EP0202443B1 - Verfahren und Vorrichtung zum Verbrennen flüssiger und/oder fester Brennstoffe in pulverisierter Form - Google Patents

Verfahren und Vorrichtung zum Verbrennen flüssiger und/oder fester Brennstoffe in pulverisierter Form Download PDF

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Publication number
EP0202443B1
EP0202443B1 EP86104628A EP86104628A EP0202443B1 EP 0202443 B1 EP0202443 B1 EP 0202443B1 EP 86104628 A EP86104628 A EP 86104628A EP 86104628 A EP86104628 A EP 86104628A EP 0202443 B1 EP0202443 B1 EP 0202443B1
Authority
EP
European Patent Office
Prior art keywords
fuel
inlet
air
combustion chamber
inlet ports
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.)
Expired
Application number
EP86104628A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0202443A3 (en
EP0202443A2 (de
Inventor
Kurt Dipl.-Ing. Skoog
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.)
STUBINEN UTVECKLING AB
Original Assignee
STUBINEN UTVECKLING AB
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
Application filed by STUBINEN UTVECKLING AB filed Critical STUBINEN UTVECKLING AB
Priority to AT86104628T priority Critical patent/ATE48906T1/de
Publication of EP0202443A2 publication Critical patent/EP0202443A2/de
Publication of EP0202443A3 publication Critical patent/EP0202443A3/de
Application granted granted Critical
Publication of EP0202443B1 publication Critical patent/EP0202443B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/007—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel liquid or 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D1/00—Burners for combustion of pulverulent fuel
    • F23D1/005—Burners for combustion of pulverulent fuel burning a mixture of pulverulent fuel delivered as a slurry, i.e. comprising a carrying liquid
    • 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
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the invention relates to a method and a device for burning liquid and / or solid fuels according to the preamble of patent claim 1 and patent claim 14.
  • a burner is proposed in DD-PS 145316, which is a combination of a so-called rotary burner with a toroidal burner.
  • this burner can only achieve relatively low efficiencies, especially in the critical starting phase. The reason is presumably that the atomization of the fuels is inadequate, so that inflammation problems occur especially in the starting phase. The enrichment or mixing of the fuels with air is also deficient, which also affects the efficiency.
  • the present invention has for its object to provide a method and an apparatus for burning liquid and / or solid fuels in pulverized form, in which or with the due to good mixing of different types of fuels at a minimal distance in the combustion chamber a practically complete combustion is possible, the combustion being able to be maintained with a high degree of efficiency even when solid fuels are supplied in dry form, and with which particularly easy ignition is achieved.
  • the fuels are introduced into the combustion chamber in finely divided form. Solid and liquid fuels are mixed with one another immediately after they are introduced into the combustion chamber, which means that combustion can be started easily, especially in the start-up phase.
  • the fuels are fed through one (small burner) or several nozzles finely distributed in the form of spray cones into the combustion chamber, whereby the alternating arrangement of nozzles or inlet openings for solid and liquid fuels ensures good mixing and therefore easy ignition.
  • the introduced fuels are "broken up" into the smallest fuel particles or droplets. In this way, a maximum fuel surface is obtained, whereby the practically complete combustion is achieved at an extremely short distance.
  • the combustion chamber can be built accordingly short.
  • the external air flow has a temperature of approximately 100 ° C. If the temperature of the external air flow is lower than 100 ° C, it is advisable to reintroduce oil in order to maintain a high combustion efficiency.
  • the device (burner) designed according to the invention is therefore suitable both for the combustion of solid fuels and of liquid fuels, specifically separately from one another or in a predetermined mixing ratio.
  • the measures according to the invention reliably prevent deposits on the side wall opposite the fuel inlet and delimiting the air flow closest to the fuel inlet when the nozzle body or fuel inlet is arranged in the front wall of the combustion chamber.
  • the central recirculation of part of the hot combustion gases also has the great advantage that part of the dissociated water and thus released oxygen flow back centrally to the fuel inlet, which also causes the combustion from the inside of the hollow fuel Spray cone is initiated here.
  • only pure oil is preferably injected in order to then increasingly introduce pulverized solid fuels.
  • the oil supply can then be switched off completely at a sufficiently high temperature of the external air flow and also of the compressed air blown in centrally and optionally the compressed air mixed with the solid fuel. The procedure is reversed when switching off the combustion. The powdered fuel is increasingly removed until finally only oil remains as fuel.
  • the solution according to the invention is also extremely suitable for the combustion of oil, in particular heavy oil.
  • oil in particular heavy oil.
  • the highest fine distribution or atomization of the oil introduced into the combustion chamber and thus an extremely large free combustion area are obtained, with the result that almost complete combustion is obtained at the shortest distance.
