Systems and methods for collective combustion of core-shell type termite particles

Abstract

A method of generating energy, comprising the steps of providing core-shell type thermite particles and burning a dispersed group of the core-shell type thermite particles to generate heat. The combustion of the core-shell type thermite particles can proceed according to the combustion modes of various core-shell type thermites.

Description

【Technical Field】 【0001】 The embodiments disclosed herein relate to the combustion and / or heating of particles, and in particular to achieving combustion and / or heat generation using an energy particle group such as the combustion of a core-shell type thermite material. 【Background Art】 【0002】 Energy particles or fuels can be burned to generate heat. This heat can be used for power generation, propulsion, environmental heating, energy storage, and other applications. Further, the energy particles can be heated to drive reactions and can be applied to joining and welding applications, additive manufacturing and construction applications, and other applications. 【0003】 In some cases, it may be advantageous to use a combination of fuel and oxidizer to generate heat in an environment where oxygen is absent. Thermite mixtures containing nano- and micro-energy particles conveniently provide a fuel-oxidizer combination that enables high heat output without environmental oxygen. However, the combustion mechanism of such mixtures is not well understood. 【Summary of the Invention】 【Problems to be Solved by the Invention】 【0004】 Accordingly, there is a need for improved systems and methods for the combustion of dispersed thermite particles for various applications. 【Means for Solving the Problems】 【0005】 Some embodiments provide a system and method for generating energy. The system and method include means or steps for providing core-shell type thermite particles and means or steps for burning a dispersed group of core-shell type thermite particles to generate heat. 【0006】 In some embodiments, the core-shell type thermite particles include nanoparticles or microparticles. 【0007】 In some embodiments, the core-shell type thermite particles include nanoparticles and microparticles. 【0008】 In some embodiments, the core-shell type thermite particles are combusted in an environment without gaseous oxygen. 【0009】 In some embodiments, the combustion mode includes initial group combustion. 【0010】 In some embodiments, the combustion mode includes subgroup combustion. 【0011】 In some embodiments, the combustion mode includes critical particle combustion. 【0012】 In some embodiments, the combustion mode includes external particle combustion. 【0013】 In some embodiments, the combustion mode includes sheath combustion. 【0014】 In some embodiments, the combustion of the core-shell type thermite particles occurs within a reactive solar collector. 【0015】 In some embodiments, a dispersed group of the core-shell type thermite particles is generated by a fuel injection device. 【0016】 In some embodiments, the fuel injection device is a rocket injection device. 【0017】 In some embodiments, the fuel injection device includes a multi-point injection system. 【0018】 In some embodiments, the generated heat is applied to an additive manufacturing process. 【0019】 In some embodiments, the generated heat is applied to a propulsion system. 【0020】 In some embodiments, the generated heat is applied to a power generation system. 【0021】 In some embodiments, the power generation system includes a combined cycle power generation system with heat recovery. 【0022】 In some embodiments, the generated heat is utilized for the propulsion of a vehicle. 【0023】 In some embodiments, the vehicle is a submarine. 【0024】 In some embodiments, the vehicle is a spaceship. 【0025】 In some embodiments, the vehicle is an airplane. 【0026】 In some embodiments, the generated heat is applied to wireless power transmission. 【0027】 In some embodiments, the combustion products are provided as reactants for another process. 【0028】 In some embodiments, the combustion products are applied to pyrotechnics. 【0029】 In some embodiments, core-shell thermite particles are combusted in an oxygen-containing environment. 【0030】 In some embodiments, the generated heat is stored as energy for further use. 【0031】 In some embodiments, the combustion of core-shell thermite particles occurs on Earth. 【0032】 In some embodiments, the combustion of core-shell thermite particles occurs in space. 【0033】 In some embodiments, the core-shell type thermite particles are energized using magnetic induction. 【0034】 In some embodiments, the heat generated is applied to welding, sintering or joining. 【0035】 In some embodiments, the core-shell type thermite particles are moved using magnetohydrodynamics or magnetic confinement and energized using magnetic induction. 【0036】 In some embodiments, the system or method is autonomous and / or semi-autonomous. 【0037】 Other aspects and features will become apparent to those skilled in the art upon review of the following description of some exemplary embodiments. 【Brief Description of the Drawings】 【0038】 The drawings included herein are for the purpose of illustrating various examples of the articles, methods, and apparatuses herein. See the drawings. 【0039】 【Figure 1】 It is a figure showing core-shell shell thermite combustion according to an embodiment. 【0040】 【Figure 2】 It is a figure showing the temperature distribution of core-shell shell thermite combustion according to an embodiment. 【0041】 【Figure 3】 It is a figure depicting the combustion of a dispersed group of core-shell type thermite according to an embodiment. 【0042】 【Figure 4】 It is a graph depicting the normalized mass fraction and temperature of the combustion of a dispersed group of core-shell type thermite according to an embodiment. 【0043】 【Figure 5】 A graph depicting the normalized radius-direction mass flow rate with respect to the normalized radius for different group combustion numbers (G) according to an embodiment. 【0044】 【Figure 6A】 A graph depicting the group mass loss rate with respect to the change in group number according to an embodiment. 【0045】 【Figure 6B】 A graph depicting the group mass loss rate with respect to the change in group number according to an embodiment. 【0046】 【Figure 7A】 A diagram showing the internal group combustion mode according to an embodiment. 【0047】 【Figure 7B】 A diagram showing the external group combustion mode according to an embodiment. 【0048】 【Figure 8A】 A diagram illustrating the individual particle combustion mode according to an embodiment. 【0049】 [[ID=3-eight]] 【Figure 8B】 A diagram illustrating the initial group combustion mode according to an embodiment. 【0050】 【Figure 8C】 A diagram showing the partial group combustion mode according to an embodiment. [[ID=4-six]] 【0051】 【Figure 8D】 A diagram showing the critical particle combustion mode according to an embodiment. 【0052】 【Figure 8E】 A diagram showing the external particle combustion mode according to an embodiment. 【0053】 [[ID=6-one]] 【Figure 8F】It is a diagram showing the sheath combustion mode according to the embodiment. 【0054】 【Figure 9A】 It is a diagram showing the external sheath combustion mode according to the embodiment. 【0055】 【Figure 9B】 It is a diagram showing the internal sheath combustion mode according to the embodiment. 【0056】 【Figure 10A】 It is a diagram showing the required number of particles (N) for different group combustion numbers according to the embodiment. 【0057】 【Figure 10B】 It is a diagram showing the ratio of the cloud radius to the particle radius with an inter-particle spacing for different group combustion numbers (G) according to the embodiment 【0058】 【Figure 11】 It is a diagram depicting various combustion modes of core-shell thermite group combustion according to the embodiment. 【0059】 【Figure 12】 It is a diagram depicting a solar collector concentrator according to the embodiment. 【0060】 【Figure 13】 It is a diagram depicting various rocket configurations according to the embodiment. 【0061】 【Figure 14】 It is a diagram depicting the configurations of various fuel injection devices according to the embodiment. 【0062】 【Figure 15】 It is a diagram depicting the spray nozzle configurations of various fuel injectors according to the embodiment. 【0063】 【Figure 16】This is a diagram depicting various rocket configurations according to the embodiments. 【0064】 【Figure 17】 This is a diagram depicting various rocket configurations according to the embodiments. 【0065】 【Figure 18】 This is a diagram depicting various fuel injection configurations according to the embodiments. 【0066】 【Figure 19】 This is a diagram depicting various rocket configurations according to the embodiments. 【0067】 【Figure 20】 This is a diagram depicting various fuel injection configurations according to the embodiments. 【0068】 【Figure 21】 This is a diagram depicting various fuel injection configurations according to the embodiments. 【0069】 【Figure 22】 This is a diagram depicting various fuel injection configurations according to the embodiments. 【0070】 【Figure 23】 This is a diagram depicting various spray fuel injection configurations according to the embodiments. 【0071】 【Figure 24】 This is a diagram depicting various spray fuel injection configurations according to the embodiments. 【0072】 【Figure 25】 This is a diagram depicting various spray fuel injection configurations according to the embodiments. 【0073】 【Figure 26A】 This is a diagram depicting various fuel injection configurations according to the embodiments. 【0074】 【Figure 26B】 A diagram depicting various fuel injection configurations according to an embodiment. 【0075】 【Figure 27】 A diagram depicting a power generation system according to an embodiment. 【0076】 【Figure 28A】 A diagram depicting a rocket system according to an embodiment. 【0077】 【Figure 28B】 A diagram depicting a rocket system according to an embodiment. 【0078】 【Figure 29】 A table comparing a conventional analysis model and a core - shell type thermite combustion model according to an embodiment. 【0079】 【Figure 30】 A table classifying intermediate models of nanothermite combustion according to an embodiment. 【0080】 【Figure 31】 A table classifying various nanothermite group combustion regimes with lower and upper limit values of the group combustion number (G) according to an embodiment. 【0081】 【Figure 32】 A flowchart showing a method of energy production by combustion of a group of dispersed core thermite particles according to an embodiment. 【Embodiments for Carrying Out the Invention】 【0082】 To provide examples of each claimed embodiment, various devices or processes are described below. The embodiments described below do not limit the claimed embodiments, and the claimed embodiments may be directed to processes or devices different from those described below. The claimed embodiments are not limited to devices or processes having all of the features of any one of the devices or processes described below, nor are they limited to features common to a plurality or all of the devices described below. 