EP2625031A2 - Composites structuraux intérieurement renforcés et procédés de fabrication associés - Google Patents

Composites structuraux intérieurement renforcés et procédés de fabrication associés

Info

Publication number
EP2625031A2
EP2625031A2 EP10814155.7A EP10814155A EP2625031A2 EP 2625031 A2 EP2625031 A2 EP 2625031A2 EP 10814155 A EP10814155 A EP 10814155A EP 2625031 A2 EP2625031 A2 EP 2625031A2
Authority
EP
European Patent Office
Prior art keywords
layers
forming
precursor
exfoliating
carbon atoms
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP10814155.7A
Other languages
German (de)
English (en)
Other versions
EP2625031A4 (fr
Inventor
Roy E. Mcalister
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
McAlister Technologies LLC
Original Assignee
McAlister Technologies LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US12/707,653 external-priority patent/US8172990B2/en
Priority claimed from PCT/US2010/024499 external-priority patent/WO2010096505A1/fr
Priority claimed from PCT/US2010/024497 external-priority patent/WO2010096503A1/fr
Application filed by McAlister Technologies LLC filed Critical McAlister Technologies LLC
Publication of EP2625031A2 publication Critical patent/EP2625031A2/fr
Publication of EP2625031A4 publication Critical patent/EP2625031A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
    • F03G7/04—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using pressure differences or thermal differences occurring in nature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N5/00—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy
    • F01N5/02—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using heat
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B3/00—Hydrogen; Gaseous mixtures containing hydrogen; Separation of hydrogen from mixtures containing it; Purification of hydrogen
    • C01B3/02—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen
    • C01B3/22—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by decomposition of gaseous or liquid organic compounds
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B3/00—Hydrogen; Gaseous mixtures containing hydrogen; Separation of hydrogen from mixtures containing it; Purification of hydrogen
    • C01B3/02—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen
    • C01B3/32—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by reaction of gaseous or liquid organic compounds with gasifying agents, e.g. water, carbon dioxide, air
    • C01B3/34—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by reaction of gaseous or liquid organic compounds with gasifying agents, e.g. water, carbon dioxide, air by reaction of hydrocarbons with gasifying agents
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B32/00—Carbon; Compounds thereof
    • C01B32/20—Graphite
    • C01B32/21—After-treatment
    • C01B32/22—Intercalation
    • C01B32/225—Expansion; Exfoliation
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10L—FUELS NOT OTHERWISE PROVIDED FOR; NATURAL GAS; SYNTHETIC NATURAL GAS OBTAINED BY PROCESSES NOT COVERED BY SUBCLASSES C10G, C10K; LIQUEFIED PETROLEUM GAS; ADDING MATERIALS TO FUELS OR FIRES TO REDUCE SMOKE OR UNDESIRABLE DEPOSITS OR TO FACILITATE SOOT REMOVAL; FIRELIGHTERS
    • C10L3/00—Gaseous fuels; Natural gas; Synthetic natural gas obtained by processes not covered by subclass C10G, C10K; Liquefied petroleum gas
    • C10L3/06—Natural gas; Synthetic natural gas obtained by processes not covered by C10G, C10K3/02 or C10K3/04
    • C10L3/10—Working-up natural gas or synthetic natural gas
    • C10L3/108—Production of gas hydrates
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B1/00—Electrolytic production of inorganic compounds or non-metals
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B1/00—Electrolytic production of inorganic compounds or non-metals
    • C25B1/01—Products
    • C25B1/02—Hydrogen or oxygen
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B1/00—Electrolytic production of inorganic compounds or non-metals
    • C25B1/01—Products
    • C25B1/02—Hydrogen or oxygen
    • C25B1/04—Hydrogen or oxygen by electrolysis of water
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B1/00—Electrolytic production of inorganic compounds or non-metals
    • C25B1/01—Products
    • C25B1/24—Halogens or compounds thereof
    • C25B1/26—Chlorine; Compounds thereof
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B11/00—Electrodes; Manufacture thereof not otherwise provided for
    • C25B11/02—Electrodes; Manufacture thereof not otherwise provided for characterised by shape or form
    • C25B11/03—Electrodes; Manufacture thereof not otherwise provided for characterised by shape or form perforated or foraminous
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B13/00—Diaphragms; Spacing elements
    • C25B13/02—Diaphragms; Spacing elements characterised by shape or form
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B15/00—Operating or servicing cells
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B3/00—Electrolytic production of organic compounds
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
    • C25B9/00—Cells or assemblies of cells; Constructional parts of cells; Assemblies of constructional parts, e.g. electrode-diaphragm assemblies; Process-related cell features
    • C25B9/17—Cells comprising dimensionally-stable non-movable electrodes; Assemblies of constructional parts thereof
    • E—FIXED CONSTRUCTIONS
    • E21—EARTH OR ROCK DRILLING; MINING
    • E21C—MINING OR QUARRYING
    • E21C50/00—Obtaining minerals from underwater, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
    • F02G5/00—Profiting from waste heat of combustion engines, not otherwise provided for
    • F02G5/02—Profiting from waste heat of exhaust gases
    • F02G5/04—Profiting from waste heat of exhaust gases in combination with other waste heat from combustion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03B—MACHINES OR ENGINES FOR LIQUIDS
    • F03B13/00—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates
    • F03B13/12—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy
    • F03B13/14—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy using wave energy
    • F03B13/16—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy using wave energy using the relative movement between a wave-operated member, i.e. a "wom" and another member, i.e. a reaction member or "rem"
    • F03B13/18—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy using wave energy using the relative movement between a wave-operated member, i.e. a "wom" and another member, i.e. a reaction member or "rem" where the other member, i.e. rem is fixed, at least at one point, with respect to the sea bed or shore
    • F03B13/1885—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy using wave energy using the relative movement between a wave-operated member, i.e. a "wom" and another member, i.e. a reaction member or "rem" where the other member, i.e. rem is fixed, at least at one point, with respect to the sea bed or shore and the wom is tied to the rem
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G3/00—Other motors, e.g. gravity or inertia motors
    • F03G3/08—Other motors, e.g. gravity or inertia motors using flywheels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
