Classifications

• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
  • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
  • C06B45/18—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component
  • C06B45/30—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component the component base containing an inorganic explosive or an inorganic thermic component
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23B—METHODS OR APPARATUS FOR COMBUSTION USING ONLY SOLID FUEL
  • F23B99/00—Subject matter not provided for in other groups of this subclass
• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
  • C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
  • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
  • C06B45/02—Compositions or products which are defined by structure or arrangement of component of product comprising particles of diverse size or shape
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B33—ADDITIVE MANUFACTURING TECHNOLOGY
  • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
  • B33Y10/00—Processes of additive manufacturing
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B45/00—Engines characterised by operating on non-liquid fuels other than gas; Plants including such engines
  • F02B45/08—Engines characterised by operating on non-liquid fuels other than gas; Plants including such engines operating on other solid fuels
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23G—CREMATION FURNACES; CONSUMING WASTE PRODUCTS BY COMBUSTION
  • F23G2900/00—Special features of, or arrangements for incinerators
  • F23G2900/508—Providing additional energy for combustion, e.g. by using supplementary heating
  • F23G2900/50804—Providing additional energy for combustion, e.g. by using supplementary heating using thermit or other compositions of metal oxides as auxiliary fuel

Definitions

• the heat is applied to welding, sintering or joining.
• the particles are moved using magnetohydrodynamics, magnetic confinement, and energized using magnetic induction.
• the system or method is autonomous and/or semi-autonomous.
• Figure 1 is a diagram depicting core shell thermite combustion, according to an embodiment
• Figure 2 is a diagram depicting temperature distribution of core shell thermite combustion, according to an embodiment
• Figure 3 is a diagram depicting dispersed group core shell thermite combustion, according to an embodiment
• Figure 4 is a graph depicting normalized mass-fraction and temperature of nanothermite group combustion, according to an embodiment
• Figure 5 is a graph depicting the normalized radial mass flow rate against the normalized radius for different group combustion numbers (G) , according to an embodiment
• Figure 6A is a graph depicting group mass-loss rate in variation with the group number, according to an embodiment
• Figure 6B is a graph depicting group mass-loss rate in variation with the group number, according to an embodiment
• Figure 7A depicts a diagram illustrating the internal group combustion mode, according to an embodiment
• Figure 7B depicts
• Nanothermites are a Metastable Intermolecular Composite (MIC) which are often made of a metal and metal oxide—mixed at a nanoscale—that can undergo an exothermic chemical reaction with sufficient energy input.
• MIC Metastable Intermolecular Composite
• the combustion of a single, core–shell nanothermite particle shares many characteristics with single-particle char or droplet combustion, the primary difference being the solid-state diffusion of oxygen that occurs within a particle in the nanothermite.
• the dispersed core–shell nanothermite reactions are not limited by the presence of gaseous oxygen (due to the solid-phase oxidizer transport from the shell)
• the combustion dynamic of multiple dispersed particles differs greatly from the classical multi-phase combustion regimes.
• Group combustion is the burning characteristic of the collection of particles and is helpful in modeling of dispersed particle combustion. Several different ‘modes’ of group combustion have been recognized for the case of dispersed droplets and solid particles.
• Equation (3) the final solution of the mass fraction variation of the vapor product (Y) at any radius (r) location is obtained by substituting Equation (5) into Equation (3) to obtain: [0105] [0106]
• Equation (5) the final solution of the mass fraction variation of the vapor product (Y) at any radius (r) location is obtained by substituting Equation (5) into Equation (3) to obtain: [0105] [0106]
• T the thermodynamic temperature at radial location (r).
• ⁇ and Cp are the thermal conductivity and specific heat of the gas-mixture, respectively.
• a similar sanity check can be performed at a radial location far from the solid particle (r ⁇ ).