【0083】 Nanothermites are often metastable intermolecular complexes (MICs) that contain metals and metal oxides mixed at the nanoscale and can undergo exothermic chemical reactions with sufficient energy input. The nanosized components, namely the metal fuel and the solid oxidizer, are often physically mixed to facilitate rapid ignition and reaction. The chemical reaction of the MIC occurs by solid diffusion of oxygen. Spherical core-shell nanothermites with a nanosized metal core encapsulated by a thin oxide shell have been developed. This shell can be either metallic or non-metallic. To maximize the contact area between the fuel and the oxidizer, the diffusion length and time scale are minimized. Core-shell nanothermites have many advantages, especially since the outer shell is thermodynamically stable, allowing the reaction to occur as discrete solid particle combustion even in the absence of gaseous oxygen. This is different from classical physically mixed nanothermite combustion, which requires physical proximity of the fuel and oxidizer particles and thus cannot react in the dispersed phase. 【0084】 Nanothermites are characterized by high reactivity and energy density and can be tailored for specific applications. Due to their highly exothermic reactions, a dispersed group of core-shell nanothermite particles can ignite adjacent particles through heat diffusion and convection of the heated combustion products, leading to self-sustained combustion. However, since the particle reactions are driven by solid oxygen diffusion, combustion in the dispersed phase is not limited by the availability of gaseous oxygen. Instead, it is limited by heat and mass transfer between the particles. Furthermore, assuming that the continuous phase has no chemical influence on the core-shell structure of the MIC, the reaction can occur in a vacuum, water, or other inert environments. Additionally, the heating and combustion reactions of a group of core-shell nanothermites and / or high-energy particles can be utilized in an oxygen-rich environment. Due to such characteristics, core-shell nanothermites are suitable for many new applications, including terrestrial and space technologies. 【0085】 Many studies have been conducted on the combustion of densely packed nanothermite particles. Physically mixed solid fuel and oxidizer particles are often mechanically compressed, and their combustion characteristics have been investigated. The packing density, measured by the theoretical maximum density (TMD), significantly affects the flame propagation speed through the connected pellets. The flame front progresses mainly convectively (when TMD is low) or conductively (when TMD is high), and the flame propagation speed varies from u(10) m / s when TMD is high to u(1000) m / s when TMD is low. Recently, the sensitivity of the flame propagation speed to TMD was evaluated using numerical models. However, the combustion characteristics of a dispersed group of core-shell nanothermite particles are not well established because the ignition and combustion of individual particles depend on heat and mass transfer between the particles, which is the focus of this study applying a theoretical perspective to this problem. 【0086】 Under sufficient heating, the combustion of a single core-shell type nanothermite particle shares many characteristics with the combustion of a single particle of carbon or a droplet. However, the main difference is the solid diffusion of oxygen that occurs within the particles in the nanothermite. The reaction of a dispersed group of core-shell type nanothermite particles is not limited by the presence of gaseous oxygen (due to the solid-phase oxidizer transport from the shell), so the combustion dynamics of multiple dispersed particles are significantly different from the classical multiphase combustion regime. Collective combustion is the combustion characteristic of an aggregate of particles and is useful for modeling the combustion of dispersed particles. In the case of dispersed droplets or solid particles, several different "group combustion modes" have been recognized. Classically, these different collective combustion modes are governed by the availability of oxygen within the dispersed clusters. Therefore, a dispersed group of core-shell type nanoenergy particles will have different collective combustion characteristics. 【0087】 The theory and models of metal combustion in gaseous oxidizers have long been the subject of mathematical research. Previous studies have examined the combustion regime of metal particles and concluded that the oxidizer and pressure have a significant impact on the thermodynamics of combustion and the combustion regime of the particles. Metal vapors react immediately with oxygen upon contact, and the vapor pressure of the metal only increases when close to the flame temperature. In the collective combustion process, it is difficult to imagine a scenario where a cloud of metal vapor burns with external oxygen. However, metal vapors can burn with external oxygen caused by high-temperature plasmas, laser-induced plasmas, electrostatic discharges, the chemical reaction region behind a detonation front, and other non-conventional combustion applications. Under these conditions, emissions from metal vapors (such as Al, B, etc.) and oxidized species (such as AlO, BO2, etc.) have been observed. In other previous studies, the scaling of flame propagation in a particle cloud has been investigated. In these studies, analytical examinations using a continuum model and numerical examinations using a discrete source model have been carried out. As a result, it has been found that at the limit of high-speed combustion compared to the inter-particle diffusion time, flame propagation cannot be predicted deterministically. 【0088】 In a very high-density metal cloud, the reaction resembles that of aggregates of metal particles, and the reaction rate may be limited by the availability of the oxidizer. However, this does not occur in the case of nanothermites. The increase in the local temperature within the particle suspension due to reactions at multiple particle sites is called the collective effect. Since the particles self-heat when reacting at multiple particle sites, heat loss to the surroundings is reduced. Compared to isolated particles, the collective effect accelerates the heating rate within the cloud, resulting in faster combustion. Previous studies have found that particles burn at all sizes and there is no minimum size for ignition. 【0089】 Clusters of dispersed particles can appear in turbulent flows where discrete particles preferentially concentrate due to the kinematics of turbulence. This preferential clustering of discrete particles becomes particularly important under external radiative heating or inductive heating. Particle heating can locally heat the fluid phase, locally generate turbulence, and further promote clustering. A non-uniform particle distribution hinders heat conduction between phases, generating hot and cold zones in the continuous phase. This is a particularly important problem in solar collectors containing many particles. If these particles are reactive, clustering can affect the combustion dynamics of these dispersed particles. In the case of core-shell nanothermite particles, the influence of local clustering on the collective combustion characteristics remains unclear. 【0090】 In this specification, a theoretical explanation based on previous analytical studies is proposed for the collective combustion characteristics of dispersed spherical core-shell type nanothermites. The subject of the present disclosure is that core-shell nanothermites are different from classical collective combustion theories in that they do not exhibit group combustion behavior with oxygen limitation because they contain both fuel and oxidizer within discrete particles. The role of collective combustion theory is not only to understand the combustion of a dispersed group of reactive particles, but also to help understand ignition time, combustion rate, heat release, flame structure, and other combustion characteristics. Considering ease of handling, the combustion rate theory is simplified to a single step with approximated rate theory parameters, ignoring additional forces that occur at the nanoscale. Most dispersed nanoparticles aggregate into micro-sized particles containing hundreds or thousands of discrete core-shell nano-sized particles. These simplifications provide an easy-to-handle framework for describing heat conduction between particles of dispersed core-shell type nanothermites. This framework can be extended in various ways to support applications, processes, and / or methodologies, and to construct and / or develop various combinations of other combustion and / or heating, or to some extent, two combinations. 【0091】 Single isolated particle combustion In the present disclosure, spherical core-shell nanoparticles composed of an aluminum core and a copper oxide shell are considered. However, in other embodiments, the theory described herein is generalizable to any core-shell type nanothermite material. In the dispersed phase, the nanoparticles tend to aggregate by intermolecular forces and electrostatic forces, forming aggregates of particles with diameters on the micrometer scale. Although core-shell particles are used on the nanoscale in most practical applications, in the present disclosure, nanoparticle aggregates are regarded as isolated particles. This simplification allows us to neglect nanoscale forces that would otherwise impede the ease of analysis. It should be noted that above the nanometer scale, as shown by 100 in FIG. 1, the analysis is scale-independent. FIG. 1 is an illustration of a core-shell nanothermite and the corresponding nanothermite aggregate that can be dispersed in a carrier phase for combustion. However, the combustion time varies with the length scale (size) of the particle aggregates. As seen in Equation (17) corresponding to the particle consumption time, when the particle size (ds,0) doubles, the particle consumption time (ts) quadruples. 【0092】 Quasi-steady assumption for single-particle combustion. First, consider the simplest case of the combustion of an isolated core-shell nanothermite particle. Under sufficient heating, oxygen from the shell undergoes solid diffusion and a chemical reaction with the pure metal core occurs, as shown in FIG. 1. Only the heterogeneous redox reaction near the surface involving oxygen in the aluminum core and the copper oxide shell is considered. Note that this reaction is independent of the availability of gaseous oxygen around the particle surface. To simplify the analysis, a completely spherical particle is considered where the solid reaction occurs at the ends. Depending on the composition of the nanothermite, in addition to solid or liquid metal oxides, gas is formed as a combustion product. In the specific case of an aluminum core with a copper oxide shell, as shown by 200 in FIG. 2, copper vapor is formed. FIG. 2's 200 shows the combustion of a single solid nanothermite. The combustion of this single particle exhibits the same behavior as high-concentration population combustion. 【0093】 In this way, a concentration gradient is formed in the gas phase, and as a result, copper vapor diffuses from the particle surface. The present disclosure is interested in obtaining the concentration profile of copper vapor. Under steady conditions, this profile must be adjusted such that the combustion of the nanothermite is equal to the stoichiometric release of copper vapor at the particle surface. The migration rate of copper vapor can be evaluated using the mass conservation equation. Considering mass conservation, under the quasi-steady assumption, the regression rate of the particle is proportional to the generation of vapor. Therefore, the temperature-dependent heat release used in previous studies is implicitly explained within the gaseous products. Furthermore, due to the small thermal mass of these particles and the fast combustion time scale, it is assumed that the temperature within the particle is not constant but uniform. Similarly, it is assumed that the thermophysical properties of solids such as specific heat do not depend on temperature. Finally, the combustion rate of the nanothermite was evaluated using stoichiometry. 