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US20080227040A1 - Method and Installation for Unsupported Lean Fuel Gas Combustion, Using a Burner and Related Burner - Google Patents

Method and Installation for Unsupported Lean Fuel Gas Combustion, Using a Burner and Related Burner Download PDF

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Publication number
US20080227040A1
US20080227040A1 US11/996,587 US99658706A US2008227040A1 US 20080227040 A1 US20080227040 A1 US 20080227040A1 US 99658706 A US99658706 A US 99658706A US 2008227040 A1 US2008227040 A1 US 2008227040A1
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Prior art keywords
air
flux
mixture
burner
per
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Abandoned
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US11/996,587
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English (en)
Inventor
Jean-Claude Dieuloufet
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Optimise a Responsabilite Ltee Ste
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Optimise a Responsabilite Ltee Ste
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Assigned to OPTIMISE, SOCIETE A RESPONSABILITE LIMITEE reassignment OPTIMISE, SOCIETE A RESPONSABILITE LIMITEE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DIEULOUFET, JEAN-CLAUDE
Publication of US20080227040A1 publication Critical patent/US20080227040A1/en
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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 
    • 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
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • 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
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23G—CREMATION FURNACES; CONSUMING WASTE PRODUCTS BY COMBUSTION
    • F23G7/00—Incinerators or other apparatus for consuming industrial waste, e.g. chemicals
    • F23G7/06—Incinerators or other apparatus for consuming industrial waste, e.g. chemicals of waste gases or noxious gases, e.g. exhaust gases
    • 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 
    • F23C2201/00—Staged combustion
    • F23C2201/20—Burner staging
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/06043—Burner staging, i.e. radially stratified flame core burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14002—Special features of gas burners of premix or non premix types, specially adapted for the combustion of low heating value [LHV] gas