    • F03G7/04—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using pressure differences or thermal differences occurring in nature
    • F03G7/05—Ocean thermal energy conversion, i.e. OTEC
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F22—STEAM GENERATION
    • F22B—METHODS OF STEAM GENERATION; STEAM BOILERS
    • F22B33/00—Steam-generation plants, e.g. comprising steam boilers of different types in mutual association
    • F22B33/18—Combinations of steam boilers with other apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24D—DOMESTIC- OR SPACE-HEATING SYSTEMS, e.g. CENTRAL HEATING SYSTEMS; DOMESTIC HOT-WATER SUPPLY SYSTEMS; ELEMENTS OR COMPONENTS THEREFOR
    • F24D11/00—Central heating systems using heat accumulated in storage masses
    • F24D11/002—Central heating systems using heat accumulated in storage masses water heating system
    • F24D11/005—Central heating systems using heat accumulated in storage masses water heating system with recuperation of waste heat
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24H—FLUID HEATERS, e.g. WATER OR AIR HEATERS, HAVING HEAT-GENERATING MEANS, e.g. HEAT PUMPS, IN GENERAL
    • F24H8/00—Fluid heaters characterised by means for extracting latent heat from flue gases by means of condensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S10/00—Solar heat collectors using working fluids
    • F24S10/40—Solar heat collectors using working fluids in absorbing elements surrounded by transparent enclosures, e.g. evacuated solar collectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S20/00—Solar heat collectors specially adapted for particular uses or environments
    • F24S20/20—Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S23/00—Arrangements for concentrating solar-rays for solar heat collectors
    • F24S23/30—Arrangements for concentrating solar-rays for solar heat collectors with lenses
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
    • H01M8/0606—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants
    • H01M8/0656—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by electrochemical means
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/18—Regenerative fuel cells, e.g. redox flow batteries or secondary fuel cells
    • H01M8/184—Regeneration by electrochemical means
    • H01M8/186—Regeneration by electrochemical means by electrolytic decomposition of the electrolytic solution or the formed water product
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/02—Processes for making hydrogen or synthesis gas
    • C01B2203/0205—Processes for making hydrogen or synthesis gas containing a reforming step
    • C01B2203/0211—Processes for making hydrogen or synthesis gas containing a reforming step containing a non-catalytic reforming step
    • C01B2203/0216—Processes for making hydrogen or synthesis gas containing a reforming step containing a non-catalytic reforming step containing a non-catalytic steam reforming step
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/02—Processes for making hydrogen or synthesis gas
    • C01B2203/0283—Processes for making hydrogen or synthesis gas containing a CO-shift step, i.e. a water gas shift step
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/04—Integrated processes for the production of hydrogen or synthesis gas containing a purification step for the hydrogen or the synthesis gas
    • C01B2203/042—Purification by adsorption on solids
    • C01B2203/043—Regenerative adsorption process in two or more beds, one for adsorption, the other for regeneration
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/06—Integration with other chemical processes
    • C01B2203/061—Methanol production
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/12—Feeding the process for making hydrogen or synthesis gas
    • C01B2203/1205—Composition of the feed
    • C01B2203/1211—Organic compounds or organic mixtures used in the process for making hydrogen or synthesis gas
    • C01B2203/1235—Hydrocarbons
    • C01B2203/1241—Natural gas or methane
    • C—CHEMISTRY; METALLURGY
    • C01—INORGANIC CHEMISTRY
    • C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
    • C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
    • C01B2203/80—Aspect of integrated processes for the production of hydrogen or synthesis gas not covered by groups C01B2203/02 - C01B2203/1695
    • C01B2203/84—Energy production
    • C—CHEMISTRY; METALLURGY
    • C02—TREATMENT OF WATER, WASTE WATER, SEWAGE, OR SLUDGE
    • C02F—TREATMENT OF WATER, WASTE WATER, SEWAGE, OR SLUDGE
    • C02F1/00—Treatment of water, waste water, or sewage
    • C02F1/46—Treatment of water, waste water, or sewage by electrochemical methods
    • C02F1/461—Treatment of water, waste water, or sewage by electrochemical methods by electrolysis
    • C02F1/46104—Devices therefor; Their operating or servicing
    • C—CHEMISTRY; METALLURGY
    • C02—TREATMENT OF WATER, WASTE WATER, SEWAGE, OR SLUDGE
    • C02F—TREATMENT OF WATER, WASTE WATER, SEWAGE, OR SLUDGE
    • C02F2303/00—Specific treatment goals
    • C02F2303/10—Energy recovery
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24D—DOMESTIC- OR SPACE-HEATING SYSTEMS, e.g. CENTRAL HEATING SYSTEMS; DOMESTIC HOT-WATER SUPPLY SYSTEMS; ELEMENTS OR COMPONENTS THEREFOR
    • F24D2200/00—Heat sources or energy sources
    • F24D2200/16—Waste heat
    • F24D2200/26—Internal combustion engine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24D—DOMESTIC- OR SPACE-HEATING SYSTEMS, e.g. CENTRAL HEATING SYSTEMS; DOMESTIC HOT-WATER SUPPLY SYSTEMS; ELEMENTS OR COMPONENTS THEREFOR
    • F24D2200/00—Heat sources or energy sources
    • F24D2200/16—Waste heat
    • F24D2200/29—Electrical devices, e.g. computers, servers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F24D—DOMESTIC- OR SPACE-HEATING SYSTEMS, e.g. CENTRAL HEATING SYSTEMS; DOMESTIC HOT-WATER SUPPLY SYSTEMS; ELEMENTS OR COMPONENTS THEREFOR
    • F24D2200/00—Heat sources or energy sources
    • F24D2200/16—Waste heat
    • F24D2200/30—Friction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S23/00—Arrangements for concentrating solar-rays for solar heat collectors
    • F24S23/70—Arrangements for concentrating solar-rays for solar heat collectors with reflectors
    • F24S23/71—Arrangements for concentrating solar-rays for solar heat collectors with reflectors with parabolic reflective surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/10—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
    • F28D7/103—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically consisting of more than two coaxial conduits or modules of more than two coaxial conduits
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B10/00—Integration of renewable energy sources in buildings
    • Y02B10/20—Solar thermal
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B30/00—Energy efficient heating, ventilation or air conditioning [HVAC]
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    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Definitions

  • the present disclosure is related to internally reinforced structural composites, suitable uses for such composites, and associated methods of manufacturing.