【0094】 There are several other assumptions in this formulation. Combustion and radiative heat release from hot particles are considered negligible, but this is a simplification and may not be valid in all cases. The kinetic energy and shear forces of the carrier phase are ignored. Finally, it is assumed that there is no chemical reaction with copper vapor in the carrier phase. Based on these assumptions, mass conservation, vapor product transport, and the energy equation were considered. The mass consumption rate (ṁs) of the solid particle is as follows. 【0095】 [Number] (1) 【0096】 Here, rs is the radius of the particle, ρs is the density of the particle, ρ is the density of the gas phase (kg / m3) including the vapor density of the copper species, u is the velocity of the mixture gas at any spherical cross-section in the gas phase, ṁ is the mass flux rate at any spherical cross-section in the gas phase, and ṁs is the mass generation rate of the vapor product. Here, since the mass (ms) of the particle decreases with time, a negative value ṁs < 0 is obtained, and similarly, the mass flux is positive. The conservation of species per unit surface area in the stationary environment of the gas phase is as follows. 【0097】 [Mathematics] (2) 【0098】 Here, Y is the mass fraction of copper vapor species at a given location, D is the diffusion rate of copper vapor species in the carrier phase, ρ is the vapor density of copper species, and ∂y / ∂r is the mass fraction gradient of copper vapor. The above equation is a simplified form of Equation (1) considering 4πr2ρu = ṁ. There are two methods to integrate the above equation as follows. (1) From the particle surface (r = rs) to the radial position r, or (2) From the radial position r to a distant position (r = r∞) However, regardless of which boundary condition is adopted, the final result is the same. The equation of the above conservation law after integration can be written as follows. 【0099】 [Mathematics] (3) 【0100】 [Mathematics] (4) 【0101】 The higher the mass burning rate of the nanotermite, the higher the mass transfer number (B). Thus, from the perspective of known boundary conditions, the accurate value of a certain mass flow rate (ṁ) parameter can be obtained. 【0102】 The storage capacitor 306 stores charge from the drain current in order to function as a short-term memory for the stored signal. 【0103】 [Mathematics] (5) 【0104】 The above is the constant mass flow rate at any spherical cross-section of radius r with respect to the predetermined mass fraction (Ys) of the vapor product in the immediate vicinity of the particle and the mass fraction (Y∞) of the vapor product far from the particle. In the general case of the above equation, Ys > Y∞. This results in a mass flow rate directed outward from the particle (ṁ > 0). In the limiting case where Ys = Y∞, the mass flow rate is zero (ṁ = 0). Therefore, the final solution for the change in the mass fraction (Y) of the vapor product at any radial position (r) is obtained by substituting Equation (5) into Equation (3). 【0105】 [Number] (6) 【0106】 Assuming that the mass flow rate of the vapor product far from the particle is zero (Y∞ = 0), this can be further simplified as follows. Y(r)=1-(1-Ys)rsr The energy conservation within the region is given by the following equation. 【0107】 [Number] (7) 【0108】 Here, T is the thermodynamic temperature at the radial position (r). Similarly, λ and cp are the thermal conductivity and specific heat of the mixed gas, respectively. 【0109】 Considering the boundary condition ṁ = 4πρr2, the solution of Equation (1) is given as follows. 【0110】 [Number] (8) 【0111】 Here, the parameter Qs is given as follows. 【0112】 [Number] (9) 【0113】 Therefore, the solution for the temperature is as follows. 【0114】 [Number] (10) 【0115】 The limiting cases can be verified from the above equation. For example, at the particle surface (r = rs), T = Ts. This represents the exact boundary condition at the particle surface. A similar sanity check can also be performed at a radial position far from the solid particle (r → ∞). Furthermore, in the limiting case where the temperature at the surface is equal to the temperature of the free stream, the solution of the above equation can be simplified to T = Ts = T∞. 【0116】 The diffusion of combustion products into the surrounding carrier gas is characterized by the Lewis number Le = α / D = λ / (ρDcp). This relates the thermal diffusivity α = λ / (ρcp) of the mixture to the mass diffusivity D. To maintain mathematical tractability, the Lewis number is assumed to be 1. This means that the mass diffusion (mass diffusivity of copper vapor with respect to the mixed gas) and the thermal diffusion are approximately equal. Considering a single Lewis number (i.e., the thermal diffusivity of the mixture is (α = λ / (ρcp)) and the diffusivity of the species is (D), and the two are equal (λ / (ρcp) = D), the above equation is simplified as follows. 【0117】 [Number] (11) 【0118】 Here, the thermal conductivity number (BT) is as follows. 【0119】 [Number] (12) 【0120】 To understand the physical meaning of the thermal conductivity (BT), assume that the copper vapor product exits with an energy of ṁcp(Ts - T∞). When this thermal energy is supplied to the copper vapor at Ts, the amount of potential energy that moves is ṁcp(Ts - T∞). The higher the thermal conductivity BT, the higher the potential for heat conduction in the surrounding gas phase. Comparison with Other Single-Particle Combustion Models 【0121】 In previous studies, analytical models for the quasi-steady single-particle combustion of various fuels were developed. Here, these models are compared with the core-shell nanothermite combustion model, and the comparison is summarized in Table 2900 of Figure 29. Spray Combustion 【0122】 Spray combustion has two basic elements: the combustion of individual fluid droplets and the combustion of aggregates of droplets. Intuitively, the combustion of a single droplet generally appears in a lean spray, while aggregates of droplets are seen in a more concentrated flow. It should be noted that the size of these clusters is much smaller than the integral length scale of the turbulence. Numerous studies have been conducted on the steady combustion and two-stage ignition of individual droplets (especially under microgravity conditions). However, the literature on collective combustion is quite limited. In the case of single-droplet combustion, the thermal conductivity corresponding to Equation (12) of the nanothermite is as follows. 【0123】 【Equation】 (13) 【0124】 In the above equation, T, Ts, b, cp, hC, and Lh are the temperature at a position away from the fuel droplet, the boiling point of the liquid fuel, the specific heat of the gas, the specific enthalpy of the combustion reaction, and the latent heat of vaporization, respectively. Similarly, YO2∞ represents the oxygen mass fraction at a position far from the droplet, and cO2 represents the oxygen stoichiometric coefficient in the reaction. Here, to clarify the physical interpretation of B, the energy of the reaction products escaping from the surface (cp(T∞ - Ts) + hcYO2∞ / cO2) was considered. By supplying this thermal energy to the non-combustible liquid fuel at the temperature of Ts, the physical quantity of the fuel that may vaporize becomes ((cp(T∞ - Ts) + hcYO2∞ / cO2) / Lh). In droplet combustion, the possibility of converting the liquid fuel into vapor is measured by the mass of the fuel per stoichiometric amount of air and is known as the transfer number B. In this sense, the larger the value of B, the higher the overall evaporation level. As a result, the combustion of fluid particles is promoted. Combustion of coal / char 【0125】 In previous studies, theoretical analyses were performed to elucidate the combustion characteristics of coal particle clusters in a stationary flow. Therein, the mass transfer number of a single coal / char particle was determined as follows 【0126】 【Equation】 (14) 【0127】 Here, YCO2, YCO2,s, YO2, YO2,s, cO2, and cCO2 represent the mass fraction of carbon dioxide (CO2), the mass fraction of carbon dioxide (CO2) on the surface of carbide particles, the mass fraction of oxygen (O2), the mass fraction of oxygen (O2) on the particle surface, and the stoichiometric coefficients of oxygen and carbon dioxide in the reaction, respectively. In this combustion reaction, the main product is carbon dioxide, and the reaction between carbon and oxygen is negligible. Furthermore, each particle releases carbon monoxide based on the oxidation of carbon atoms and the reduction of carbon dioxide. This carbon monoxide is later oxidized to produce carbon dioxide, providing a homogeneous gas phase. Therefore, they proposed the following one-step reaction scheme: CO + 1 / 2O2 → CO2. Considering this reaction, if the oxidation rate of carbon monoxide is high, the oxygen concentration in the particle cloud decreases. Also, if diffusion control is ensured for the combustion of all carbon particles in the carbon cloud, the global rate of carbon cloud combustion is considered to be independent of the oxidation of carbon monoxide. 【0128】 Particle consumption time and the D-square law 【0129】 Consider equations (1) and (4) at the particle surface and simplify by replacing the particle radius with the diameter (ds). 【0130】 【Number】 (15) 【0131】 Here, kq is a constant corresponding to the slope of the straight line relationship between the square of the diameter (ds2) and time (t). Physically, kq represents the combustion rate of the nanotemit particles. It should be noted that the terms on the right side of the above equation are constant over time, and the solution of the linear differential equation of the above equation is as follows. 【0132】 【Number】 (16) 【0133】 Here, ds,02 is the initial size of the particles. Therefore, the time it takes for the particles to be completely consumed (ds = 0) is calculated as follows (assuming complete and idealized combustion occurs). 【0134】 [Number] (17)) 【0135】 The particle diameter decreases linearly with time. It takes a finite time (ts = ds,02 / kq) for the particles to be completely consumed. This is an approximation that is orders of magnitude off, considering the non-uniform structure of the core-shell type nanothermite. For other solid fuels and liquid fuels, the scaling relationship between the lifetime and the particle diameter (td ∝ ds,02) has been shown previously. 