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US20080131823A1 - Homogeous Combustion Method and Thermal Generator Using Such a Method - Google Patents

Homogeous Combustion Method and Thermal Generator Using Such a Method Download PDF

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Publication number
US20080131823A1
US20080131823A1 US11/571,699 US57169905A US2008131823A1 US 20080131823 A1 US20080131823 A1 US 20080131823A1 US 57169905 A US57169905 A US 57169905A US 2008131823 A1 US2008131823 A1 US 2008131823A1
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United States
Prior art keywords
combustion
fuel
injection means
combustion chamber
axis
Prior art date
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Abandoned
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US11/571,699
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English (en)
Inventor
Tidjani Niass
Etienne Lebas
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IFP Energies Nouvelles IFPEN
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Individual
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Assigned to INSTITUT FRANCAIS DU PETROLE reassignment INSTITUT FRANCAIS DU PETROLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LEBAS, ETIENNE, NIASS, TIDJANI
Publication of US20080131823A1 publication Critical patent/US20080131823A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/08—Disposition of burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/006—Combustion apparatus characterised by the shape of the combustion chamber the chamber being arranged for cyclonic combustion
    • F23C3/008—Combustion apparatus characterised by the shape of the combustion chamber the chamber being arranged for cyclonic combustion for pulverulent fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/04—Disposition of air supply not passing through burner to obtain maximum heat transfer to wall of combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D1/00—Burners for combustion of pulverulent fuel
    • F23D1/02—Vortex burners, e.g. for cyclone-type combustion apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07007—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber using specific ranges of oxygen percentage
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery

Definitions

  • the present invention relates to a method for burning a fuel and a high-oxygen-content combustion agent, and to a thermal generator using such a method.
  • combustion is highly localized and takes place in a smaller space than the total volume of the combustion chamber.
  • This combustion takes place in the form of a flame, which brings about temperature spikes with formation of thermal NO and difficulty in controlling heat flows which are intense and localized.
  • the goal of the present invention is to overcome the above drawbacks.
  • the invention relates to a combustion method wherein a fuel and a combustion agent with a high oxygen content are injected into a combustion chamber, particularly a thermal generator, said combustion chamber having at least one fuel injection means and at least one wall essentially parallel to the axis of said injection means, characterized by comprising:
  • the combustion agent injection can be counter-current to the fuel injection.
  • the combustion agent can be injected in a helical or circular movement around the axis of the fuel injection means.
  • the combustion agent can be injected essentially perpendicularly to the axis of the fuel injection means.
  • the combustion agent injection rate can be between 50 and 150 m/s.
  • the oxidizing combustion agent can be a fluid containing at least 90% oxygen.
  • the fuel can be injected in the shape of a cone.
  • the method can also include post-combustion of the fumes at the combustion chamber outlet.
  • the invention also relates to a thermal generator having a combustion chamber in which combustion of a mixture of a fuel and an oxidizing combustion agent occurs, said combustion chamber having at least one fuel injection means and at least one wall essentially parallel to the axis of said injection means, characterized by having at least one means for injecting the fuel in the direction of the wall and at least one means for injecting the combustion agent such that it encounters the fuel in the vicinity of said wall at a rate between 1 and 300 m/s such that said fuel and said combustion agent are distributed over the entire volume of the combustion chamber before entering into reaction.
  • the fuel injection means can also have a deflector.
  • the fuel injection means can be mounted on one of the faces and be disposed substantially in the axis of the combustion chamber.
  • the combustion agent injection means can be mounted on the other face and be disposed at a distance from the axis of the combustion chamber and in the vicinity of the wall.
  • At least one combustion agent injection means can be mounted on the peripheral wall.
  • the combustion agent injection means can be located at a distance from the fuel injection means.
  • the fuel injection means can be mounted on the wall and be disposed essentially orthogonally to the axis of combustion chamber.
  • the combustion agent injection means can be mounted on the wall and be essentially orthogonal to the axis of fuel injection means.
  • a plurality of injection means extending along the combustion chamber axis can be provided.
  • the combustion agent injection means can be sloping in order to obtain a circular or helical movement of the combustion agent around the axis of the fuel injection means.
  • FIG. 1 is a schematic view in axial section of a thermal generator using the method according to the invention
  • FIG. 2 is a schematic view in axial section of an alternative generator using the method according to the invention.
  • FIG. 3 is a schematic view in axial section of a variant of the generator in FIG. 1 .
  • FIG. 4 is a cross-sectional view along line 4 - 4 in FIG. 3 ;
  • FIG. 5 is a cross-sectional view showing a variant of FIG. 2 ;
  • FIG. 6 is a cross-sectional view along line 6 - 6 in FIG. 5 ;
  • FIG. 7 is a perspective view with a local cross section showing another embodiment of the invention.
  • a thermal generator 10 has, sequentially, a combustion chamber 20 with heat recovery at the walls, a zone 12 linking this combustion chamber to a post-combustion zone 14 , a supplementary heat recovery zone 16 , and a zone 18 for evacuating and/or processing the fumes coming from combustion.
  • the walls of generator 10 are advantageously membrane walls formed by tubes connected to each other by welded fins in order to seal these walls off from the outside.
  • These membrane walls preferably have the function of heating and/or vaporizing water in the case of steam production.
  • Certain parts of these walls can be covered with insulating materials to limit heat exchange and/or contact of the tubes with locally corrosive atmospheres.
  • the walls are also covered with insulating materials to limit heat losses.
  • the combustion chamber 20 can be of the cylindrical type as illustrated in the figure, or of any parallelepipedic type.
  • This chamber has a peripheral wall 22 , in this case a horizontal cylindrical wall concentric with axis XX′, delimited by two substantially vertical lateral faces 24 and 26 which, to simplify the following description, are called front face 24 and rear face 26 , the rear face being the face toward the linking zone 12 .
  • Front face 24 has a fuel injection means preferably located in the axis XX′ of the generator and for this reason the same axis designation is retained for this fuel injection means.
  • this injection means is preferably an injector 28 , advantageously provided with internal parts ensuring mixture of the fuel with an atomizing fluid.
  • the injector 28 can consist of a tube in which said fuel is carried by a fluid such as steam.
  • This injector whose axis is the same as the combustion chamber axis, is configured such that it sprays the fuel from axis XX′ into the entire combustion chamber, both toward the center of the chamber and toward the peripheral wall 22 of the chamber, in the form of a cone as shown by arrows A in order to distribute the fuel throughout the chamber.
  • the vertex angle of this cone is between 15 and 1800, and preferably between 60 and 150°, and the injection rate is chosen by the individual skilled in the art as a function of operating conditions in order to favor good penetration of the fuel droplets in the chamber.
  • the total volume of the combustion chamber is preferably between 0.5 and 50 m 3 .
  • An industrial boiler or a thermal generating plant can be comprised of a set of combustion chambers 20 , which chambers may or may not have a common face, and the combustion products generated in these chambers spill into one or more zones common to several or all of said chambers. If the chambers have a common face, said face may or may not be impermeable to gas, namely it can be comprised for example of a membrane wall or of pipes that are not connected.
  • a liquid fuel such as heavy fuel oil or pitch
  • it is preheated to a temperature between 50 and 300° C. to obtain an appropriate viscosity enabling this fuel to be thoroughly atomized.
  • This atomization can be effected simply by pressure or with the assistance of an auxiliary atomizing fluid such as steam.
  • the fuel is introduced into the generator in atomized form with most of the mass flow having a particle size less than 500 ⁇ m.
  • This fuel is carried and dispersed by an auxiliary fluid such as steam, with the ratio by weight between the fuel and the carrier fluid being between 0.1 and 10.
  • the present invention is not limited to the fuel types described above but also encompasses the use of gaseous fuels such as natural gas, fuel oil, refinery gas, etc.
  • the rear face 26 has at least one means for injecting an oxidizing combustion agent which is either a gas with a very high oxygen concentration, generally over 90%, or pure oxygen.
  • This combustion agent injection means is an injector 30 , preferably tubular and made of refractory material, whose axis is substantially parallel to axis XX′ while being disposed at a distance therefrom, preferably in the vicinity of wall 22 .
  • Injection of the fuel can also be assisted by any means, such as by fumes recycled from the dust arrester, which has the advantage of speeding up the combustion agent injection rate and favoring operation of combustion chamber 20 as an agitated reactor, limiting concentration heterogeneities due to oxygen injection.
  • the combustion agent injection rate is between 1 and 300 m/s and more particularly between 50 and 150 m/s.
  • the number of combustion agent injectors 30 , their locations, and the combustion agent injection rate will be determined by any means, particularly by digital simulation, to obtain substantial circulation of fuel as will be explained in the remainder of the description.
  • the fuel is injected into said chamber, through injector 28 , in all directions in space and particularly in the direction of the combustion agent injectors 30 , as indicated by arrows A, in order to ensure mingling of the fuel and the combustion agent.
  • Combustion agent injection and fuel injection are performed in such a way as to ensure intense turbulence throughout combustion chamber 20 .
  • coupling means that the direction of the combustion agent stream is essentially opposite that of the fuel and that the angle formed by the direction of the combustion agent stream and the fuel stream is between 90° and 180°.
  • combustion agent is injected such that it encounters this fuel in an extensive volume near wall 22 to create swirls that will lead to fuel/combustion agent mixing near this wall then extend over the entire combustion chamber section.
  • the fuel injection conditions such as initial fuel rate, spatial distribution of fuel, droplet and particle size, number of injectors, and atomization or carrier fluid flowrate, and the combustion agent injection conditions such as the number of injection points, combustion agent rate, orientation of jets relative to the combustion chamber axis, and the flowrate of any carrier gas such as steam or recycled fumes, are determined for example by digital simulation such that the characteristic time of the turbulent fuel mixing remains less than the characteristic time of the chemical kinetics. Under these conditions, the reagents and products are mixed by turbulence before reacting. Thus, at no point in the combustion chamber does combustion speed up and create hot spots. Theoretically, combustion chamber 20 functions as a fully agitated reactor.