Definitions

  • the invention concerns a method for achieving combustion of an unsupported lean fuel gas, using a burner including a gas port nose on a central axis, creating, inside the burner, a mixture of fuel gas and combustion air, rotating around the central axis and in front of the gas port nose.
  • the invention is applied particularly in the various following installations:
  • lean gas any gas of low calorific value, i.e. less than 3000 Kcal/m 3 and in particular any very lean gas with a net calorific value (NCV) below 1000 Kcal and which concerns more specifically the subject of this invention.
  • NCV net calorific value
  • the burner in accordance with the invention may nevertheless be used with richer gases or with support gases.
  • the burners of lean or residual gases include generally various infeed pipes of combustible fluids to the burner nozzle, the pipes being configured, especially in a coaxial shape, so as to create one or more rings of combustibles centered on the axis of the burner.
  • combustible fluids are generally distributed in a flux of combustion air or on the periphery of the latter.
  • combustion air is generally fed to the nose of the burner (hereafter called combustion burner) in one flux or even in two.
  • These burners usually include rich gas distribution tubes in a peripheral ring and accessory tubes (ignition burner, flame presence control tube, . . . ) which upset the rotation of the air flux.
  • Lean combustibles are generally very difficult to burn because they consist primarily of neutral gases and present themselves distributed in large volumes and under low pressure.
  • the instability of the flames produced causes major variations of pressure in the combustion chamber, thereby generating vibrations of the structure of the boilers or installations concerned.
  • the burners often require to be operated with a substantial amount of excess air to make sure that all combustible fractions are exposed to oxygen for a complete burn and in order to ensure the quality of the combustion products, which causes profits to shrink considerably, increases the specific consumption of rich gas and hence the operating costs and inevitably raises the level of polluting emissions.
  • the invention aims to remedy the above drawbacks.
  • a preferred basic principle of the method is to partition as much as possible the quantity of air needed for combustion and to incorporate it as soon and as intimately as possible into the combustible gaseous flux (or the inverse), by improving the mixture through high-speed jet impacts by creating incidents of turbulence and by putting the mixture into maximum rotation in order to reduce the axial velocity of the mixture and to ensure the consistency and continuity of the combustion.
  • the lean gas is put into rotation by blades and the specific flow of the fraction of combustion air brought in at the periphery at the exit of the burner.
  • the invention consists of fragmenting the combustion air and of progressively incorporating chosen quantities of it into the lean gas flux.
  • the method consists therefore of creating a pre-mix of air and fuel (outside the flammability limit) preferably inside the body of the burner and to bring to the nose of the burner only the air complement on both sides of this mixture through the expedient of jets at very high speed (above 80 m/s) [above 262.5 ft/sec] by making the gas “in a sandwich”.
  • the combustion air directed to the nose of the burner has specific flows at high speed:
  • the subject of the invention is a method to obtain the combustion of a lean fuel gas using at least one burner including a gas port nose or head on a central axis, a process in which a mixture of fuel gas and combustion air is created in rotation around a central axis.
  • the method distinguishes itself by consisting of the following stages in which the following are ejected in front of the combustion head:
  • the invention is also concerned with a burner for lean fuel gas of the type that includes a gas port nose on a central axis and means to feed a mixture of fuel gas and combustion air in rotation around the central axis, the burner being especially noteworthy because it includes neither a mixing chamber nor a combustion chamber.
  • the burner distinguishes itself primarily by being configured so as to eject in front of the gas port nose:
  • the burner is configured so as to divide a flux of air into at least one flux of pre-mix air and a flux of complementary air, comprising at least one flux of central complementary air and/or one flux of peripheral complementary air.
  • the invention is also concerned with an installation for the combustion of fuel gas applying the method or comprising at least one burner in conformance with the invention.
  • the installation uses or includes at least two burners that are configured so as to gear in a common direction the overall rotary motion resulting from their mixture flux in front of the gas port nose.
  • FIG. 1 shows a schematic view of an installation for lean gas combustion, equipped with a burner in accordance with one way of carrying out the invention.
  • FIG. 2 shows a partial sectional view along axis AA of FIG. 1 .
  • FIG. 3 shows a back view of the burner as per the right side view of FIG. 1 .
  • FIG. 4 shows a partial sectional view of a beam as per section CC of FIG. 2 .
  • FIG. 5 shows a partial bottom view as per D-D of FIG. 4 .
  • FIG. 6 shows a detailed schematic view of the chamber 7 of the burner in FIG. 1 .
  • FIGS. 7 , 8 , and 9 show different sectional and partial section views, respectively, of FIG. 6 : a sectional view along E-E, a right side view along F, and a left side view along G.
  • FIGS. 10 , 11 , and 11 A show, respectively, a detailed schematic view of the central tube 13 of the burner of FIG. 1 , a left side view along H and a right side view.
  • FIG. 12 shows a detailed sectional view of the central pole 50 as per FIG. 1 .
  • FIG. 13 shows a partial sectional and schematic view of a construction variant of a flaring cone of the central pole.
  • FIG. 14 shows a detailed sectional view of FIG. 9 .
  • FIGS. 15 and 16 show, respectively, the sectional views along L-L and K-K of FIG. 14 , respectively.