【0136】 Returning to the initial assumption of quasi-steady combustion, it is assumed that the particles are stationary and the generation and expansion of the gas are completely symmetric. In the above analysis, the relative velocity of the nanothermite particles with respect to the gas phase is not considered. However, it has been empirically found for other fuels that the scaling relationship of Equation (17) holds even when the gas velocity is superimposed. Previous studies that developed correlation equations for droplet evaporation described the correction factor ku in the presence of a free-stream gas velocity (u∞). Therefore, the modified ratio obtained by dividing ku by kq as a correction in the presence of a certain flow is ku / kq = aReb. Here, Re is the Reynolds number, a is generally about 0.3, and b is also about 0.25 - 0.3 in droplet evaporation. For these values, the dependence of ku / kq on various Re is relatively weak. Therefore, the above relationship provides motivation for researchers to measure the time variation of the nanothermite diameter during combustion in more detail. Mass Conservation and Collective Combustion 【0137】 A simplified analytical framework was provided above to characterize the combustion of discrete, quasi-steady, spherical core-shell type nanothermite particles. In contrast, here we have derived an analytical approach to describe the combustion of a nanothermite cloud. There has been no prior disclosure regarding the thermally driven particularities of core-shell nanothermite combustion. The theoretical approach adopted in this disclosure follows similar lines as those used in spray combustion and pulverized coal combustion, but is adapted to the specific properties of nanothermites. 【0138】 The dispersed core-shell type nanothermite particles are considered as a spherical particle swarm (however, the results can be easily extended to cylindrical or planar clouds). Consider a group with a radius RG containing nanothermite particles as shown at 300 in Fig. 3. This group is essentially a two-phase region, consisting of discrete solids and a continuous gas phase. The gas phase inside the group is divided into a film region (region C, near the particles) and a gas intermediate region (region B shown in Fig. 3). There is a separation of length l between the particles. A dispersed aggregate of core-shell type Al / CuO nanothermite is considered, and copper vapor is generated when the aluminum core oxidizes. The copper vapor is formed at the particle surface and diffuses through the film region into the gaseous intermediate region. The heat conduction and the rate of nanothermite combustion are determined by the diffusion of copper vapor. The copper vapor finally diffuses into the outer region (region A). To simplify the collective combustion analysis, two additional assumptions were considered. The first assumption is that ds / l << 1 and it is a continuum in the group region. As a result, the particles are recognized as point sources. The second assumption is the existence of a uniform, monodisperse cloud of nanothermite particles. 【0139】 In a classical collective combustion region, an internal region of unburned fuel is formed by the evaporation of liquid fuel or the pyrolysis of solid fuel (due to oxygen deficiency), and a flame is formed around clusters of these particles. During this change, the flame of individual particles migrates to the flame around the particle group. In the case of nanothermites, the oxidizer is available within each particle. That is, this is a type of nanoreactor without restrictions on the availability of the oxidizer, and each particle functions as a microreactor with the ability to ignite when reaching above the ignition temperature. Therefore, the combustion kinetics of this group are purely problems of heat and mass transfer. 【0140】 It is worth noting that the heat release is a function of temperature. The temperature change within the cloud plays an important role in collective combustion, which depends on the mass transfer of copper vapor above the ignition temperature. Since region B in Figure 3 is the region of the average mass and average temperature within the interstitial field, it is reasonable to consider that the combustion reaction occurs uniformly. Therefore, the group is regarded as a homogeneous phase. It has been previously demonstrated for the group interaction system that all particles must be at the same temperature (Ts) for thermodynamic equilibrium to occur in the steady state. Therefore, the reaction rate in each configuration was considered constant in the model. 【0141】 In the group method or cloud method described in this specification, the statistical average of the mass source is obtained. The mass conservation of the copper vapor of all particles in the control volume enclosed within the cross-section between radius r and r + dr is given by the following equation. 【0142】 [Number] (18) 【0143】 Quasi-steady assumption of collective combustion - The governing equations of the above collective combustion hold under the following assumptions. The combustion time of each particle is long enough to establish a steady state on a continuous gas field of size O(RG). The combustion of each particle and its influence can be regarded as a point source of mass and energy for the gas field. The ignition of each particle is governed by the ambient temperature of the gas phase. 【0144】 An appropriate inter-particle vapor product propagation model can determine how a steady combustion field is realized within the theory of group combustion. The solution of the governing equations above was determined according to the approach adopted in the literature. Here, the solution for a monodisperse and uniformly distributed group is shown. The radial variations of the mass fraction and temperature are as follows. 【0145】 【Number】 (19) 【0146】 【Number】 (20) 【0147】 Here, MSC = ln(1 + B) is the dimensionless velocity of sheath combustion as defined in Equation (30). The group combustion number (G) can be expressed as follows. 【0148】 【Number】 (21) 【0149】 【Number】 (22) 【0150】 【Number】 (23) 【0151】 Here, n is the particle density (unit: m-3), rs is the particle radius, N is the total number of particles in the group, SS is the surface area of particles in the unit volume, σF is the ratio of fuel to air volume, ms,G is the total mass of particles in the group, and φ = 1 - ρTGD / ρs is the virtual porosity of particles in the group. ρTGD = ms,G / 4πR3G is the theoretical group density. 【0152】 The G number represents the relationship between the total number of particles (N) and the normalized inter-particle spacing l / rs within the cluster. Since the core-shell particles are local sources of heat and mass, the physical meaning of G can also be determined from Eqs. (19) and (20) as the ratio of the characteristic heat release rate of the exothermic reaction to the heat transport rate of the products (as copper vapor) within the group / cloud. 【0153】 The normalized mass fraction and temperature of the nano-thermite group combustion obtained using Eqs. (19) and (20) are plotted on graph 400 of Fig. 4. This is a reasonable observation because the evaporation of droplets and the combustion of core-shell type nano-thermites depend mainly on temperature rather than the presence or absence of an oxidizer. The changes in the temperature (T) and mass fraction (Y) of the nano-thermite combustion products, such as in Eqs. (19) and (20), are different from those in spray combustion and coal combustion. However, the normalized Shvab-Zeldovich variables for spray combustion (Φ = βF-02 - βF-02,∞βsF-02 - βF-02,∞, where βF-02 = YFcF - Y02c02) and coal combustion (Φ = 1 + βC02-021 + βC02-02,∞, where βC02-02 = YC02cC02 + Y02c02) are similar to those of the dimensionless temperature (and dimensionless mass fraction) of the nano-thermites (Eqs. (19) and (20)). 【0154】 Group mass loss rate and correction factor 【0155】 Due to symmetry, the outflow of copper vapor increases gradually in the radial direction (r) from the center of the cloud (r = 0) towards the periphery of the cloud (r = RG). The mass flow rate of the cloud at the radial position (r) is determined as follows by summing up the total particle sources (from Eq. (4)). 【0156】 【Number】 (24) 【0157】 Furthermore, the total mass flow rate (m dot G) at the boundary and outside the cloud is as follows. 【0158】 [Number] (25) 【0159】 Therefore, the normalized radial mass outflow rate of the group is given by the following equation. 【0160】 [Number] (26) 【0161】 [Number] (27) 【0162】 The graph 500 in FIG. 5 plots the normalized radial mass outflow rate (ṁr / ṁG) against the normalized radius (r / RG) for different group combustion numbers (G). 【0163】 As G increases, it is observed that most of the combustion occurs near the group periphery, such as sheath combustion for G > 100. 【0164】 Furthermore, the dimensionless mass group rate (MG) can be obtained as follows. 【0165】 [Number] (28) 【0166】 The mass flux in the cloud is normalized by (4πRGρD), similar to the normalization term for single-particle combustion shown in Equation (5). The normalized mass flux considered in nanothermite group combustion is described so that the conditions of the cloud and single-particle combustion can be compared. Solutions for the group mass loss rate are provided in two forms. First, the ratio of the dimensionless nanothermite group combustion (MG) to the dimensionless sheath combustion rate (MSC) is defined as follows. 【0167】 [Number] (29) 【0168】 Here, the dimensionless sheath burning rate (MSC) is obtained as follows from Equation (4). 【0169】 [Number] (30) 【0170】 As the magnitude of G increases, as indicated by the slopes of graphs 600 and 602 in FIGS. 6A and 6B, the above ratio (MG / MSC) tends to reach a unit value. In the limiting cases (e.g., G < 0.1 and G > 100), it can be approximated as 1 - (tanh(G1 / 2) ≒ CG + 3. Before proceeding to the next form of the group mass loss rate, it is important to note that the group combustion of nanotemitters is classified based on the magnitude of MG / MSC and is also classified based on its group combustion number (G). Next, the group mass loss rate can be normalized by integrating the isolated group combustion rate (MISO,G) as follows. 【0171】 [Number] (31) 【0172】 Here, the dimensionless isolated group combustion is provided as follows by considering Equation (5) for single particle combustion. 【0173】 [Number] (32) 【0174】 Graph 602 in FIG. 6B plots the change in M with G, considering a monodisperse and uniform nanotemitter group. When the magnitude of G is about 0.5, M corresponds to about 80% of the isolated particle combustion. When the collective combustion number (G) is 100, the particle combustion rate is only about 10% of the isolated particle combustion rate. As G approaches zero, the ratio M tends to approach 1. 【0175】 In the present disclosure, the species diffusion is treated as being controlled, and the problem is considered from a thermal perspective. Based on FIG. 4 of RG, the collective combustion is essentially a cloud of high-temperature combustion particles that lose heat to the surroundings. Graph 600 in FIG. 6A shows the results of the group mass loss rate in the form of the change in MG / MSC with the group number (G). Graph 602 in FIG. 6B shows the group mass loss rate in the form of the change in M with the group number (G). 【0176】 For a group of particles where G approaches zero, each particle within the group is confined in a gas at temperature T∞. Here, in the range of MG / MSC ≤ 0.1, it is considered that MG / MSC → 0. This case of isolated group combustion corresponds to a group number G < 0.5, and when M > 0.8, M → 1. As the magnitude of G increases, each particle within the group reaches the same temperature as the particle surface (TPS), and the concentration of copper vapor corresponds to the saturation state. Therefore, a compact group of particles functions as an isolated single large particle placed in the surrounding fluid of T∞ and Y∞. Under these conditions, the group of particles is considered to burn in the sheath combustion (SC) region. As the magnitude of G increases, the specific MG / MSC reaches 1, which is considered in the range of MG / MSC > 0.9. This corresponds to a group number G > 100 with M → 0 and is in the range of M ≤ 0.03. This change in M does not indicate that the combustion rate of the nanothermite decreases as G increases. 