  • the fume temperature and composition are substantially homogenous throughout combustion chamber 20 .
  • This temperature is, in normal operation, between 600 and 2000° C. and preferably between 800 and 1500° C. so as to limit NOx formation associated with any unwanted air intake or the nitrogen in the fuel.
  • the rates of fuel and combustion agent injection into combustion chamber 20 are such that the mixture obtained has an overall stoichiometry less than 1, i.e. with excess fuel relative to the combustion agent. This limits formation of nitrogen oxides from the nitrogen in the fuel.
  • the temperature homogeneity prevents formation of thermal NO with the nitrogen coming from any air entering the combustion chamber.
  • the injections of combustion agent can be organized, still with the aid of digital simulation, such as to keep a slightly oxidizing atmosphere near the wall, while keeping the atmosphere rich overall to spare the wall from reducing corrosion phenomena.
  • the linking zone 12 which in this case is tubular in shape, connects the outlet of combustion chamber 20 to the post-combustion zone 14 which precedes the heat recovery zone 16 at the outlet of which the combustion fumes are evacuated and/or processed.
  • the linking zone has at least one additional oxidizing combustion agent injector 32 that mixes this fuel with the fumes coming from combustion chamber 20 .
  • This fuel/combustion agent mixture then penetrates into post-combustion zone 14 where combustion is completed.
  • the heat resulting from combustion in the post-combustion zone is recovered directly in this post-combustion zone thanks to, for example, means not shown such as membrane walls or suspended tubes, or in the heat recovery zone 16 by any means such as a heat exchanger 34 or a sequence of exchangers accommodated in this recovery zone.
  • the fumes coming from this recovery zone which are generally at a temperature between 150 and 300° C., are directed by zone 18 to an evacuation and/or processing means such as for example a dust arrester and a chimney (not shown in the figure).
  • an evacuation and/or processing means such as for example a dust arrester and a chimney (not shown in the figure).
  • FIG. 2 shows a variant of FIG. 1 and which has the same reference numerals as this figure.
  • the fuel is injected through an injector 28 , mounted on the front face 24 , extending inside combustion chamber 20 in the form of a tube.
  • This tube 28 whose axis is also the same as axis XX′ of combustion chamber 20 , has at its end a deflector 36 whose purpose is to convert the jets of fuel leaving the tube into jets directed at the peripheral wall 22 of combustion chamber 20 and to its front face 24 .
  • the fuel can be a solid, liquid, or gaseous fuel and the injection can be assisted or unassisted.
  • this tube is cooled either by a fluid such as water or by the mixture of fuel and booster fluid.
  • the combustion agent injection means is an injector 30 , or a series of injectors spaced axially along the axis of the combustion chamber, which is disposed on the peripheral horizontal wall 22 of combustion chamber 20 .
  • two series of three injectors are provided, located at a distance from the fuel outlet of injector 28 , and preferably in the vicinity of the front face 24 , each of the series being circumferentially spaced regularly from the other.
  • the fuel injection conditions such as initial fuel flowrate, spatial distribution of fuel, size of droplets or particles, number of injectors, and atomization or carrier fluid flowrate
  • the combustion agent injection conditions such as number of injection points, combustion agent flowrate, orientation of jets relative to combustion chamber axis, and flowrate of any carrier gas such as steam or recycled fumes
  • the characteristic time of the fuel turbulent mixing remains less than the characteristic time of the chemical kinetics.
  • the fuel is injected into said combustion chamber 20 from injector 28 , in all directions of space and particularly in the direction of the combustion agent injectors 30 , as indicated by arrows A, in order to ensure mingling of the fuel and the combustion agent.
  • combustion develops over a substantial volume of combustion chamber 20 and the walls of this chamber 20 are also kept in an oxidizing atmosphere with the advantages listed above.
  • FIGS. 3 and 4 show a variant of FIG. 1 and which, for clarity, have the same reference numerals as this figure.
  • the linking zone 12 has at least one injector of additional oxidizing combustion agent 32 which ensures mixing of this agent with the fumes coming from combustion chamber 20 ; this mixture of fuel and combustion agent then penetrates into the post-combustion zone 14 to complete combustion.
  • FIGS. 5 and 6 illustrate a variant of the embodiment of FIG. 2 and which also have the same main reference numerals.
  • the fuel is also injected into combustion chamber 20 in the form of a fuel cone 38 .
  • This fuel cone results from the action of deflector 36 which generates this cone whose base is opposite the front face 24 .
  • the injectors 30 or series of injectors are distributed circumferentially around the peripheral wall 22 and are sloped such as to introduce the combustion agent tangentially into combustion chamber 20 .
  • this arrangement has the purpose of favoring the mingling of fuel and combustion agent.
  • This agent which is injected circularly or helically, encounters the fuel near the wall 22 and mixes therewith, generating a mixture that develops over the entire combustion chamber.
  • combustion can develop over a substantial volume of combustion chamber 20 .
  • the unused fuel leaves combustion chamber 20 through linking zone 12 where it completes combustion due to the additional combustion agent injectors 32 as described above.
  • FIG. 7 shows another embodiment of the invention and which has the same reference numerals as the previously described examples plus 100.
  • a thermal generator 110 has a combustion chamber 120 , a linking zone 112 , a heat recovery zone 116 , and a zone 118 for evacuating and/or processing the fumes coming from combustion.
  • the generator has a combustion chamber 120 with a lengthwise axis XX′ which can be cylindrical or substantially parallelepipedic in shape.
  • the combustion chamber is parallelepipedic with a rectangular section whose peripheral wall 122 is formed of a succession of walls around axis XX′. This succession of walls comprises vertical walls 140 and 142 and upper horizontal wall 144 and lower horizontal wall 146 .
  • the generator also has a front face 124 as well as a rear face 126 .
  • the vertical wall 142 has at least one fuel injector 128 with an axis ZZ′ essentially perpendicular to the axis XX′ of combustion chamber 120 and the horizontal wall 144 has at least one combustion agent injector 130 such that the axis of the combustion agent injector is essentially perpendicular to the axis ZZ′ of the fuel injector.
  • the linking zone 112 is located at the intersection of the upper horizontal wall 144 and the vertical wall 142 , particularly at the right part of the generator as illustrated in this figure.
  • the combustion chamber can also be subdivided into permeable or impermeable compartments by means of walls, which can be membrane walls for example, substantially parallel to the two vertical faces 124 , 126 which close off the two ends of the combustion chamber.
  • the purpose of this provision is to limit the volume of each unit combustion chamber to less than 50 m 3 as indicated above.
  • the fuel injector 128 with axis ZZ′ sprays the fuel into combustion chamber 120 in very wide jets (arrow A) so as to ensure good distribution of the fuel throughout the combustion chamber 120 and good mingling of the fuel and combustion agent.
  • an essentially horizontal row of fuel injectors spaced regularly apart is provided along axis XX′ of the combustion chamber.
  • the injectors can also have other arrangements, staggered for example, and/or sloping relative to wall 142 .
  • the combustion agent injector 130 is located on the upper horizontal wall 144 .
  • a row of combustion agent injectors is provided, regularly spaced along axis XX′, whose positions match or do not match those of the row of fuel injectors.
  • the fuel is injected into combustion chamber 120 from injector 128 in all directions of space, particularly in the direction of the combustion agent injectors 30 1 , as indicated by arrows A, to ensure mingling of the fuel and combustion agent near walls 140 , 144 , and 146 so that they can mix and then occupy the entire section of the combustion chamber.
  • the entire combustion chamber is at a homogenous temperature.
  • the walls of combustion chamber 120 are advantageous comprised of membrane walls formed of tubes connected together by welded fins in order to seal said walls off from the outside.
  • Some parts of these walls can be covered with insulating materials to limit heat exchange and/or contact of the tubes with locally corrosive atmospheres.
  • the walls are also covered externally with insulating materials to limit heat losses.
  • the combustion zone takes up the entire combustion chamber due to the very high turbulence generated by injecting the combustion agent.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
US11/571,699 2004-07-07 2005-07-07 Homogeous Combustion Method and Thermal Generator Using Such a Method Abandoned US20080131823A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0407514 2004-07-07
FR0407514A FR2872887B1 (fr) 2004-07-07 2004-07-07 Procede de combustion homogene et generateur thermique utilisant un tel procede
PCT/FR2005/001762 WO2006013290A1 (fr) 2004-07-07 2005-07-07 Procede de combustion homogene et générateur thermique utilisant un tel procédé.