  • FIG. 1 shows an installation 1 for the combustion of lean fuel gas, using a burner 2 mounted between 4 main parts ZA, Zb, ZC, ZD that are separated by three partitions 3 , 4 , 5 .
  • the parts represent, respectively, a zone ZA firebox where combustion takes place, a zone ZB containing or in communication with the lean fuel gas, a zone ZC containing or in communication with combustion air, a zone ZD that is exterior to the installation and accessible to personnel.
  • the products of combustion must contain less than 50 ppm of CO with less than 1% of oxygen in these fumes. Ignitibility of this gas occurs when there is 35% to 73% of gas in the mixture.
  • the burner includes a gas port nose 6 ending in Zone A of the chamber.
  • the nose is centered on a central axis X which happens to be, under the circumstances, the main axis of the burner to the extent that the latter has a general circular shape around this axis.
  • the burner also includes means to feed this nose which are capable of ejecting a flux of air and fuel gas in rotation around a central axis centered on the gas port nose.
  • This nose which constitutes the front end of the burner is intended to receive, in front of or on it, to the left of the figure, a flux of fuel gas and combustion air which is put into rotation around the central axis, with means to feed this nose provided for this purpose and which are described subsequently.
  • the burner also comprises a central chamber 7 connected to the nose and upstream of the burner (relative to the direction of the flux discharge) and mounted in zone ZB between partitions 3 and 4 , with at least one opening 8 ending in this zone ZB.
  • zone ZC there is a back end 7 B of the burner linked to chamber 7 , upstream of the latter, and presenting at least one access for at least one inflow of combustion air of zone ZC.
  • zone ZD various pipes discharge which extend between the chamber and the exterior, while crossing the burner and among which pipes one finds, if applicable, a rich gas supply pipe, a flame control pipe, an ignition pipe or other pipes or equipment known to the experts (not shown).
  • the method may include a first stage in which a flux of air intended for combustion is divided into at least one flux of ore-mix air and a flux of complementary air.
  • the complementary air is constituted of at least one central flux of air and/or one flux of peripheral air.
  • the burner is configured to divide the air coming from the space ZC into several flux (flows). It comprises a number of intakes or access on its back end: a central access 9 to receive an intake of a flux of central air, a peripheral access 10 to receive an intake of peripheral air, and at least one main access 10 A to receive an intake of pre-mix air. More access points can be added as indicated later on.
  • this dividing step could be done differently, for example by external pipes outside the burner, and each flux of air could be supplied by independent and external pipes.
  • a pre-mix flux is ejected containing a mixture of pre-mix air and of fuel gas, in rotation around the central axis.
  • the pre-mix flux is nonflammable to the extent that it is mixed at a rate far from the ignitibility ranges, for example above an ignitibility threshold.
  • ignitibility a rate far from the ignitibility ranges, for example above an ignitibility threshold.
  • the burner in the example described, is configured to achieve the preceding pre-mix inside itself, in this particular case in a so-called pre-mix space 16 of the chamber 7 .
  • This rotation in the example described, is also preferably achieved in the chamber upstream of the gas port nose.
  • the pre-mix air access points 10 A mentioned above lead to the chamber for the same reason as the fuel gas access ports 8 for the purpose of obtaining a pre-mixture using the mixing devices 11 described later on.
  • the pre-mixing could be done beforehand outside the burner, for example, in an enclosure provided for this purpose in which a rate above the ignitibility rate is maintained.
  • the mixing occurs at a rate between 5 and 20% above the ignitibility threshold with an insufficient air percentage (proportions going between 78 and 95% gas in the mixture),
  • the complementary flux is ejected a the center of the pre-mix flux by way of the flux of central complementary air and/or around the pre-mix flux by way of the flux of peripheral complementary air, in a manner so as it reaches the threshold of ignitibility at the gas port nose.
  • ejection of the complementary flux occurs simultaneously at the center and in the periphery in order to achieve a better final mix.
  • the burner is configured so as to deliver the pre-mixture flux in the form of ring 12 located between a central pipe 13 and the periphery 14 of the front end of the chamber.
  • the pre-mixture flux is obtained by incorporating pre-mixture gas in fuel gas.
  • the burner includes the incorporating devices 11 mentioned earlier which inject air into the fuel gas.
  • Incorporation is done directly in an enclosure of the chamber having a pre-mixture space 16 ( FIG. 2 ) located between a central pipe 13 and an internal partition 31 of the chamber.
  • incorporation is achieved by injection of pre-mix air at an entry point of the fuel gas into the burner so as to:
  • the burner includes injection devices including nozzles 17 or calibrated directional high-output orifices located in the incorporation devices 11 that are profiled and directed towards the pre-mixture space 16 at the ports 8 .
  • the gas located near and around the ports 8 is driven by the partial vacuum generated by the air jets at the exits of the nozzles which are directed by the orientation of the jets and [the gas] is mixed by the turbulence created by the jets.
  • a rotational movement of the mixture is also initiated in the pre-mixing space by the orientation of the air jets.
  • injection devices are preferably for constant duty.
  • the incorporating devices may also preferably comprise second means of pre-mix air injection. These means of injection are placed so as to obtain an incorporation of air parallel to the central axis and by directing the pre-mix flux towards the gas port nose.