【0177】 The above range of the group number (G) defines the group mass loss rate in the sheath combustion mode (G > 100 with MG = MSC) and the isolated combustion mode (G < 0.5 with MG = MISO,G) by equations (29) and (31), respectively. The change in the group mass loss rate (MG / MSC and M) with the group number (G) has already been established in spray combustion and coal combustion, but it helps to prove that these changes are the same and consistent in nanothermite combustion as well. Group Classification 【0178】 In the following part of this specification, the classification of the cluster combustion mode of the nanotellurites will be described in more detail. As described above, this classification is based on the range of the magnitude of the cluster mass loss rate MG / MSC and further depends on the cluster combustion number (G). G can be redefined as the ratio of the mass transfer between the particles within the cluster (region A in Figure 3) to the mass transfer between the cluster and its surroundings (region B in Figure 3). This is useful for the classification of different nanotellurite combustion modes. When the mass transfer along the cluster boundary and the surrounding region (region A in Figure 3) is very fast compared to the net transfer between the particles within the cluster and the surrounding gas phase (region B in Figure 3), G is small and is likely to result in the isolated combustion (ISOC, region i) mode. When the mass transfer along the cluster boundary and the surrounding region is significantly lower than the net transfer between the particles within the cluster and the surrounding gas phase, G is large and is suitable for the adoption of the sheath combustion (SC, region iv) mode. 【0179】 In addition to the isolated combustion (ISOC) model and the sheath combustion (SC) model, Table 3000 in Figure 30 also classifies the intermediate models of nanotellurite combustion. Overall, the nanotellurite clusters can be simply classified into internal cluster combustion (representing regime I with G < 10 and MG / MSC < 0.7 as shown in Figures 7A and 7B) and external cluster combustion (representing regime II with G > 10 and MG / MSC > 0.7). Other modes are partial cluster combustion at the upper limit of internal cluster combustion with a cluster combustion number in the range of 0.5 < G < 10. This represents zone ii in Table 3000 with 0.1 < MG / MS < 0.7 and 0.8 > M > 0.2. Further, the cluster combustion number in the range of 10 < G < 100 represents zone iii with 0.7 < MG / MSC < 0.9 and 0.2 > M > 0.03. Zone iii is the lower limit of external cluster combustion and represents the modes of critical particle combustion (CPC) and external particle combustion (EPC). Isolated particle combustion (ISOC) 【0180】 When the particles are sufficiently separated from each other, the particles burn in the isolated combustion mode. The presence of adjacent particles does not affect the combustion characteristics of individual particles. Internal group combustion (IGC) 【0181】 Species in the gas phase do not undergo chemical reactions and do not need to find oxygen-deficient regions, so it is difficult to define the zone of cloud combustion of nanotermites. Therefore, various minor modes of nanotermite combustion (IPG, IGC, PG, and CGC, EPC, SC) are classified into the same group. In spray combustion, internal group combustion (IGC) and external group combustion (EGC) are also established. In the case of internal group combustion (IGC), the mass fraction of copper (vapor product) is the highest (Y = YMax) and is located inside the group cloud (r < RG). Individual Particle Combustion (IPC) 【0182】 When the number density (n) of nanotermites increases, the combustion characteristics of the constituent particles change due to the temperature rise in the region. However, assume that the inter-particle distance (l) is large. Even in such a case, each particle maintains its own combustion characteristics, and the temperature of the cloud becomes higher than the combustion temperature of isolated particles. This is called IPC, as shown at 800 in Figure 8A. Initial Group Combustion (IGC) 【0183】 The outermost nanotermites continue to burn by IPC as n increases. These nanotermites generate copper vapor, and as a result, the copper vapor (YCu) in the cloud increases. If this state continues, the copper vapor reaches the maximum mass fraction of saturation at the core of the cloud. Furthermore, since the mass fraction of the combustion products is maximized, the temperature at this location becomes the highest. This is called IGC, as shown at 802 in Figure 8B. Partial Group Combustion (PGC) 【0184】 When n further increases, the inner particles starve for the outer vapor (and thus thermal energy) and ignite at a slow pace. The vapor from the internal region diffuses outward and establishes the highest temperature inside the cloud. However, the nanotermites located in the outer region of the cloud burn in the form of IPC. This phenomenon is denoted as PGC. Refer to 804 in Figure 8C. External Group Combustion (EGC) 【0185】 Assume that the concentration of nanotemitters (n) further increases, the copper vapor concentration in the cloud decreases, and the position where YCu ≒ 0 moves radially outward from the center of the cloud. Furthermore, the mass fraction of the fuel near the group center increases with the increase in the number density. In the EGC region, the maximum mass fraction of copper vapor (Y = YMax) is located at the group cloud radius (r = RG). Critical Group Combustion (CGC) 【0186】 When the magnitude of n becomes even larger, the flux of copper vapor cannot penetrate to the center of the cloud and cannot prevent the combustion of nanotemitters at the center. The maximum temperature is only located on the surface of the cloud. This is called CGC as shown in 806 of Figure 8D. External Particle Combustion (EPC) 【0187】 When n becomes even larger, the flux of the inner copper vapor prevents the outer copper vapor (and heat) from penetrating into the center (and its vicinity) of the cloud. The maximum temperature is still determined by the group radius (RG). This is called EGC as shown in 808 of Figure 8E. Sheath Combustion (SC) When n increases and a compact group is formed, a state is achieved where the temperature at the boundary of the particle group becomes the ignition temperature of the nanotemitters. This group functions in the same way as individual large particles with a radius RG. 【0188】 The mass density of the particle group is close to the density of a single particle (ρG = ρs). This combustion mode is known as sheath combustion as shown in 810 of Figure 8F. Thus, the results of single particles previously presented in this specification can be used for high-density spherical clouds. 【0189】 In reality, T∞ is lower than the ignition temperature of the core-shell type nanotemitters considered. Figures 8A - 8F show that the magnitude of the temperature profile is greater than the ambient temperature (T > T∞). This indicates that the combustion of the core-shell nanotemitters results in a net heat release to the initial ambient gas. 【0190】 As shown in Fig. 7A, since all the particles in the system can access the oxidizer, the profile of the mass fraction (Y) indicates that combustion is occurring inside the thermite cloud. Fig. 7B also shows combustion in the region adjacent to the thermite cloud. Furthermore, the temperature profiles in Figs. 8A - 8F peak at the cloud boundary or inside it and decrease to the far - field temperature (T∞). Regardless of the external combustion mode in Figs. 8D - 8F, the highest temperature mainly occurs at the boundary. This is because, due to the high particle concentration, the heat flux to the surrounding gas is larger than the heat inflow into the cloud interior. Considering that a single particle burns instantaneously and completely, the combustion time of a single particle is zero (ts = 0) (Equation (17)), but this is not the case for nanothermite. 【0191】 It is important to emphasize that the combustion of nanothermite is not limited to the oxidizer. That is, the content of copper oxide in the core - shell is neither more nor less than the content of aluminum. This is an important point different from spray combustion and coal combustion. Due to this characteristic, the internal particles at the cloud boundary may react via heat diffusion or mass convection of the products. 900 in Fig. 9A shows external - sheath combustion (ESC), and 902 in Fig. 9B shows the internal - sheath combustion (ISC) mode of nanothermite. 【0192】 Figure 10A shows 1000 depicting the required number of particles (N). Figure 10B shows the ratio of the cloud radius to the particle spacing (l / rs) for different group combustion numbers (G). The change in G represents different group combustion modes. l / rs < 2, RG / rs < 2, and N < 1 are theoretical and have no physical meaning. As shown in graph 1000 of Figure 10A, l / rs = 30 is fixed, and as N increases, the group radius increases. Therefore, at l / rs = 30, the mode of isolated particle combustion occurs when N ≤ 6, internal group combustion occurs when 6 ≤ N ≤ 488, external group combustion occurs when 488 ≤ N ≤ 15,450, and sheath combustion occurs when N ≥ 15,450. Similarly, considering graph 1002 of Figure 10B where l / rs = 30 is selected, the mode of isolated particle combustion occurs when RG / rs ≤ 32 (for example, rs = 30 μm, RG ≤ 1 mm), internal group combustion occurs when 32 ≤ RG / rs ≤ 146 (1 mm ≤ RG ≤ 4.6 mm), external group combustion occurs when 146 ≤ RG / rs ≤ 464 (4.6 mm ≤ RG ≤ 15 mm), and sheath combustion occurs when RG / rs ≥ 464 (RG ≥ 15 mm). As the combustion rate reaches isolated particle combustion, the group radius (RG) decreases, correlating with the increase in the combustion rate of each particle. Note that the quasi-steady assumption supports all the plots in this section, and the consideration of time dependence reduces the interaction. Comparison with Other Group Combustion Models 【0193】 Table 3100 in Figure 31 classifies various nanothermite group combustion regimes by the lower and upper limits of the group combustion number (G). The upper limit of a regime corresponds to the lower limit of the next regime. The region before individual particle combustion (IPC) corresponds to isolated particle combustion (ISOG) where the particles burn without interaction. From Table 3100, it can be seen that the size of the nanothermite region changes exponentially from IPC0.5 to CPC10 and SC100. As is clear from this table, the magnitude of G is higher in the nanothermite region than in spray combustion. Such a high magnitude of G occurs because the combustion is not limited by the availability of oxygen in the gas phase. 