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US (1) US20080131823A1 (fr)
EP (1) EP1766289A1 (fr)
FR (1) FR2872887B1 (fr)
WO (1) WO2006013290A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20120037A1 (it) * 2012-02-02 2013-08-03 Uni Degli Studi Di Roma To R Vergata Bruciatore
US20140260305A1 (en) * 2013-03-13 2014-09-18 Rolls-Royce Canada, Ltd. Lean azimuthal flame combustor
KR101446915B1 (ko) * 2013-04-08 2014-10-06 국민대학교산학협력단 역방향 공기주입 방식을 이용한 무화염 연소 공업로
WO2014168383A1 (fr) * 2013-04-08 2014-10-16 국민대학교산학협력단 Four industriel à combustion sans flamme utilisant une technique d'injection d'air inverse, système de remise en circulation d'air inverse et système de pile à combustible appliquant un reformeur de combustible exempt de catalyseur utilisant une technique d'injection d'air inverse à grande vitesse
KR20150106247A (ko) * 2014-03-11 2015-09-21 국민대학교산학협력단 고속 역방향 공기노즐을 이용한 무촉매 무화염 연료 개질기 및 이를 이용한 연료전지 시스템
US10543387B2 (en) * 2017-03-28 2020-01-28 The Boeing Company Combustion arrester test systems and methods