  • These second means of injection may be formed, as in the example described, by tubes 21 around orifices 22 in the partition 23 of the back end of the burner ( FIGS. 3 , 10 , 11 ).
  • These tubes are preferably of different lengths and are five in number in the example. They extend to the interior of the pre-mixing space from air intakes or orifices 22 located on the partition 23 or back face of the burner.
  • the orifices 22 are preferably capped by flaps (not shown) that can be operated by scaled springs or electric controls.
  • the flaps may be located on the orifices with or without tubes.
  • the tubes allow, on the one hand, to avoid the respective flows upsetting each other and, on the other hand, to supply air at different points with a guarantee of its distribution.
  • the orifices have a determined size so as to avoid finding themselves too massively inside the limits of ignitibility and that there may locally be conditions that are favorable to a combustion that would deteriorate the burner.
  • the pre-mixture gas would replace the pre-mixture air and the flows, the pre-mixture could be unchanged and the central and peripheral flows could involve for instance fuel gas instead of combustion air.
  • the flux of central complementary air is ejected in rotation in front of the gas port nose and in divergent flow to penetrate the pre-mix flux and the flux of peripheral complementary air is ejected in a convergent flow and in strong spiral rotation.
  • the burner is configured in the example with a cone-shaped deflector 18 at the exit of the central pipe 13 and blades 19 in the pipe which put the central flux of air into rotation.
  • Other equivalent means may also be suitable, as for example calibrated directional orifices or oriented ports in a separating partition.
  • the central air is divergent with an angle at the top of 60 to 180° or of 30 to 90° in relation to the axis of the burner.
  • This ejection produced in this way allows achieving good penetration of the air in the pre-mixture so as to best complete the rate of missing air.
  • the flux of central air of the example has previously penetrated the intake 9 in the internal conduit of pipe 13 , in the ring space around the central pole 51 .
  • this central air can have another function that is explained later on, which is to feed at its ejection base a rich gas which would be distributed in ring shape around the central air, during its use, in particular during startups or shortages of lean gas.
  • the burner is configured with injection nozzles 20 a, 20 b located on a ring 14 on the front end or face of chamber 26 a.
  • the nozzles are oriented both tangentially to a circle centered on the central axis and oriented towards the front. Spiral rotation is obtained by this dual slant of the nozzles.
  • the peripheral air wraps around the flux of lean gas and enhances its rotation. It is distributed at high speed and optimizes the mixing.
  • Nozzles 20 a, 20 b are fed by the space of peripheral pre-ejection 30 located in a double partition of the chamber at the front of the chamber which is itself fed by the intake devices 10 A that have been provided in the vicinity of the back end 26 b of the chamber.
  • the chamber of the burner is the chamber of the burner
  • the chamber 7 has a general rotational shape and consists of:
  • the nozzles are in fact exit perforations made in the ring one of the functions of which is to close off the front end of the double wall of the chamber.
  • the other back end of the double wall is closed off by a wall 23 B.
  • the nozzles are arranged on the ring, being offset relative to the radial axis R of the chamber and slanted towards the front relative to a plane perpendicular to the chamber.
  • the nozzles are offset and slanted in different ways according to an alternation.
  • the angles proposed are specific to this power of the burner, but would be inevitably modified for another size burner. These angles have been determined so that the jets of consecutive orifices do not interfere with each other and do not collide with the end of tube 13 nor impede the flow of fluids coming out of the gas ring contained between 13 and 56 , nor the divergent complementary central air. This divergent cone must practically “mesh” with the convergent complementary peripheral jet with the most acute angle (here 15°).
  • the angle of the next orifice is more open in order to continue further along in the rotation the work of the preceding orifice.
  • a first series of nozzles ( 20 a ) maybe slanted from 5° to 45° to the front, (15° preferred in the example of execution) and from 30 to 65° relative to the radial axis (R), (44° preferred in the example) and a second series of nozzles ( 20 b ) slanted from 25 to 65° to the front (45° preferred in the example), and from 30 to 70° relative to the radial axis (53° preferred in the example).
  • the chamber may also include orifices 55 arranged on the internal wall 25 at the height of the pre-ejection chamber 30 . These orifices permit feeding the blade device 37 from the chamber 30 in order to improve the air/lean gas mixture between the blades.
  • the central tube is a central tube
  • a central tube 13 meant to be installed centered on the central axis, is dimensioned to extend longitudinally between the two ends of the chamber and to put in communication with each other.
  • This tube includes:
  • the blades are profiled so as to create a rotation of the pre-mix flux during its flow towards the exit of the vessel.
  • a space between the vessel and the tube forms a ring-shaped conduit 38 ( FIG. 1 ) intended to convey the flux of pre-mix air.
  • a wall 23 forms a radial collar of the central tube, said wall separating the pre-mix space with the back end of the central tube which is itself in communication with the air chamber.
  • the central pole The central pole:
  • the central pole 51 is intended to be located in the central tube 13 and centered on the central axis.
  • the burner also includes a second set of blades 19 located inside and in proximity to the front end of the central tube.
  • the blades are attached to the central pole 51 which crosses the central tube. They are meant to extend from the surface of the pole 50 to the inside wall 52 of the central tube.
