, liquid fuels can be pumped or flowed into cracks (which can originally be created by hydraulic or explosive methods) in 4-1 ~ | -.- _; 1 Laifrifw-itrtrlrt r-i: if / all N. iiz-ï-l '' är, s »-ivrxsvissfiri: fear fra; - ~~ L-: i: 1«: i ». :, stares / sits. 10 15 20 25 30 16 connection to a source or source region and is electrically ignited. The explosion can stimulate the source and expand the oil or gas reservoir for extraction.
Another exemplary application of the structures and methods described herein includes an electronic projectile or cannon device.
For example, Figure 13 illustrates an exemplary structure 1300 for an electrically fired projectile or cannon. As shown, a volume of electrically combustible propellant is suitably connected to electrodes and placed within the structure to propel a projectile as it is fired, for example, the combustion of the propellant drives the projectile from the cylinder.
According to another aspect described herein, a plurality of structures for igniting electrically ignitable fuels (e.g., structures 100, 200, 600, 700, 800, 900, 1000, 1200, or other structures described) may be combined in groups of individually addressable core elements. For example, ﬂ gyrï14 illustrates yet another exemplary structure 1400 for activating an electrically ignitable propellant, wherein the structure comprises a series of propellant strips separated by insulation. Furthermore, a plurality of core elements or structures similar to those illustrated may be combined or packaged in different trustor arrays suitable for different propulsion or gas generating devices. Furthermore, various structures described with respect to solid fuels can generally be designed for use with liquid fuels and vice versa (of course, additional structures such as seals may be needed to store liquid fuels).
Various other structures and configurations of electrodes, exhaust ports and cavities, multiple core arrangements (including vertically packed structures) are further described in U.S. Patent Application 11 / 305,742.
Exemplified methods and structures described herein enable multiple trust units to be produced simultaneously, reducing costs while obtaining a large quantity. The examples are generally scalable and make it possible to include trustors in several sizes in a single set.
The core elements can be in direct contact with each other or separated with i 'i fišê Zøfšz- N-älïfšäïwwïïaiåizi "~ i3l ~ ÜF Fil l' Fgfíiiffššï.
L! f ~ íïhlTFi l'i '* _ lflf: lïarr ﬂ iïj * f. f * - Û l ~ I i * __ f '~. f f l »- '1., iori_i = l1'i; l' lv 10 15 20 25 30 17 conductive electrodes or insulating layers as shown and described. Furthermore, the electrodes may include conductive materials such as copper, aluminum, stainless steel, zirconium, gold, and the like. Insulating materials for molds, casings or for separating cores may include rubber, phenolic plastic, Teflon, ceramic materials and the like. The electrode geometries can be configured to allow specific volumes or surfaces of fuel to ignite individually and / or in combination to achieve the desired pressure / gas generation control.
Electrode geometry and / or conductive coatings can control the combustion of propellants as either inward from the surface or to simultaneously ignite specific volumes. Electrode surfaces can be varied from soft to porous meshes that change surface area on contact with the propellant. Once the hardware composition / stack has been developed, the fuel can be added by casting with or without vacuum depending on the scale. Furthermore, a mandrel can be used to control the casting of the fuel according to the prior art.
It will further be appreciated that various additional features may be included or associated with the structures described, such as power supplies, control devices, electrical pins, connectors, inclusions, electrode structures, and the like. It will be appreciated that one can utilize a chamber shape with a two dimensional array of fuel chambers and stack or stack core elements described herein to form a three dimensional trustor array. Furthermore, various other process techniques can be used and the described process techniques can be performed in a different order or in parallel.
The above detailed description is provided to illustrate exemplary embodiments and is not intended to limit the invention. Those skilled in the art will appreciate that various modifications and variations within the scope of this invention are possible. For example, various examples described herein may be used alone or in combination with other systems and methods, and may be modified to vary applications and design considerations. Thus, this invention is defined by the appended claims and should not be limited by this description.
: U l '- =: ~ fi:; lr: _;:; »~: l N = ... = e ::. F.nlflsr-isclli ala-Yster- trßra ﬂ rrilr Jlvr ﬁ- ll .y; ::; zsí »zrlff, -il :: _ iz. <= 1:> sr ~ _;» f, i.