  • U.S. Patent No. 3,404,061 discloses a graphite material having expanded particles compressed together without a binder material.
  • graphite material is not sufficiently strong and highly variable in quality.
  • U.S. Patent No. 3,935,354 discloses a dense carbon-carbon composite that is strong.
  • a deficiency of this carbon-carbon composite is that its production requires large investments in equipment and energy, and the production has low yields of desired results per mass of carbon. Accordingly, several improvements in reinforcing composite structural materials may be desirable.
  • Figure 1 is a flow chart illustrating a process of manufacturing a reinforced structural composite in accordance with embodiments of the technology.
  • Figures 2A-2C are perspective views of a precursor undergoing certain stages of the process in Figure 1.
  • Figure 3 is a cross-sectional view of a reactor configured to manufacture a reinforced structural composite in accordance with embodiments of the technology.
  • Figures 4A and 4B are perspective views of an elongated structure incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figures 5A and 5B are perspective views of a racket incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figure 6 is a cross-sectional view of a pressure vessel incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figure 7 is another cross-sectional view of the pressure vessel in Figure 6.
  • Figure 8 is a cross-sectional view of a fuel injector incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figure 9 is a cross-sectional view of a tube valve incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figure 10 is a cross-sectional view of a tube valve in an inward open application in accordance with embodiments of the technology.
  • Patent Applications filed concurrently herewith on August 16, 2010 and titled: METHODS AND APPARATUSES FOR DETECTION OF PROPERTIES OF FLUID CONVEYANCE SYSTEMS (Attorney Docket No. 69545-8003US); COMPREHENSIVE COST MODELING OF AUTOGENOUS SYSTEMS AND PROCESSES FOR THE PRODUCTION OF ENERGY, MATERIAL RESOURCES AND NUTRIENT REGIMES (Attorney Docket No. 69545-8025US); ELECTROLYTIC CELL AND METHOD OF USE THEREOF (Attorney Docket No.
  • exfoliate and “exfoliation” generally refer to the act or the operation for spreading or opening up particle aggregates (e.g., molecular layers) from a closed or folded state.
  • particle aggregates e.g., molecular layers
  • Figure 1 is a flow chart illustrating a process of manufacturing a reinforced structural composite in accordance with embodiments of the technology.
  • graphite is used as an example for manufacturing the reinforced structural composite.
  • embodiments of the process discussed below may also be applied to hexagonal boron nitride (BN) and/or other materials with generally similar crystal structure.
  • an initial stage of the process includes forming a precursor structural component (block 1).
  • forming the precursor structural component can include forming a single crystal precursor by decomposing methane and/or other hydrocarbons as follows:
  • the single crystal precursor may be produced via graphite conversion and/or other suitable techniques.
  • the endothermic heat requirement for the foregoing reactions is approximately 18 to 20 Kcal/mol of light paraffin (e.g., methane).
  • the required heat may be provided by combustion of the same or similar hydrocarbons.
  • the heating process may be supplemented by waste heat from a suitable energy conversion process.
  • the energy content of the carbon materials (e.g., graphite) produced is quite low. Thus, less energy is required to produce structures with greater strength and stiffness than producing steel I-beams and trusses.
  • the precursor may be a right cylinder of a suitable cross- sectional shape and length.
  • the precursor can include a cylindrical graphite crystal with a plurality of basal (or a-b) planes defining cross sections of the crystal, and a c-axis along an axis of rotation for the cylinder, as discussed in more detail below with reference to Figures 2A-2C.
  • the precursor can also include cross sections that are squares, triangles, rectangles, hexagons, octagons, ellipses, and/or irregular shapes based on particular design criteria.
  • the cross sections of the precursor can have rounded corners to reduce stress risers.
  • the formed precursor according to the foregoing processes can have superior material properties in comparison with other materials.
  • the precursor can have high strength at elevated temperatures.
  • the precursor can be resistant to oxidation in air up to about 650°C.
  • the precursor can provide thermal conductivity generally similar to copper (Cu) in any direction in the basal planes at room temperature.
  • the precursor can also have a thermal conductivity like ceramics along the c-axis. Thermal expansion can be low in the basal planes but can become large (e.g., nearly 12 times greater) along the c-axis at elevated temperatures (e.g., 2200°C).
  • the precursor can have high tensile strength in the basal planes but low tensile strength along the c-axis.
  • the bonding strength in basal planes is believed to be about 150-170 Kcal/g-atom.
  • the Van der Waal bonding energy along the c-axis between basal planes is believed to be about 1.3 to 1.6 Kcal/g-atom.
  • the basal planes may be forced apart to cause cleavage of the crystal structure in the precursor.
  • forming the precursor structural composite can also include mechanically processing the formed precursor based on a target structural configuration and/or dimension.
  • the precursor may be machined to near net finish dimensions and ground to produce desired smoothness and finish.
  • the precursor may be milled, cut, shaped, detailed, degreased, and/or otherwise altered mechanically.
  • a subsequent stage of the process can include preparing the precursor for exfoliation (block 2).
  • the precursor may be subject to chemical conditioning and subsequent hydrating.