【0194】 In prior research, the transient combustion of a stationary droplet cloud has been analyzed. They reported that the cloud ignites more easily compared to a single droplet. Furthermore, when the clusters are dense, ignition is limited to a narrow band along the outer surface of the cluster. Similarly, the ignition of fuel sprays has also been investigated in other prior research. Here, it was determined that the influence of convection is not so important in clouds with a high spray concentration. In this case, combustion does not start until a significant amount of fuel has evaporated and the environment is saturated. Regarding this point, other research numerically studied the time-dependent ignition when a low-temperature spray is suddenly exposed to a high-temperature environment. As a result, it was found that even if the cloud is non-diluted (G>1), ignition and combustion can occur within the cloud. This abnormal combustion is contrary to the typical norms of collective combustion. Collective combustion of non-spherical particle distributions 【0195】 To model the combustion of nanothermites, in the present disclosure, a collective combustion model for a simple shape of spherical particle distribution has been developed. The virtual collective combustion of nanothermites is shown at 1100 in FIG. 11, considering the two-dimensional flux of nanothermites injected from the nozzle and the laminar flow surrounding it. The injection of these nanothermites is distributed such that the concentration is high near the nozzle and low far away. Symmetry conditions near the centerline can be considered. As a result, the temperature of the mixed gas increases in the region where the concentration of nanothermites is high. In such a system, the nanothermite particles are randomly distributed and the flow field is complex, so it is difficult to obtain a closed-form solution to this problem. To be able to identify the parameters that govern the collective behavior in such a system, as described above in this specification (and FIGS. 8A - 8F), it is useful to achieve an explicit solution for the combustion rate and correction factor for a simple shape. 【0196】 The particle distribution diagram 1100 of the nanotemitters is shown in Fig. 11 together with the contour map of the heat release in the corresponding region. The combustion flow regime can be classified into either an external group combustion regime or an internal group combustion regime. These regions are considered to correspond to simple shape regions (such as SC, EPC, etc.). As long as there are particles within the boundary of such a particle distribution and no particles outside, there is a mass source term for the particles within the boundary but not for the particles outside. In other words, there are fluctuations in the number density that indirectly serve as a mass source. Assuming that these zones are reformed into a spherical shape and there is no convection across the zones, a closed-form solution for the combustion speed of the cloud can be obtained. 【0197】 When ignited, the nanotemitters burn mostly along the boundary of the external group combustion distribution. Since the core of the nanotemitters is too cold to be ignited at the nozzle exit, it was assumed that ignition starts further downstream. Since the nanotemitters are of high density (SC), heat conduction and ignition are impossible within the distribution boundary, and as a result, ignition occurs outside this boundary. As the separation of the particles progresses (EPC), heat penetrates inside the cloud and ignites those particles. When the separation of the particles becomes large enough, the heat penetrates to the middle region of the jet and intersects the entire cluster to ignite (CPC). After this zone, there may be an internal group combustion outside the external group combustion. There may be an individual combustion zone (PGC) or a nested combustion zone (IGC) around the particle group. Subsequently, there is a terminal zone (IPC) where the unburned nanotermit particles are consumed individually. 【0198】 It is important to emphasize that this theory began by focusing on aluminum-copper oxide. However, this framework can be applied to various different nanothermite compositions, such as aluminum oxide-bismuth or aluminum oxide-iron. Some of these fuels are prone to generating gas, while others are prone to generating energy. Aluminum oxide-copper generates less vapor compared to other types of nanothermites. Therefore, it is possible to extend all of these different effects to the present disclosure, including describing the high enthalpy threshold and observing the impact on the results, as well as the large amount of gas generation. 【0199】 The combustion modes and characteristics described herein can be applied to many different systems, environments, and applications. Generally, in the application of dispersed combustion of core-shell thermite particles, the core-shell type thermite particles are dispersed in a group and ignited, and the group of thermite particles burns to generate heat. This heat can be applied to various applications. 【0200】 Referring now to FIG. 12, depicted therein is 1200, which applies the combustion characteristics of a dispersed group of core-shell type thermite particles described herein. 1200 shows a reaction-type solar collector filled with core-shell type thermite particles. These particles can be ignited using concentrated solar energy and burned in a group of particles to generate heat. 【0201】 Next, referring to FIG. 13, depicted therein is 1300, which shows a number of different rocket configurations including nozzles, combustion chambers, and fuel injectors. The various nozzle, combustion chamber, and fuel injector configurations of FIG. 13 can be applied to the collective combustion of thermite core-shell particles as described herein. These configurations can include bell-type, cone-type, spike-type, E-D-type, R-F-type, and H-F-type nozzles. 【0202】 Referring now to FIG. 14, depicted therein is 1400 which illustrates various fuel injection device configurations. The various fuel injection device configurations of FIG. 14 can be applied to the collective combustion of thermite core-shell particles, as described herein. The configurations can include concentric tubes, concentric tubes with liquid swirl, non-concentric five-tubes, non-concentric double-tubes, and non-concentric triple-tube configurations. In some examples, the configurations of FIG. 14 can be applied to combinations of various core-shell type thermite particles with reactive gas and / or carrier gas. 【0203】 Referring now to FIG. 15, depicted therein in detail is 1500 which shows various spray nozzles that can be applied as fuel injection devices for the collective combustion of thermite core-shell particles, such as those described herein. The configurations of the spray nozzles include single-hole, multi-hole, pintle, and pintaux. In some examples, the configurations of FIG. 15 can be applied to combinations of various core-shell type thermite particles with reactive gas and / or carrier gas. 【0204】 Referring now to FIG. 16, depicted therein in detail is 1600 which shows the configurations of various rocket injection devices. The different configurations can be applied, for example, to achieve different combustion modes as described herein when applied to the collective combustion of thermite core-shell particles. The configurations can include low momentum and high momentum fuel jets. 【0205】 Referring now to FIG. 17, depicted therein in detail is 1700 which shows the configurations of various rockets. The different configurations can be applied, for example, to achieve different combustion patterns as described herein when applied to the collective combustion of thermite core-shell particles. The configurations can include acute orifices, short tubes with round inlets, short tubes with conical inlets, short tubes with spiral effects, and acute cones. 【0206】 Referring now to FIG. 18, 1800, 1802, 1804, and 1806 depicted therein detail various rocket fueling configurations. Different configurations can be applied to achieve different combustion modes as described herein, for example, when applied to the collective combustion of thermite core shell particles. 【0207】 Referring now to FIG. 19, 1900 and 1902 depicted therein detail the configuration of a rocket engine. These rocket engine configurations can be applied to achieve different modes of combustion as described herein, for example, when applied to the collective combustion of thermite core shell particles. 【0208】 Referring now to FIG. 20, 2000 depicted therein details a fuel injection device configuration. These fuel injection device configurations can be applied to achieve different modes of combustion as described herein, for example, when applied to the collective combustion of thermite core shell particles. The fuel injection device configuration of FIG. 20 may include different two sets, different three sets, different four sets, and different five sets. 【0209】 Next, referring to FIG. 21, 2100 depicted therein details an engine and fuel supply configuration for an engine. These engine configurations can be applied to achieve different combustion modes as described herein, for example, when applied to the collective combustion of thermite core shell particles. The engine fuel injection device configuration of FIG. 21 may include a double collision flow pattern, a triple collision flow pattern, a self-collision flow pattern, and a shower head flow pattern. 【0210】 Next, referring to FIG. 22, shown therein is 2200 which details the fuel injection device configuration. These fuel injection device configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The fuel injection device configurations of FIG. 22 can include concentric tubes, concentric tubes with liquid swirl, different five-sets, different two-sets, different three-sets, same two-sets, shower heads, variable area (pintle), and splash plates. 【0211】 Now referring to FIG. 23, shown therein is 2300 which details the fuel injection device spray configuration. These fuel injection device spray configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The fuel injection device spray configurations of FIG. 23 can include normal fluff fans, even flat fans, hollow cones, flooding flat fans, and swirl chambers. 【0212】 Next, referring to FIG. 24, shown therein is 2400 which details the fuel injection device spray configuration. These fuel injection device spray configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The fuel injection device spray configurations of FIG. 24 can include spray configurations such as air spray, hydraulic microspray, hollow cone, flat fan, and full cone. 【0213】 Next, referring to FIG. 25, shown therein is 2500 which details the fuel injection device spray configuration. These fuel injection device spray configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The fuel injection device spray configurations of FIG. 25 can include full cone, hollow cone, flat fan, solid stream, cluster nozzle, tang type nozzle, flat fan nozzle, and air pressure spray configurations. Such configurations can include external mixing and internal mixing. 【0214】 Referring now to FIG. 26A, depicted therein is 2600 which shows in detail a fuel injection device configuration. These fuel injection device configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The fuel injection device configuration can include throttle body injection and single point injection. 【0215】 Referring now to FIG. 26B, 2602 and 2604 depicted therein show in detail a fuel injection device configuration. These fuel injection device configurations can be applied, for example, when applied to the collective combustion of thermite core-shell particles, to achieve different modes of combustion as described herein. The configuration of the fuel injection device can include throttle body injection and multi-point injection. 