• the temperature variation within a cloud plays an important role in group combustion, which depends on the mass transfer of copper vapor above the ignition temperature. It is reasonable to assume that combustion reactions in region B (of Figure 3) take place uniformly since it is the domain of mean mass and mean temperature within the interstitial field. Thus, the group is considered as a homogeneous phase. It was previously demonstrated for a group interaction system that all the particles must be at the same temperature ( Ts) for the thermodynamic equilibrium to occur at a steady-state. Therefore, the reaction rate in each configuration was considered constant in the model. [0141] The group or cloud method described herein involves obtaining the statistical mean of the mass source.
• the clouds mass flow rate at a radial location (r) is determined by summing up the overall particle sources (from Equation (4)) as follows: [0156] (24) [0157] Further, the total mass flow rate ( m ⁇ G) at the boundary and outside of the cloud is as follows: [0158] (25) [0159] Thus, the normalized radial mass outflux rate of the group is given by the following formula: [0160] (26) [0161] (27) [0162] Graph 500 of Figure 5 plots the normalized radial mass flow rate (m ⁇ ⁇ r /m ⁇ G) [0163] against the normalized radius (r/ RG) for different group combustion numbers (G).
• the non-dimensional mass group rate ( MG) can be obtained as follows: [0165] (28) [0166]
• the mass flux in the cloud is normalized by (4 ⁇ RG ⁇ D) , analogous to the normalizing term of single particle combustion presented in Equation (5).
• the normalized mass flux considered in the nanothermite group combustion was described so that the conditions of the cloud versus the single particle combustion could be compared.
• the solution for the group mass-loss rate is provided in two forms.
• Figures 8A-8F demonstrate that the core–shell nanothermite combustion results in net heat release to the initial ambient gas because the magnitudes of the temperature profile are greater than the ambient temperature (T> T ⁇ ).
• the mass fraction (Y) profiles are indicative of combustion occurring inside the thermite cloud since every particle in the system has access to an oxidizer.
• Figure 7B also shows combustion in an area bordering the thermite cloud.
• the temperature profiles in Figures 8A-8F are at their maximum at or within the cloud boundary and decrease to that of a distant temperature ( T ⁇ ).
• Fuel injector spray configurations of Figure 23 may include regular flat fan, even flat fan, hollow cone, flooding flat fan and whirl chamber.
• FIG 2400 pictured therein is diagram 2400, detailing fuel injector spray configurations. These fuel injector spray configurations may be applied, for example, to achieve different modes of combustion as described herein, when applied to the group combustion of thermite core-shell particles.
• Fuel injector spray configurations of Figure 24 may include air atomizing, hydraulic fine spray, hollow cone, flat fan and full cone spray configurations.
• the systems and methods described herein may be applied to additively manufacturable systems, such as printed integrated systems. In some examples, the systems and methods described herein may be applied to printing of thermite systems and integration of printed thermite systems into thermophotovoltaic systems. In some examples, the systems and methods described herein may be applied to system for converting heat to electricity. In some examples, the systems and methods described herein may be applied to energy storage system that are incorporated into the infrastructure of a smart city. In some examples, the systems and methods described herein may be applied to in-situ resource utilization materials mixed with aerogels to produce radio receivers and transmitters.
• such methods allow for the heating and/or ignition of nanothermite/nanoenergetic composites through induction, specifically via heating using eddy currents or heating via hysteresis, or heating using a combination of both eddy currents and hysteresis.
• the heating in such examples is used as part of a boiler for power generation in a power plant.
• the systems and methods described herein may be applied to driving steam engines (e.g. Sterling engines) – by means of combustion and/or sintering, for heating the working fluid where nano-/micro- thermites and energetic materials are used to heat the working fluid by way of complete combustion or convection to enable a phase change.

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• Chemical & Material Sciences (AREA)
• Engineering & Computer Science (AREA)
• Organic Chemistry (AREA)
• Crystallography & Structural Chemistry (AREA)
• Inorganic Chemistry (AREA)
• Metallurgy (AREA)
• Materials Engineering (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Thermal Sciences (AREA)
• Physics & Mathematics (AREA)
• Fluidized-Bed Combustion And Resonant Combustion (AREA)
• Solid-Fuel Combustion (AREA)
• Gasification And Melting Of Waste (AREA)

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• 2023
  • 2023-06-08 EP EP23818691.0A patent/EP4537017A1/de active Pending
  • 2023-06-08 WO PCT/CA2023/050792 patent/WO2023235983A1/en not_active Ceased
  • 2023-06-08 JP JP2024572384A patent/JP2025524376A/ja active Pending
  • 2023-06-08 US US18/873,166 patent/US20260070857A1/en active Pending
  • 2023-06-08 CA CA3258936A patent/CA3258936A1/en active Pending

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