  • the precursor may be soaked in a suitable oxidizing medium (e.g., chromic acid, nitric acid, potassium chlorate, sulfuric acid, and/or a combination thereof) under agitation at about 80°C to 100°C for a period of time (e.g., 8 hours).
  • the precursor may also be pressurized (e.g., at 10 atmospheres or higher) and at higher temperatures (e.g., about 150°C to 180°C).
  • the precursor can then be washed in distilled or deionized water to remove the oxidizing medium and to hydrate the precursor.
  • the precursor may be subject to hydration and/or other suitable operations to implant interstitial molecules without chemical conditioning.
  • the process may also include neutralizing the oxidizing medium and/or other suitable operations.
  • the stage of preparing the precursor for exfoliation may be omitted.
  • graphite crystals (at least in the a form) have a layered structure.
  • the carbon atoms are arranged in a hexagonal lattice with an atomic separation of 0.142 nm. Adjacent layers of the hexagonal lattice are separated by a distance of 0.335 nm.
  • the basal planes may be expanded and small molecules (e.g., water, hydrogen, oxygen, nitrogen, argon, silicon, phosphorous, boron, fluorine, a metal, etc.) may be "sandwiched" between layers of the hexagonal lattice.
  • small molecules e.g., water, hydrogen, oxygen, nitrogen, argon, silicon, phosphorous, boron, fluorine, a metal, etc.
  • another stage of the process can include exfoliating the precursor based on a target density and/or strength to form a reinforced structural composite (block 3).
  • the prepared precursor can be quickly heated in a furnace at an elevated exfoliation temperature (e.g., 900°C) in an inert atmosphere and continuous removal of emissions (e.g., water vapor) from the precursor.
  • an elevated exfoliation temperature e.g., 900°C
  • continuous removal of emissions e.g., water vapor
  • the precursor can be greatly expanded to form a reinforced structural composite with low density and little residual stress in the expanded basal planes.
  • the precursor may include a central hole, and a pin and/or other support structures may be inserted into the central hole to help keep the basal planes stacked during the exfoliation operation.
  • the pin and/or other support structures may also serve as a central heat source during the exfoliation operation for improving heat transfer to the precursor.
  • the precursor may be exfoliated via radio frequency irradiation, resistive electrical heating, and/or other suitable heating techniques.
  • the exfoliation operation can include exfoliating every other basal plane, every third basal plane, every fourth basal plane, and so forth based on a target density, specific heat, thermal conductivity, structural and other properties of the reinforced structural composite. For example, in one embodiment, by adjusting a concentration of the exfoliating agent, an average target exfoliation percentage (e.g., 50%, 33.3%, 25%, and/or other suitable percentage values) may be achieved. In other embodiments, the exfoliation operation can also include adjusting at least one of an exfoliation temperature, an exfoliation duration, and/or other suitable operating parameters based on the target property of the reinforced structural composite.
  • an average target exfoliation percentage e.g. 50%, 33.3%, 25%, and/or other suitable percentage values
  • the exfoliation operation can also include cooling the precursor to a desired process temperature (e.g., 600°C) and closing the expanded crystal via press forming along the c-axis based on a target density and/or other property of the reinforced structural composite.
  • the resulting reinforced structural composite may have a density of about 0.08 g/cc or less, or may have a density up to about 2.00 g/cc or more depending upon a target strength of the reinforced structural composite. Generally, it is believed that the higher the density, the greater the tensile and compressive strengths in the reinforced structural composite.
  • furnace fixtures and/or a central pin with stops may be provided to limit the degree of initial expansion and to directly produce the desired density during the exfoliation operation.
  • the process can optionally include post treating the formed reinforced structural composite (block 4).
  • the formed reinforced structural composite may be fitted with heat exchanger tubing, axially reinforcing rods, and/or other suitable components.
  • the formed reinforced structural composite can be stabilized by forming a surface support material on the reinforced structural composite.
  • the surface support material may be selected based on particular application results such as pressure containment, maximization of section modulus per resulting truss weight, load spreading and absorption of impact forces, heat transfer into and out of the volume between the basal planes, and/or other suitable results.
  • the surface support material can include glass or carbon fibers coated with epoxy and/or other suitable adhesives. Such surface support material may be layered along the c-axis or within 60° of the c-axis of the reinforced structural composite for stabilizing the spaced apart basal planes.
  • the surface support material can include one or more layers of graphite film (e.g., adhesively coated pyrolytic graphite films with about 5-50 ⁇ thickness). The resulting composite structure can have a low adhesive content and low surface membrane anisotropy because the pyrolytic graphite film has high strength in all directions.
  • the graphite film may be provided with various surface capabilities. For example, when high strength, high temperature, and/or high heat transfer capabilities are desired, the graphite film may be coated with diamond-like carbon, a suitable braze metal or metal alloy (e.g., as copper, nickel, cobalt, aluminum, or a combination thereof). The coated reinforced structural composite may then be heat treated to diffuse or braze bond the reinforced structural composite to the graphite film. Diffusion bonding provides high integrity of the graphite films to each other and good heat and load transfer between the reinforced structural composite and the graphite films.
  • a suitable braze metal or metal alloy e.g., as copper, nickel, cobalt, aluminum, or a combination thereof.
  • the coated reinforced structural composite may then be heat treated to diffuse or braze bond the reinforced structural composite to the graphite film. Diffusion bonding provides high integrity of the graphite films to each other and good heat and load transfer between the reinforced structural composite and the graphite films.
  • heat treating the coated reinforced structural composite may include reordering of diamond-like carbon to graphite during the heat treatment.
  • diamond-like carbon coatings may be used for bonding short strips of graphite film into a long strip with a target length.
  • Spontaneous reordering from diamond-like carbon to graphite during heat treatment can also provide activation energy for diffusion bonding of the surface support material to the reinforced structural composite.
  • Diamond-like carbon may be coated onto the graphite film via chemical vapor deposition and/or other suitable techniques with a precursor gas.