【0216】 As shown in FIGS. 26A - 26B, when applying the collective combustion of thermite core-shell particles to an engine, the engine can constitute internal combustion or external combustion. In some examples, the systems and methods described herein can be applied to thermal power generation. In some examples, the systems and methods described herein can be applied to additive manufacturing processes and methods that include those applying a cooling spray method. In some examples, the systems and methods described herein can be applied to the manufacture and / or use of recyclable energy particles. In some examples, the systems and methods described herein can be applied to a curing method using electromagnetic radiation. In some examples, the systems and methods described herein can be applied to an induction-based system for heating and ignition. In some examples, the systems and methods described herein can be applied to an inter-ignition system that includes solar radiation sources and non-radiation sources, as well as radiation sources such as electromagnetic radiation, lasers, masers, MW radiation, infrared radiation, terahertz radiation, and other radiations. 【0217】 In some examples, the systems and methods described herein can be applied to additive manufacturing that includes induction heating. In some examples, the systems and methods described herein can be applied to a surface finishing configuration of additive manufacturing that includes a cooling system that enables phase change. In some examples, the systems and methods described herein can be applied to additive manufacturing having embedded core-shell type thermite particles. In some examples, the systems and methods described herein can be applied to additive manufacturing that includes spraying onto a structural layer. In some examples, the systems and methods described herein can be applied to additive manufacturing for the purposes of synthesis and fabrication. 【0218】 Referring now to FIG. 27, depicted therein at 2700 is a detailed illustration of the application of collective combustion of thermite core-shell particles to a power generation cycle. The power generation cycle can constitute a typical combined cycle or a multiple power generation cycle. The collective combustion of thermite core-shell particles can be applied, for example, as a fuel source in such a power generation cycle in place of a coal or natural gas combustion system. 【0219】 Referring now to FIGS. 28A-28B, depicted therein at 2800 and 2802 are rocket configurations to which the collective combustion of thermite core-shell particles can be applied. By applying the fuel particle shapes and structural configurations of FIGS. 28A-28B, the combustion (e.g., combustion mode) of the collective combustion of thermite core-shell particles can be configured and adjusted. 【0220】 In some examples, the systems and methods described herein may be applied to thermal conversion systems, including, but not limited to, thermal storage and radiative heat recycling systems, as well as thermoelectric, spintronics, and / or hybrid systems. In some examples, the systems and methods described herein can be applied to energy storage systems that use wireless power. In some examples, the systems and methods described herein can be applied to the additive manufacturing of anodes and cathodes for battery storage systems. In such examples, thermite can function as an anode and a cathode. In some examples, the systems and methods described herein can be applied to thermal energy storage in micro / nano materials such as energy composite materials. In some examples, the systems and methods described herein can be applied to induction heating systems. In some examples, the systems and methods described herein can be applied to the combination of a thermophotovoltaic system and thermite for converting thermal energy into electricity. In some examples, the systems and methods described herein can be applied to additive manufacturable systems such as printed integrated systems. In some examples, the systems and methods described herein can be applied to the printing of thermite systems and the integration of printed thermite systems into thermophotovoltaic systems. In some examples, the systems and methods described herein can be applied to systems for converting heat into electricity. In some examples, the systems and methods described herein can be applied to energy storage systems incorporated into the infrastructure of smart cities. In some examples, the systems and methods described herein can be applied to in-situ resource utilization materials mixed with aerogels for manufacturing wireless receivers and transmitters. In some examples, the systems and methods described herein can be applied to thermal energy storage systems using wireless power transmission, TPV, thermoelectricity, spintronics, quantum effects, and the like. In some examples, the systems and methods described herein can be applied to hybrid systems for cogeneration, including the incorporation of thermal conversion systems that use other renewable energy sources. 【0221】 In some examples, wireless power transfer may use multiple transmitters and multiple receivers to create a network, the pilot signal between the receiver and the transmitter may be established using a first electromagnetic source to create initial conditions, the receiver may transmit the first electromagnetic source to multiple transmitters, or the transmitter may transmit a second electromagnetic source to multiple receivers. Further, the multiple transmitters and receivers may be networked in multiple network configurations. In other embodiments, the transmitter may be at least one or a combination thereof such as mmWave, laser, maser, MW, infrared, THz, etc., and other electromagnetic sources may be used to create the initial conditions. In other embodiments, the transmitter may be a non-radiative source such as a magnet or an electromagnet. In other embodiments, the receiver may receive energy from multiple electromagnetic radiation sources and / or non-radiative sources. 【0222】 In some examples, the systems and methods described herein are configured to operate in extreme temperature environments and use heat available from a source to convert heat to electricity - a thermoelectric conversion system - for example, satellite systems, rovers, space structures, drones, aircraft, and other similar examples. For example, satellite systems, explorers, space structures, drones, aircraft, etc. In some examples, the systems and methods described herein can be applied to submarines / drones that use geothermal energy as a heat source to power multiple systems. In some examples, the systems and methods described herein can be applied to the storage of heat in structures (e.g., graphene-based and / or micro and / or nano energy particles). In some examples, the systems and methods described herein can be applied to structures that can be inflatable, deployable, and additionally manufacturable. In some examples, the systems and methods described herein can be applied to systems coupled to other thermoelectric power systems. In some examples, the systems and methods described herein can be applied to enable continuous flight using reusable vehicles for communication, asset monitoring, climate change, mobile data collection systems, airborne telescopes, and other use cases. In some examples, the systems and methods described herein can be applied to vehicles operating in multiple domains (e.g., land, air, water, and space). In some examples, the systems and methods described herein can be applied to systems and methods that combine power generation, storage, and distribution. 【0223】 In some examples, the systems and methods described herein can be charged from renewable sources and other sources, and can be applied to thermal energy storage systems that provide hot water, cooling, and on-demand heating and electricity. In some examples, the systems and methods described herein can be applied to temperature control systems that drive various thermal reactions. In some examples, the systems and methods described herein can be applied to graphene-based systems, and other materials can be added to improve performance. In some examples, the systems and methods described herein can be applied to metering systems with blockchain technology. In some examples, the systems and methods described herein may be applied to reduce emissions and may be applied to locally additive manufacturable systems. In some examples, the systems and methods described herein can be applied to thermal energy storage systems integrated into existing or new infrastructure (e.g., buildings, windows, houses, sidewalks, utility poles, other surfaces or volumes). In some examples, the systems and methods described herein can be applied as an alternative to gas boilers and heat pumps. In some examples, the systems and methods described herein can be applied to active and / or passive cooling systems for terrestrial and / or space applications for robotic exploration and human space exploration (including living and working in space). In some examples, the systems and methods described herein can be applied to traction applications such as vehicles that use, for example, TCS and / or TSS. In some examples, the systems and methods described herein can be applied to magnetohydrodynamic systems and methods. In some examples, the systems and methods described herein can be applied to the networking of multiple nodes for wireless power transmission and power transfer. 【0224】 In some examples, the systems and methods described herein can be applied to emitters that include multilayer systems using high-energy materials that have a controllable and adjustable operating range and are deployable, additive manufacturable, and inflatable. In some examples, the systems and methods described herein can be applied to receivers that include multilayer systems using high-energy materials that have a controllable and adjustable operating range and are deployable, additive manufacturable, and inflatable. In some examples, the systems and methods described herein can be applied to populations of particles prepared in both symmetric and asymmetric multi-dimensional geometric shapes. In some examples, the systems and methods described herein can be applied to smart networking for power management using AI / ML algorithms for continuous operation. 【0225】 In some examples, the systems and methods described herein can be applied to a thermal power plant that uses nanothermites / nanoenergy particles and / or composite materials for power generation. Such methods enable heating and / or ignition of the nanothermite / nanoenergy composite material via induction, specifically heating using eddy currents, or heating using hysteresis, or heating that combines both eddy currents and hysteresis. The heating in such examples is used as part of a power generation boiler in a power plant. In some examples, the systems and methods described herein can be applied to drive - by combustion and / or sintering of - a steam engine (e.g., a Stirling engine), where nano / microthermites and high - energy materials are used to heat a working fluid by complete combustion or convection to enable a phase change. In some examples, the systems and methods described herein can be applied to dual combustion that drives multiple processes using the above - described systems, where the by - products of one reaction become the products of another reaction. In some examples, the systems and methods described herein can be applied to a chemical looping method and / or a metal looping method for driving a process that generates electricity. In some examples, the systems and methods described herein can be applied to chemical looping and / or metal looping by combustion or sintering for by - product generation and treatment of materials and / or by - products. In some examples, the systems and methods described herein can be applied to a heat storage system and recycling for radiating heat. 