  • the burner may also include a “burn cone” 18 as a deflector located downstream of the central tube and spaced from it so as to provide a divergent outflow of the central flux of air.
  • the burn cone is placed at the front end of the axial pole 51 .
  • the gas is ejected at the end of the pole, at a divergent angle that is defined by a series of calibrated orifices 54 placed in a ring form around the cone shaped deflector 18 which allows to eject this gas over a maximum circumference so that any rich gas jets that may be present and originate as close as possible to the central combustion air and have maximum momentum when colliding with the flow of lean gas.
  • the cone shaped deflector maybe a deflector 18 b with a peripheral serration 52 and have central orifices 53 leading to the inside of the conduit of the central pole.
  • the burner is designed to receive, under normal operating conditions, an ejection of complementary flux at a very high speed above 100 m/second whereas the pre-mix flux is ejected at a speed between 40 and 80 m/sec.
  • the burner may include a rich gas supply.
  • the rich gas is brought in under pressure to the periphery of the central tube directly to the pre-mix space.
  • the rich gas is distributed around the central tube so as to mix thoroughly with the pre-mixture.
  • the vessel 36 maybe connected to a rich gas supply tube (the orifices 10 A 2 being blanked off) or another vessel 36 B (not shown) wrapped around vessel 36 and connected to the supply tube.
  • Calibrated orifices arranged with a divergent angle may be made in a ring connecting the two tubes 13 and 56 B at the front end.
  • the double wall 56 tube portion may extend to the end of the central tube 13 , forming a central double wall 56 B so as to eject the rich gas directly to the gas port nose around the central air.
  • the rich gas is, still under pressure, brought into the central pole. It is ejected at a defined divergent angle by a series of calibrated orifices 53 arranged in a ring around a particular device (deflector with peripheral serration 52 ) which allows to eject this gas on a maximum circumference so that the rich gas jets originate as close as possible to the combustion air and have maximum momentum when colliding with the flow of lean gas.
  • the above configurations make it possible to obtain a consistent flame of a continuous structure and maximum surface (optimization of thermal transfer in the burn chamber).
  • the rich gas is thus supplied with combustion air at its base, whatever the composition/proportion of the fuels: single and pure gas or gas in mixtures.
  • the burner is designed in mechanic/welded modules which allow for a maximum of flexibility and ease of design, adaptation, construction, installation and maintenance, in the knowledge that:
  • An ignition flame is brought to the nose of the burner through the intermediary of a guide tube 60 ( FIG. 1 ).
  • the permanent air system is then activated by a pump (not shown) which blows combustion air into the back end of the burner by putting the air supply vessel ZC under pressure.
  • a fraction of the combustion air penetrates into the double wall 27 of the vessel ( FIG. 6 ) across the inlet orifices 10 that are for example rectangular and made in the ring-shaped wall 23 B closing the double wall at the rear. Whereas another fraction penetrates directly into the double vessel towards the nozzles 20 a, 20 b.
  • the girders are put under pressure and combustion air escapes from the nozzles in a tangential direction ( FIG. 7 ) to a circle centered on the central axis and towards the blades of the first rotation device.
  • the combustion gas which may be under light pressure (generally less than 200 CE) enters crosswise into the vessel under an effect of entrainment of the air jets at the level of the ports 8 between the girders 11 .
  • the turbulence results in a pre-mixing or stirring inside the pre-mix space 16 of the vessel at the entry of the blade device ( FIG. 7 ), especially by deflection against the deflection wall 31 .
  • the girders Since the girders also open into the pre-ejection chamber 30 of peripheral air, they contribute to the air supply there in addition to the air conveyed by the inside of the deflection or guide double wall 24 , 25 .
  • Combustion air also penetrates by entry 9 of the central tube 13 ( FIGS. 10 , 11 ) and opens directly at the level of the nose 6 , after having entered the space between the blades of the second blade device 19 ( FIG. 2 ) where it assumes a rotational movement.
  • This air re-exits in front of the nose in a deflecting manner by way of the cone shaped deflector 18 placed in front of it.
  • peripheral air is ejected from the chamber 30 ( FIGS. 9 , 14 - 16 ) in the form of two swirls by way off the peripheral nozzles 20 a, 20 b in front of the gas port nose.
  • the rotational direction of the different flux of air may be opposite that of the pre-mix flux, but preferably they should be in the same direction.
  • supplemental air may enter the pre-mixture chamber by tubes 21 or flaps ( FIGS. 10 , 11 ) arranged on a ring-shaped wall 23 coming from the collar of the central tube and helping to enrich the air mixture.
  • Air may also come from the back end of the vessel 36 through orifices 10 A 2 and enrich the pre-mixture.
  • air may escape from the vessel beginning from the pre-ejection chamber 30 through orifices 55 made in the inside wall of the vessel and it penetrates radially in the blade device 37 between the blades. This helps to improve the stirring of the gas mixture with air.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Environmental & Geological Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
US11/996,587 2005-07-26 2006-07-26 Method and Installation for Unsupported Lean Fuel Gas Combustion, Using a Burner and Related Burner Abandoned US20080227040A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0507964A FR2889292B1 (fr) 2005-07-26 2005-07-26 Procede et installation de combustion sans soutien de gaz combustible pauvre a l'aide d'un bruleur et bruleur associe
FR0507964 2005-07-26
PCT/FR2006/001821 WO2007012755A1 (fr) 2005-07-26 2006-07-26 Procédé et installation de combustion de gaz combustible pauvre, sans soutien, à l'aide d'un brûleur et brûleur associé