  • the chemistry of the precursor gas may be adjusted to dope the diamond-like coating with oxygen, fluorine, hydrogen, phosphorous, silicon, and/or other suitable dopants.
  • the diffusion bonding process may be controlled based on target physical and electrical properties of a final product.
  • diamond-like coatings may be formed via direct ion beam source deposition.
  • the outside surface of the reinforced stmctural composite may be insulated with a suitable organic or ceramic closed-cell foam or hardened plastic.
  • the surface support material may be formed on the reinforced structural composite when the reinforced structural composite is under a vacuum while the surface support material is under pressure.
  • FIGS 2A-2C are perspective views of a precursor 5 undergoing certain stages of the process in Figure 1.
  • the precursor 5 includes a plurality of basal planes 6 (identified individually as first, second, and third basal planes 6a, 6b, and 6c, respectively) extending along the c-axis.
  • the basal planes 6 are generally parallel to one another.
  • Adjacent basal planes 6a, 6b, and 6c have a first spacing Dj (e.g., 0.142 nm).
  • Dj e.g. 0.142 nm
  • Three basal planes 6a, 6b, and 6c each with a circular shape are illustrated in Figures 2A-2C for illustration purposes.
  • the precursor 5 can include any suitable number of basal planes.
  • the precursor 5 can include a plurality of exfoliation agents 7 "sandwiched" between adjacent basal planes 6.
  • the exfoliation agents 7 can include water, hydrogen, oxygen, nitrogen, argon, silicon, phosphorous, boron, fluorine, a metal, and/or a combination thereof.
  • the concentration and/or composition of the exfoliation agents 7 may be controlled by adjusting at least one of a hydration time, a period of chemical conditioning, compositions of chemical conditioning, and/or other suitable operating parameters of the precursor preparation operation.
  • the exfoliation agents 7 are expanded and optionally removed from the interstitial spaces in the precursor 5.
  • the expansion of the exfoliation agents 7 cause the basal planes 6 to have a second spacing D 2 that is larger than the first spacing Di.
  • the second spacing D 2 can be 300 times, 200 times, or 100 times larger than the first spacing D 1 .
  • the second spacing D 2 can have other relations with the first spacing Di.
  • the spacing between the adjacent basal planes 6 may be adjusted based on a target density, tensile strength, compressive strength, shear strength, yield strength, brittleness, specific heat, thermal conductivity, structural and other properties of the reinforced structural composite.
  • FIG 3 is a cross-sectional view of a reactor 100 configured to manufacture a reinforced structural composite in accordance with embodiments of the technology.
  • the reactor 100 can include a ceramic stand 104, a resistor tube 106, and two cooling disks 110 (only one cooling disk 1 10 is illustrated in Figure 3 for clarity). Even though only particular components are shown in Figure 3, in other embodiments, the reactor 100 may include other suitable mechanical and/or electrical components.
  • the resistor tube 106 can include a first end 106a configured to receive a precursor 102 and the stand 104.
  • the resistor tube 106 can also include a second end 106b coupled to the cooling disk 110.
  • Suitable resistor tube materials include carbon, polycr stalline graphite, molybdenum disilicide, silicon carbide, single crystal graphite, and/or others with suitable materials with adequate thermal shock resistance and capable of sustained heating to about 1,000°C.
  • the resistor tube 106 may be thermally insulated by placement of foils of reflective material around the resistor tube 106 and/or by wrapping the resistor tube 106 with a high temperature ceramic wool.
  • the resistor tube 106 also includes conductors 108 (e.g., copper, aluminum, etc.).
  • the conductors 108 can be cooled by passing of water or other suitable coolant through ports 120 and passages 122 in the cooling disk 110. Water or other suitable coolant may be sealed by O-rings 112 and 1 14.
  • a protective atmosphere which may be vacuum or a protective gas (e.g., carbon dioxide, argon, and/or other inert gases) may be provided to the interior of resistor tube 106 through a port 116 in the cooling disk 1 10. Emitted exfoliation agents during exfoliation of the precursor 102 may be removed by flushing of the protective gas and/or by removal to vacuum.
  • a protective atmosphere may be provided on the outside of resistor tube 106 by injecting carbon dioxide, argon, and/or another inert gas through a port 124 and held in place by a generally impervious insulator membrane 128 (e.g., bonded ceramic felt) wrapped around top and bottom disks 110 and held in place by at least one circumferential clamp (not shown) to the cooling disk 1 10.
  • a generally impervious insulator membrane 128 e.g., bonded ceramic felt
  • three or any other desired number of high temperature super-alloy bolts 1 17 may be used to hold the resistor tube 106 between the cooling disks 110.
  • the bolts 117 may be electrically insulated with insulators 118. Electrical cables that deliver alternating or direct current can be attached by suitable cable nuts, washers, and spring washers (not shown). Matching thread 126 allows the cable nuts to be tightened to assure low resistance contact between electrical cables and the conductors 108.
  • the reactor 100 can also include spring washers 130 (one is shown) to accommodate thermal expansion and contraction of the resistor tube 106. The spring washers 130 may be placed on the insulators 118 and the cooling disks 110.
  • the precursor 102 (e.g., generally similar to the precursor 5 in Figure 2A) can be mounted on the stand 104 and inserted together into the bore of the resistor tube 106 (as shown in phantom lines).
  • the resistor tube 106 is then heated by passing electric current from the conductor 108 proximate the second end 106b of the resistor tube 106 through the resistor tube 106 to another conductor 108 (not shown) proximate the first end 106a of the resistor tube 106.
  • Several embodiments of the reinforced structural composite discussed above with reference to Figures 1 -2C may have applications in a wide range of technical fields.
  • several embodiments of the reinforced structural composite may be used to construct truss assemblies for transportation applications.
  • Such truss assemblies can have lower curb weight, longer life, and improved safety compared to conventional materials such as aluminum alloys, steel, and conventional composites.