【0226】 In some examples, the systems and methods described herein can be applied to a thermal power plant used for cogeneration that simultaneously generates electricity and useful heat. In such examples, the wasted thermal energy is put to some productive use. In some examples, the systems and methods described herein can be applied to a thermal power plant used for multi-generation to simultaneously generate electricity, useful heat, cooling, propulsion, energy storage, and industrial products. In some examples, the systems and methods described herein can be applied to a thermal power plant that can be combined with renewable and non-renewable power generation systems for power generation and / or multi-power generation for generating electricity, useful heat, cooling, propulsion, energy storage, and industrial products. Non-renewable power generation systems include, but are not limited to, oil, gas, coal, natural gas, nuclear power, etc. Renewable power generation systems include, but are not limited to, solar heat, biomass, compressors, fuel cells, geothermal energy, etc. In some examples, the systems and methods described herein can be applied to multi-power generation achieved by the interconversion phenomenon via spin between heterogeneous physical entities for generating electricity, light, sound, vibration, and heat on Earth and in space. These phenomena include, but are not limited to, the Seebeck effect, the Peltier effect, the spin Seebeck effect, the spin Peltier effect, the spin Hall effect, the inverse spin Hall effect, etc. Spin conversion occurs in the region near the interface between physical entities mediated by spin, and enables the interconversion of electricity, light, sound, vibration, and heat by transferring angular momentum. In some examples, the systems and methods described herein can be applied to an energy storage system for on-demand use and distribution. These systems include, but are not limited to, electrochemical, electromagnetic, thermodynamic, mechanical, etc. The stored energy is used directly or indirectly through an energy conversion process as needed to provide a balance between energy supply and demand. 【0227】 In some examples, the systems and methods described herein can be applied to methods of generating power on Earth and in the space of the Moon, other planets, asteroids, meteoroids, and other celestial bodies. In some examples, the systems and methods described herein can be applied to the use of nanothermit fuels, along with in-space resource utilization as a fuel source such as composite plus materials from the Moon, Mars, asteroids, and other celestial bodies, or combinations of the foregoing. In some examples, the systems and methods described herein can be applied to high-temperature control using induction. Such systems enable precise control of heat generation in a defined area and, as such, can be used to drive many chemical processes. In some examples, the systems and methods described herein can be applied to new or existing power generation applications with a compact design. In some examples, the systems and methods described herein can be applied to heating applications to ensure that electronic devices and space systems, space architectures, and other space systems maintain operation and withstand extremely cold or harsh environments. 【0228】 In some examples, the systems and methods described herein can be applied to the use of microparticles and nanoparticles in homogeneous and / or heterogeneous mixtures. In some examples, such applications can include the combustion of the same group of fuels and / or combinations of groups of fuels and / or additives. In some examples, the systems and methods described herein can be applied to the additive manufacturing of 2D / 3D structures where combustion and / or heating are required. In some examples, the systems and methods described herein may be applied to other energy systems to enhance performance in at least one aspect of nuclear, nuclear fusion, nuclear fission, renewable technologies, solar, TPV, plasma, or solar thermal. 【0229】 In some examples, the systems and methods described herein can be applied to power, propulsion, and construction systems and methods. In some examples, the systems and methods described herein can be applied to adapting combustion needs to a combustion profile. In some examples, the systems and methods described herein can be applied to various manufacturing methods such as physical mixing methods, chemical methods, thermal methods, and other methods. In some examples, the systems and methods described herein can be applied to in-situ resource utilization and international space research platforms. In some examples, the systems and methods described herein can be applied to multi-generation power generation systems such as those that apply cogeneration, or trigeneration. In some examples, the systems and methods described herein can be applied to heat storage systems and batteries. In some examples, the systems and methods described herein can be applied to multi-source heating systems such as those that apply wireless power using solar energy, solar collectors, induction, or electromagnetic radiation (such as mm waves, lasers, MW, infrared, THz, etc.). In some examples, the systems and methods described herein can be applied to propulsion, power generation, heating, catalytic, welding or joining applications, storage, and carbon sequestration. In some examples, the systems and methods described herein can be applied to fireworks, other pyrotechnics, and public dispensing. In some examples, the systems and methods described herein can be applied to additive manufacturing of 2D and / or 3D structures. In some examples, the systems and methods described herein can be applied to components for satellites and / or space systems, or robotic explorers. In some examples, the systems and methods described herein can be applied to the manufacture and use of components for living spaces and / or space architecture. In some examples, the systems and methods described herein can be applied to solar collectors for enhancing energy production in space. In some examples, the systems and methods described herein can be applied to heating and combustion in oxygen-deficient environments, under microgravity, or under variable gravity for space-based applications.In some examples, the systems and methods described herein can be combined with other energy systems to enhance performance with at least one of nuclear, nuclear fusion, nuclear fission, renewable technologies, solar, thermophotovoltaic, plasma, and solar thermal. 【0230】 In some examples, the systems and methods described herein can be applied to thermite fuels in the form of pellets, waxes, solids, liquids, and / or plasmas. In some examples, the systems and methods described herein can be applied to fuel configurations consisting of tubes of various shapes and sizes. In some examples, the systems and methods described herein can be applied to engines. In some examples, the systems and methods described herein can be applied to recyclable fuels. 【0231】 Referring now to FIG. 32, depicted therein is a flowchart showing a method 3200 for generating energy. Method 3200 includes 3202 and 3204. 【0232】 At 3202, core-shell thermite particles are provided. 【0233】 At 3204, a group of the dispersed core-shell thermite particles is combusted to generate heat. In some examples, the core-shell thermite particles are heated without achieving combustion. 【0234】 The foregoing description provides examples of one or more apparatuses, devices, methods, or systems, but it will be understood that other apparatuses, devices, methods, or systems may also be included within the scope of the claims as interpreted by one of ordinary skill in the art.

Claims

[Claim 1] A method of generating energy, A step of providing core-shell type thermite particles, The steps include burning a dispersed group of core-shell type thermite particles in order to generate heat, A method that includes this. [Claim 2] The method according to claim 1, characterized in that the core-shell type thermite particles include at least one of nanoparticles or microparticles. [Claim 3] The method according to claim 1, characterized in that the core-shell type thermite particles are burned in an environment without gaseous oxygen. [Claim 4] The method according to claim 1, characterized in that the combustion mode includes any of initial group combustion, partial group combustion, critical particle combustion, external particle combustion, or sheath combustion. [Claim 5] The method according to claim 1, characterized in that the combustion of the core-shell type thermite particles occurs within a reactive solar collector. [Claim 6] The method according to claim 1, characterized in that the dispersed group of core-shell type thermite particles is generated in a fuel injection device. [Claim 7] The method according to claim 1, wherein the fuel injection device is at least one rocket injection device or a multi-point injection system. [Claim 8] The method according to claim 1, characterized in that the core-shell type thermite particles are heated by eddy currents, hysteresis, or a combination of both. [Claim 9] The method according to claim 1, characterized in that the generated heat is applied to an additive manufacturing process, a propulsion system, or a power generation system. [Claim 10] The method according to 9, characterized in that the power generation system includes a combined cycle power generation system with heat recovery. [Claim 11] The method according to claim 1, characterized in that the generated heat is used to propel the vehicle. [Claim 12] The method according to 11, characterized in that the vehicle is a submarine, a spaceship, or an airplane. [Claim 13] The method according to claim 1, characterized in that the generated heat is applied to power generation for wireless power transmission. [Claim 14] The method according to claim 1, characterized in that the combustion product is provided as a reactant for another process. [Claim 15] The method according to claim 1, wherein the combustion product is applied to a pyrotechnic device. [Claim 16] A system that generates energy, A means of providing core-shell type thermite particles, A means for burning a dispersed group of core-shell type thermite particles in order to generate heat, A system that includes this. [Claim 17] The system according to claim 16, characterized in that the core-shell type thermite particles include at least one of nanoparticles or microparticles. [Claim 18] The system according to claim 16, characterized in that the dispersed group of core-shell type thermite particles is generated in a fuel injection device. [Claim 19] The system according to claim 16, wherein the fuel injection device is at least one of a rocket injection device or a multi-point injection system. [Claim 20] The system according to claim 16, characterized in that it is applied to a mutual ignition system including a radiation source or a non-radiation source.

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