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US20080227040A1 true US20080227040A1 (en) 2008-09-18

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US11/996,587 Abandoned US20080227040A1 (en) 2005-07-26 2006-07-26 Method and Installation for Unsupported Lean Fuel Gas Combustion, Using a Burner and Related Burner

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US (1) US20080227040A1 (fr)
EP (1) EP1907754B1 (fr)
CN (1) CN101297160B (fr)
EA (1) EA012937B1 (fr)
ES (1) ES2443116T3 (fr)
FR (1) FR2889292B1 (fr)
PL (1) PL1907754T3 (fr)
WO (1) WO2007012755A1 (fr)

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US10414005B2 (en) 2014-04-09 2019-09-17 General Electric Company Method and apparatus for servicing combustion liners
CN110848667A (zh) * 2019-09-25 2020-02-28 西安交通大学 一种低热值含氮燃气燃烧系统及方法
CN115468164A (zh) * 2022-09-01 2022-12-13 芜湖精塑实业有限公司 一种低氮燃烧器
CN116554928A (zh) * 2023-05-11 2023-08-08 广州美东能源有限公司 一种用于替代天然气的lpg混空制备工艺

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EP2479491A1 (fr) 2011-01-20 2012-07-25 Fortum OYJ Procédé et brûleur pour brûler du gaz pauvre dans une chaudière de centrale électrique
WO2012098174A1 (fr) 2011-01-20 2012-07-26 Fortum Oyj Procédé et brûleur pour la combustion de gaz pauvre dans une chaudière de centrale
US10414005B2 (en) 2014-04-09 2019-09-17 General Electric Company Method and apparatus for servicing combustion liners
CN110848667A (zh) * 2019-09-25 2020-02-28 西安交通大学 一种低热值含氮燃气燃烧系统及方法
CN115468164A (zh) * 2022-09-01 2022-12-13 芜湖精塑实业有限公司 一种低氮燃烧器
CN116554928A (zh) * 2023-05-11 2023-08-08 广州美东能源有限公司 一种用于替代天然气的lpg混空制备工艺

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CN101297160B (zh) 2011-07-20
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PL1907754T3 (pl) 2014-05-30
EA200800437A1 (ru) 2008-08-29
FR2889292A1 (fr) 2007-02-02
FR2889292B1 (fr) 2015-01-30
CN101297160A (zh) 2008-10-29
ES2443116T3 (es) 2014-02-17
EA012937B1 (ru) 2010-02-26
EP1907754A1 (fr) 2008-04-09

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