权利要求:
Claims (30)
[1]
An apparatus for providing electrically initiated and / or controlled combustion, the apparatus comprising: a volume of electrically combustible propellant, wherein the electrically combustible propellant itself can support combustion; and two electrodes capable of igniting the propellant.
[2]
The device of claim 1, wherein the electrically combustible propellant comprises liquid propellant.
[3]
Device according to claim 2, wherein the device can bring the liquid propellant into contact with the electrodes for combustion.
[4]
The device of claim 1, wherein supplying direct current to the electrodes causes combustion of the electrically ignitable propellant upon contact between a positive electrode and the electrically ignitable propellant.
[5]
Device according to claim 1, wherein supply of alternating current to the electrodes causes combustion of the electrically ignitable propellant upon contact between both electrodes and the propellant.
[6]
The device of claim 1, wherein the electrically ignitable propellant is ignited by current passing through it via the electrodes.
[7]
The device of claim 1, wherein at least one of the electrodes comprises an insulating material that insulates a portion of the electrode from the electrically ignitable propellant.
[8]
The device of claim 1, further comprising a power source coupled to the electrodes and capable of varying the current passing through at least a portion of the propellant. i., i '«li) RRl'-Å. 19
[9]
The device of claim 1, further comprising a pressurizing device for increasing the pressure of the electrically ignitable propellant, wherein the amperage required to ignite the electrically ignitable propellant decreases with increasing pressure.
[10]
Device according to claim 9, wherein the current required to ignite the electrically ignitable propellant is not achieved by the device but the pressure increase from the pressurizing device.
[11]
Device according to claim 9, wherein the pressurizing device comprises one or more of an explosive charge, shock effect, compressed gas, pneumatic pressurizing or valve device.
[12]
The device of claim 1, wherein the two electrodes comprise coaxially arranged electrodes.
[13]
The device of claim 1, wherein the two electrodes comprise wire electrodes.
[14]
The device of claim 1, wherein the volume of electrically flammable propellant comprises a cylindrical ring of propellant defining a nuclear region, wherein the nuclear region can channel exhaust gases from the device upon combustion.
[15]
The device of claim 1, further comprising an exhaust port for passing combustion gases.
[16]
The device of claim 15, wherein the electrodes extend through the exhaust port to induce combustion of propellant passing therethrough.
[17]
The device of claim 1, further comprising an exhaust region for passing combustion gases from the structure, the electrodes extending through the exhaust region to induce ignition of propellant passing therethrough. .l-al 4) * .i _ | * ~. ^ nya 'LIF ”F *» THF _ |' -l F »I Ilï msn: r- lvlGRF-% l'ísff = l-: lïïulšlíl: 'íEFY ;: =; @ f. ,, -; as ~ .2orilo: ll. »z__, v 'iv l .jliï 10 15 20 25 30 20
[18]
The device of claim 1, further comprising a projectile that can be propelled by combustion of the electrically ignitable propellant.
[19]
A composition for providing electrical ignition of one or more combustible elements, the composition comprising: a plurality of combustible elements, each combustible element comprising a volume of electrically ignitable fuel capable of supporting combustion itself; and electrodes associated with the plurality of combustible elements, the electrodes being configured to selectively ignite at least one of the plurality of combustible elements.
[20]
The composition of claim 19, wherein the electrodes have electrical contact with at least one of the plurality of combustible elements, wherein combustion of the electrically ignitable propellant is initiated at one of the contact points.
[21]
The composition of claim 19, wherein supplying direct current to the electrodes causes combustion of the electrically ignitable propellant at the point of contact between a positive electrode and the electrically ignitable propellant.
[22]
The composition of claim 19, wherein supplying alternating current to the electrodes causes combustion of the electrically ignitable propellant at the points of contact between at least two electrodes and the electrically ignitable propellant.
[23]
The composition of claim 19, wherein the electrodes comprise wire electrodes.
[24]
The composition of claim 19, wherein an insulating layer is located between two adjacent combustible elements. “Hg _-_ i.1__É 'ff; 'V. __. w .fl-mir i i Per i ri Res erreë li.e.f = lf ﬁ ^ i : ai1'_f 'i ,, irfflw si; ~ 1: »i a» »ir ._l 1- 10 15 21
[25]
The composition of claim 19, wherein an electrode is located between two adjacent combustible elements.
[26]
The composition of claim 19, wherein two adjacent combustible elements are placed in direct contact with each other.
[27]
The composition of claim 19, further comprising an insulating layer.
[28]
A method of stimulating gas and oil sources, the method comprising: administering a volume of electrically ignitable fuel within a source region; ignition of the volume of electrically ignitable fuel.
[29]
The method of claim 28, wherein the electrically ignitable propellant comprises liquid electrically combustible propellant.
[30]
The method of claim 29, wherein the electrically ignitable propellant is pumped into the source prior to ignition. M, i

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法律状态:
2012-06-12| NAV| Patent application has lapsed|

优先权:

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