  • several embodiments of the reinforced structural composite may be used to construct airplane wings, rudders, flaps, spoilers, nacelle components, passenger seat assemblies, interior panels, and/or other airplane components.
  • airplane components are lighter in weight, stronger, and last much longer because of high fatigue life and high endurance strength.
  • reinforced structural composite may also be used in virtually all transportation systems from roller skates to rail trains to produce stiffer, higher strength, lower weight, and longer life components.
  • devices constructed with several embodiments of the reinforced structural composite are discussed below with reference to Figures 4A-10.
  • Figures 4A and 4B are perspective views of an elongated structure incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • the elongated structure 10 may be a vaulting pole.
  • the elongated structure 10 may be a ski pole, a hiking pole, a golf club, a shin guard, a face guard, a helmet, a bat, a shoe, and/or any other suitable structures.
  • the elongated structure 10 includes a reinforced structural composite 12 and a surface membrane 14 adhered thereon.
  • the elongated structure 10 may also include a port 18 and an optionally internal lumen (not shown) in the reinforced structural composite 12.
  • the stiffness of the elongated structure may be adjusted by pressurizing the interior space formed by the reinforced structural composite 12 and adhered surface membrane 14. Fill port 18 allows the interior pressure to be increased or decreased based on a target stiffness.
  • the flexibility, strength, and/or other characteristics of the elongated structure 10 may also be controlled by adjusting the spacing between basal planes 6 ( Figures 2A-2C) of the reinforced structural composite. The extreme strength and capability of providing strength in all directions of the basal planes 6 provides a safety factor while allowing precision tuning of the characteristics of the elongated structure 10 based on local conditions and/or other suitable parameters.
  • FIGs 5A and 5B are perspective views of a racket 20 incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • the racket 20 can be a tennis racket.
  • the racket 20 can be a badminton racket and/or other suitable types of racket.
  • the racket 20 includes a shaft 21 attached and/or formed integral with an head 23, at least one of which can be constructed from several embodiments of the reinforced structural composite 22 discussed above.
  • fibers 24 e.g., epoxy coated
  • fibers 24 can be used to stabilize the reinforced structural composite 22.
  • the shaft 21 and/or the head 23 can have high section modulus for tensioning the strings 26.
  • the shaft 21 can include an internal space 25 in fluid communication with a charge port 34.
  • the shaft 21 of the racket 20 may be pressurized with a fluid (e.g., air) to tension the strings 26 by increasing the circumference of the composite and the distance each string 26 traverses.
  • a fluid e.g., air
  • Figure 6 is a cross-sectional view of a pressure vessel 80 incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • Figure 7 is another cross-sectional view of the pressure vessel 80 in Figure 6.
  • the pressure vessel 80 includes a reinforced structural composite 87 and a central hole 81 bored therethrough to accommodate a suitable perforated tube or wire cloth 78 with perorations 86.
  • the reinforced structural composite 87 can include a plurality of basal planes 88 extending longitudinally along the bore 81.
  • the perforated tube or wire cloth 78 can hold the basal planes 88 in place during exfoliation, provide longitudinal reinforcement to the pressure vessel 80, and circulate fluids through the perforations 86 into and out of the basal planes 88.
  • the pressure vessel 80 can also include fittings 82 and 84 with a separation designed to allow the crystals to exfoliate to a desired basal-plane spacing. Further heat transfer and or fluid transfer may be provided by tubes (not shown) that pass substantially perpendicular to the basal planes 88 in the pressure vessel 80.
  • outer perimeters of the basal planes 88 can be coated with an adhesive or diffusion braze formula (not shown) and encased within a suitable low-permeability membrane 90. Exfoliated basal planes 88 can thus form a high strength radial reinforcement to the membrane 90.
  • Suitable adhesives can include a thermoset composition (e.g., epoxies, phenol- formaldehyde, melamine-formaldehyde, silicones and addition-polyimide), a composition containing siloxanes, a thermoplastic (e.g., aromatic polyesters, unsated polyesters, and polyetherimides).
  • the outer perimeters of the basal planes 88 may also be coated for diffusion bonding (e.g., a diamond-like material).
  • Suitable materials for the membrane 90 include graphite foils, deep-drawn or spin formed titanium, aluminum, stainless steel, electro-formed nickel, and/or other suitable materials.
  • the membrane 90 can also include composite membranes having metallized thin films of polyethylene terephthalate, ethylene chlorotrifluoroethylene, polyvinylidene fluoride, and polyolefins. Suitable metallizing materials include iron, aluminum, titanium, chromium, nickel, or alloys thereof.
  • carbon deposits including those described in “Dual Ion Beam Deposition of Carbon Films with Diamond Like Properties” (NASA TM-83743), the disclosure of which ins incorporated herein in its entirety, may also be used for joining of basal planes 88 to the membrane 90.
  • heat transfer to/from the pressure vessel 80 may be controlled by incorporating a heat spreader 92 over the membrane 90.
  • the heat spreader 92 can include corrugated fins covered by an insulative membrane 94 to form a honeycomb of passageways 96 with an inlet 89a and an outlet 89b ( Figure 6).
  • a heat transfer fluid may be circulated through the passageways 96.
  • Suitable heat transfer fluids can include hydrogen, air, water, engine exhaust, and other heat transfer.
  • filtered ambient-temperature air may be circulated through the passageways 96 to remove heat from the basal planes 88 as fuel gases are loaded into storage as adsorbed monolayers and as "arrested" gases between monolayers.
  • the term “arrested” generally refers to gases that have entered the space between the monolayers on exfoliated basal planes 88, transferred energy to the basal planes 88, and as a result have reduced vapor pressures.
  • Materials suitable for the insulative membrane 94 include thermoplastics and thermosetting compounds which may be foamed, laminated, reinforced, or un-reinforced.
  • the heat spreader 92 may be formed on the cylindrical portion of the membrane 90 continuing over a portion of the ends of the membrane 90 via diffusion or metallurgically bonding. In other embodiments, the heat spreader 92 may have other configurations.