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2304316A2 (fr) * 2008-07-11 2011-04-06 Rheinkalk GmbH Unité brûleur et dispositif brûleur pour combustible solide pulvérulent
FR3142475A1 (fr) 2022-11-25 2024-05-31 IFP Energies Nouvelles Production de carburants de synthèse à partir de dioxyde de carbone avec oxycombustion partielle ou totale de sous-produits
FR3142477A1 (fr) 2022-11-25 2024-05-31 IFP Energies Nouvelles Production de carburants de synthèse à partir de CO2 avec oxycombustion partielle de sous-produits et séparation de CO2

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2904417A (en) * 1959-09-15 Process for the production of synthesis
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US4021188A (en) * 1973-03-12 1977-05-03 Tokyo Gas Company Limited Burner configurations for staged combustion
US4154567A (en) * 1977-01-07 1979-05-15 Continental Carbon Company Method and apparatus for the combustion of waste gases
US4473185A (en) * 1979-10-25 1984-09-25 Peterson Folke K Method and device for producing microdroplets of fluid
US5038562A (en) * 1988-08-19 1991-08-13 Webasto Ag Fahrgeutechnik Burner for regeneration of a particle filter device
US5052919A (en) * 1985-12-20 1991-10-01 Siemens Aktiengesellschaft Multi-stage combustion chamber for combustion of nitrogen-containing gas with reduced nox emissions, and method for its operation
US5076779A (en) * 1991-04-12 1991-12-31 Union Carbide Industrial Gases Technology Corporation Segregated zoning combustion
US5425630A (en) * 1993-11-04 1995-06-20 Dutescu; Cornel Kinetic dissociator
US5529484A (en) * 1993-11-08 1996-06-25 Moard; David M. Apparatus and method for decreasing nitrogen oxide emissions from internal combustion power sources
US5546701A (en) * 1994-09-20 1996-08-20 Hydrogen Burner Technology, Inc. Underoxidized burner utilizing improved injectors
US5645410A (en) * 1994-11-19 1997-07-08 Asea Brown Boveri Ag Combustion chamber with multi-stage combustion
US6203314B1 (en) * 1994-07-08 2001-03-20 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Combustion assembly for a furnace and method of use