  • the basal planes 88 may be longitudinally reinforced by applying high-strength roving, yarns, and/or fibers over the membrane 90.
  • axial reinforcement roving 98 may be applied over the corrugated surface of the heat spreader 92, allowing the corrugated surface of the heat spreader 92 to serve as a load spreader against the membrane 90 while avoiding interfering with heat exchange between the membrane 90 and heat spreader 92.
  • Suitable high strength reinforcement yarns and cables may be made from boron, boron nitride, carbon, graphite, glass, silicon carbide, refractory metals, and/or ceramic fibers.
  • Epoxy, polyamide varnishes and/or other suitable adhesion and matrix resins may be suitable as adhesive coatings on yarns and cables.
  • FIG 8 is a cross-sectional view of a fuel injector 400 incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • the fuel injector 400 overcomes a difficult problem with many modern diesel engines that limit the size of the diesel fuel injector port to about 8.4 mm (0.33") in diameter.
  • the fuel injector 400 includes a stationary ignition conductor 404 (e.g., a Liz wire bundle or conductive rod).
  • a cable group 406 e.g., fiber optic cables
  • the cable group 406 may be insulated with a stationary coaxial tube 408.
  • the insulator tube 408 can be constructed from a ceramic insulator as disclosed copending applications incorporated above.
  • the insulator tube 408 can be constructed from other suitable materials that can contain 80KV DC or AC at temperatures up to about 1000°F.
  • the insulator tube 408 can also serve as a low friction central journal bearing surface for guiding unidirectional motion of a tube valve 410 along with a coaxial plunger 414.
  • the plunger 414 is normally closed to urge the tube valve 410 to stay in a closed position at the flared area against a valve seat 412. As such, an outward opening valve is formed.
  • ignition voltage applied to a stationary terminal 424 is transmitted to the ignition conductor 404 to develop plasma discharge blasts of ionized fuel that is rapidly accelerated as injected into a combustion chamber 428.
  • the plasma generating ignition conductor 404 includes a central stationary electrode 406 in which plasma can be started by acicular features (e.g., sharp threads 440) and the internal diameter of the port bore 402.
  • a thin electrode liner 403 may be used to protect the bore 402 instead of using high frequency AC to eliminate plasma erosion as disclosed in co-pending applications incorporated above.
  • the tube valve 410 can include reinforced structural composite.
  • Figure 9 is a cross-sectional view of a tube valve 410, shown as the tube valve 600 in Figure 9, incorporating embodiments of the reinforced structural composite in accordance with embodiments of the technology.
  • a relatively low density spaced graphite structural core 602 provides a desired geometry.
  • the core 602 can include a valve seat 614 at one end and One or more provisions such as concentric tubes 608 and/or 610 bonded to the outside of surface 606 at a second end.
  • the core 602 can also include a suitable low-friction coating 604 (e.g., polyimide, PEEK, Parylene H, or PTFE copolymer) formed on the inside surfaces of a tubular elastomer (e.g., fluorosilicone).
  • a tubular elastomer e.g., fluorosilicone
  • the elastomer may be applied to the flared valve surface 612 for inward opening valve operation.
  • High strength materials such as graphite filament reinforced polyimide or graphite tape with thermoset adhesives is applied to the outside surfaces 606.
  • an elastomer seal (e.g., fluorosilicone, perfluoroelastomer, or other fluoroelastomers) of conforming shape may be applied to a valve seal 614.
  • One or more provisions such as concentric tubes 608 and/or 610 are bonded to the outside of surface 606 at locations such as 432 and/or 430 for allowing plunger 414 to apply unidirectional force to rapidly push valve 410 off of valve seat 412 and to close the tube valve 410 when compression spring 432 returns plunger 414 to the normally closed position.
  • Fuel flow may be routed as desired including from fitting 442 through or around a system for operating plunger 414 such as a piezoelectric or solenoid winding 426, then through ports 444 to enter the concentric flow channel 446.
  • the flow channel 446 may be supported and spaced between a suitable ceramic or polymer insulator 418 and the insulator tube 408 by a long- lead spiral 422 constructed from, e.g., PTFE or PEEK monofilament.
  • an inward opening tube valve 500 system includes a core assembly 600 that provides for an opening seal 612 from a valve seat 618 when fuel delivery is desired in response the plunger 620 impacting against concentric feature 610.
  • the concentric feature 610 is bonded to tube surface 606 to apply tensile force to the open valve 500 after plunger 620 has gained kinetic energy by motion through unidirectional distance Di.
  • the tube valve 500 is moved to open seal 612 from seat 618 (D 2 -Di).
  • Ceramic 640 provides high voltage containment and supports ceramic tube 408'.
  • a suitable metal alloy cap 642 holds ceramic end-cap 640 in place.
  • At least the tubular portion 616 of the tube valve 500 can be constructed from a light weight but strong graphite structural core 616 reinforced by a carbon-carbon layer.
  • the core 616 can be generally similar in structure as the elongated structure 10 in Figure 4A.
  • the carbon-carbon layer may be prepared from a suitable precursor application of carbon donor (e.g., petroleum pitch or a thermoplastic such as a polyolefin or PAN).
  • carbon donor e.g., petroleum pitch or a thermoplastic such as a polyolefin or PAN
  • Radio frequency shielding and protection 650 may be provided by carbon-carbon outside layer 630. Additional protection may be established by plating surface 636 with a suitable alloy such as a nickel alloy that may be brazed to the threaded portion 640 by a suitable braze alloy composition.
  • the tube 420 ( Figure 8) and housing 460 ( Figure 8) may be prepared as a low density spaced graphite structural core with carbon-carbon layers on the inside and outside diameters. Such components may be joined by threads or by brazing with a suitable alloy.