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1238148B (de) * 1953-07-22 1967-04-06 Siemens Ag Brennkammer fuer mit Kohlenstaub betriebene Feuerungen
US5123361A (en) * 1991-11-25 1992-06-23 The United States Of America As Represented By The Secretary Of The Navy Annular vortex combustor
US5297729A (en) * 1992-08-28 1994-03-29 Combustion Concepts, Inc. Furnace apparatus
US5975886A (en) * 1996-11-25 1999-11-02 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Combustion process and apparatus therefore containing separate injection of fuel and oxidant streams
AT408267B (de) * 1999-05-25 2001-10-25 Vaillant Gmbh Luftstufenbrenner

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2904417A (en) * 1959-09-15 Process for the production of synthesis
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US4021188A (en) * 1973-03-12 1977-05-03 Tokyo Gas Company Limited Burner configurations for staged combustion
US4154567A (en) * 1977-01-07 1979-05-15 Continental Carbon Company Method and apparatus for the combustion of waste gases
US4473185A (en) * 1979-10-25 1984-09-25 Peterson Folke K Method and device for producing microdroplets of fluid
US5052919A (en) * 1985-12-20 1991-10-01 Siemens Aktiengesellschaft Multi-stage combustion chamber for combustion of nitrogen-containing gas with reduced nox emissions, and method for its operation
US5038562A (en) * 1988-08-19 1991-08-13 Webasto Ag Fahrgeutechnik Burner for regeneration of a particle filter device
US5076779A (en) * 1991-04-12 1991-12-31 Union Carbide Industrial Gases Technology Corporation Segregated zoning combustion
US5425630A (en) * 1993-11-04 1995-06-20 Dutescu; Cornel Kinetic dissociator
US5529484A (en) * 1993-11-08 1996-06-25 Moard; David M. Apparatus and method for decreasing nitrogen oxide emissions from internal combustion power sources
US6350118B1 (en) * 1994-06-08 2002-02-26 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Combustion assembly for a furnace and method of use
US6203314B1 (en) * 1994-07-08 2001-03-20 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Combustion assembly for a furnace and method of use
US5546701A (en) * 1994-09-20 1996-08-20 Hydrogen Burner Technology, Inc. Underoxidized burner utilizing improved injectors
US5645410A (en) * 1994-11-19 1997-07-08 Asea Brown Boveri Ag Combustion chamber with multi-stage combustion

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20120037A1 (it) * 2012-02-02 2013-08-03 Uni Degli Studi Di Roma To R Vergata Bruciatore
US20140260305A1 (en) * 2013-03-13 2014-09-18 Rolls-Royce Canada, Ltd. Lean azimuthal flame combustor
CN105164471A (zh) * 2013-03-13 2015-12-16 工业涡轮（英国）有限公司 贫方位角火焰燃烧器
JP2016511388A (ja) * 2013-03-13 2016-04-14 インダストリアル タービン カンパニー （ユーケイ） リミテッドＩｎｄｕｓｔｒｉａｌ Ｔｕｒｂｉｎｅ Ｃｏｍｐａｎｙ （ＵＫ） Ｌｉｍｉｔｅｄ リーン方位角炎燃焼器
US9618208B2 (en) * 2013-03-13 2017-04-11 Industrial Turbine Company (Uk) Limited Lean azimuthal flame combustor
KR101446915B1 (ko) * 2013-04-08 2014-10-06 국민대학교산학협력단 역방향 공기주입 방식을 이용한 무화염 연소 공업로
WO2014168383A1 (fr) * 2013-04-08 2014-10-16 국민대학교산학협력단 Four industriel à combustion sans flamme utilisant une technique d'injection d'air inverse, système de remise en circulation d'air inverse et système de pile à combustible appliquant un reformeur de combustible exempt de catalyseur utilisant une technique d'injection d'air inverse à grande vitesse
KR20150106247A (ko) * 2014-03-11 2015-09-21 국민대학교산학협력단 고속 역방향 공기노즐을 이용한 무촉매 무화염 연료 개질기 및 이를 이용한 연료전지 시스템
KR101634793B1 (ko) * 2014-03-11 2016-06-29 국민대학교산학협력단 고속 역방향 공기노즐을 이용한 무촉매 무화염 연료 개질기 및 이를 이용한 연료전지 시스템
US10543387B2 (en) * 2017-03-28 2020-01-28 The Boeing Company Combustion arrester test systems and methods

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EP1766289A1 (fr) 2007-03-28
FR2872887A1 (fr) 2006-01-13
WO2006013290A1 (fr) 2006-02-09

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