  • a hydrogen-characterized fuel e.g., ammonia
  • other fuels with low energy density e.g., carbon monoxide and hydrogen
  • the carried commodity may be reformed using waste heat from the engines as follow:
  • propulsion engines including heat engines such as compression-ignition diesel type engines, various rotary combustion engines, and gas turbines to operation on fuels that may be reformed from such commodities by endothermic reactions in which the heat rejected by such heat engines is utilized to drive such reactions.
  • heat engines such as compression-ignition diesel type engines, various rotary combustion engines, and gas turbines
  • gas turbines to operation on fuels that may be reformed from such commodities by endothermic reactions in which the heat rejected by such heat engines is utilized to drive such reactions.
  • several embodiments of the fuel injector 400 may also be used in power plants, chemical plants, and/or other suitable locations with heat producing engines.
  • Thermo-chemical regeneration using heat rejected by an engine provides attractive fuel savings because the hydrogen characterized fuels that are produced yield 15 to 30% more energy upon combustion than their feedstock.
  • the embodiments of the fuel injector 400 allows hydrogen characterized fuels to combust up to 12 times faster than diesel or bunker fuels, thus greatly improving engine efficiency and eliminating particulates in the exhaust of the engine.

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Abstract

L'invention concerne des composites structuraux intérieurement renforcés, des utilisations appropriées de ces composites, ainsi que des procédés de fabrication associés. Dans un premier mode de réalisation, un procédé de fabrication d'un composant structural renforcé consiste d'abord à former un précurseur possédant un réseau cristallin pourvu d'une pluralité de couches en treillis, et à exfolier ensuite le précurseur. Par conséquent, la distance entre les paires adjacentes de la pluralité de couches en treillis s'allonge. Par ailleurs, le procédé consiste à envelopper le précurseur ainsi exfolié d'un matériau de support de surface autour d'au moins une partie de la circonférence des couches en treillis individuelles du précurseur exfolié.
EP10814155.7A 2009-08-27 2010-08-16 Composites structuraux intérieurement renforcés et procédés de fabrication associés Withdrawn EP2625031A4 (fr)

Applications Claiming Priority (9)

Application Number Priority Date Filing Date Title
US23747609P 2009-08-27 2009-08-27
US30440310P 2010-02-13 2010-02-13
US12/707,653 US8172990B2 (en) 2009-02-17 2010-02-17 Apparatus and method for controlling nucleation during electrolysis
PCT/US2010/024499 WO2010096505A1 (fr) 2009-02-17 2010-02-17 Appareil et procédé de capture de gaz au cours d'une électrolyse
PCT/US2010/024498 WO2010096504A1 (fr) 2009-02-17 2010-02-17 Appareil et procédé de contrôle de la nucléation au cours d'une électrolyse
US12/707,656 US8075749B2 (en) 2009-02-17 2010-02-17 Apparatus and method for gas capture during electrolysis
PCT/US2010/024497 WO2010096503A1 (fr) 2009-02-17 2010-02-17 Cellule électrolytique et son procédé d'utilisation
US12/707,651 US8075748B2 (en) 2009-02-17 2010-02-17 Electrolytic cell and method of use thereof
PCT/US2010/045658 WO2011028400A2 (fr) 2009-08-27 2010-08-16 Composites structuraux intérieurement renforcés et procédés de fabrication associés

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EP2625031A2 true EP2625031A2 (fr) 2013-08-14
EP2625031A4 EP2625031A4 (fr) 2016-06-08

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EP10814156.5A Withdrawn EP2470787A4 (fr) 2009-08-27 2010-08-16 Système énergétique destiné à une habitation
EP10855997.2A Withdrawn EP2470786A4 (fr) 2009-08-27 2010-08-16 Systèmes et procédés de développement économique durable par production à spectre complet intégré d'énergie renouvelable
EP10817626.4A Withdrawn EP2470752A4 (fr) 2009-08-27 2010-08-16 Ensembles de conversion d'énergie et procédés d'utilisation et de fabrication correspondants
EP10858212.3A Withdrawn EP2567066A4 (fr) 2009-08-27 2010-08-16 Système de conversion d'hydrate de gaz pour la récolte de dépôts d'hydrate d'hydrocarbure
EP10814157.3A Withdrawn EP2470788A4 (fr) 2009-08-27 2010-08-16 Augmentation de l'efficacité de systèmes de conversion de l'énergie thermique océanique complétés (sotec)
EP10814155.7A Withdrawn EP2625031A4 (fr) 2009-08-27 2010-08-16 Composites structuraux intérieurement renforcés et procédés de fabrication associés
EP10846282.1A Withdrawn EP2470822A4 (fr) 2009-08-27 2010-08-16 Appareils et procédés pour stocker et/ou filtrer une substance

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EP10814156.5A Withdrawn EP2470787A4 (fr) 2009-08-27 2010-08-16 Système énergétique destiné à une habitation
EP10855997.2A Withdrawn EP2470786A4 (fr) 2009-08-27 2010-08-16 Systèmes et procédés de développement économique durable par production à spectre complet intégré d'énergie renouvelable
EP10817626.4A Withdrawn EP2470752A4 (fr) 2009-08-27 2010-08-16 Ensembles de conversion d'énergie et procédés d'utilisation et de fabrication correspondants
EP10858212.3A Withdrawn EP2567066A4 (fr) 2009-08-27 2010-08-16 Système de conversion d'hydrate de gaz pour la récolte de dépôts d'hydrate d'hydrocarbure
EP10814157.3A Withdrawn EP2470788A4 (fr) 2009-08-27 2010-08-16 Augmentation de l'efficacité de systèmes de conversion de l'énergie thermique océanique complétés (sotec)

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JP (6) JP2013503310A (fr)
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BR (1) BR112012004093A2 (fr)
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EP2470752A2 (fr) 2012-07-04
JP2014025587A (ja) 2014-02-06
WO2011034677A3 (fr) 2011-05-12
JP2013503299A (ja) 2013-01-31

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