  • Solid fuels are primarily coal, e.g. Hard coal, bituminous coal, gas-rich coal or a mixture thereof.
  • the oil and / or coal burner shown in a schematic longitudinal section in FIG. 1 has a nozzle body 32 with fuel inlet openings 10, 12 'opening into the combustion chamber 16, which is arranged sunk in the end wall 33 of the combustion chamber and of several gas channels 35, 37 , 39, 41 and 43 is concentrically surrounded.
  • the gas channel 35 immediately surrounding the nozzle body 32 opens into the combustion chamber 16 through an inlet opening 36 which is closest to the fuel inlet.
  • a so-called “primary primary air” flows through the channel 35, which can be enriched with combustion gases of higher temperature, the gas emerging from the opening 36 having a flow rate of 100 to 200 m / s, preferably about 130 m / s.
  • the side walls 60 and 62 delimiting the opening 36 are each conical in shape with the formation of an annular nozzle.
  • the "primary primary gas” emerges, it is deflected by swirl elements 46 in the form of guide vanes by approximately 70 ° and thus set in rotation about the longitudinal axis 14 of the nozzle body or combustion chamber.
  • the primary primary gas is blown into the gas channel 35 at a pressure of about 1000 to 1200 mm water column.
  • the gas channel 35 is surrounded concentrically by a further gas channel 37, the annular inlet opening 38 opening into the combustion chamber 16 is likewise delimited by conical side walls 64 and 66.
  • the side walls 64, 66 are directed in such a way that they impart a cone-like flow profile to the gas flow emerging from the ring opening 38, which penetrates the opposite flow profile of the fuels and the "primary primary air" emerging from the ring opening 36.
  • the exit velocity of the “secondary primary air” is approximately 120 to 180 m / s, preferably 140 m / s.
  • the annular gap width of the opening 38 can be changed by changing the relative position of the side walls 64, 66 delimiting it.
  • the exit velocity of the “secondary primary air” is of course variable in a corresponding manner.
  • the “secondary primary air” is also blown into the annular duct 37 at a pressure of about 1000 to 1200 mm water column.
  • the “secondary primary air” is deflected by the swirl elements 48 in the same direction as the “primary primary air” is deflected by the swirl elements 46 arranged in the region of the opening 36.
  • the “secondary primary air” is preferably not enriched with hot combustion gases, since it serves less as a carrier medium for the fuel introduced into the combustion chamber 16, but rather to enlarge the free surface thereof and to enrich or supply the fuel particles or droplets with oxygen.
  • the component comprising the nozzle body 32, the ring channel 35 immediately surrounding it and the ring channel 37 through which the “secondary primary air” flows can be inserted as a whole into the end wall 33 of the combustion chamber 16 or into the gas register 39, 41, 43 to be described and thus also easily replaceable with a corresponding, slightly modified component.
  • the gas channel 37 for the “secondary primary air” is in turn surrounded by a concentric gas channel 39, this by another gas channel 41 and finally by a gas channel 43.
  • the corresponding ring openings opening into the combustion chamber 16 are identified by the reference numerals 40, 42 and 44.
  • the annular channels 39, 41 and 43 are flowed through selectively, preferably by air, the blowing in taking place under a pressure of about 200 to 300 mm water column.
  • swirl elements 50, 52, 54 arranged in the region of the openings in the form of baffles and thus set in rotation about the longitudinal axis 14, specifically in in the same direction as the “primary primary air” or “secondary primary air” through the swirl elements 46 and 48.
  • the swirl elements 50 deflect the gas or air flow by approximately 70 °.
  • the swirl elements 52 and 54 deflect the gas or air flow by approximately 40 to 50 ° and 0 to 40 °. All of the swirl elements, in particular the outermost swirl elements 54, can be changed with regard to their angular position and can thus be adapted to the fuel or fuel mixture to be burned.
  • the flow velocity of the air emerging from the ring opening 40 is approximately 40 m / s at the start of combustion, and approximately 70 m / s at full load.
  • the flow velocity of the air emerging from the ring openings 42 and 44 varies between 0 m / s at the start of combustion and 70 m / s at full load.
  • an annular mouthpiece 68 arranged between the two ring openings or gaps 36 and 38 and comprising the two adjacent or facing side walls 62 and 64 of the two ring openings 36 and 38 is in the axial direction or in the direction of the longitudinal axis 14 - and slidably mounted.
  • the ring mouthpiece 68 is connected to the tube jacket 70 separating the two primary air channels 35, 37, so that the axial displacement of the ring mouthpiece 68 takes place by corresponding action on the tube jacket 70.
  • the ring mouth piece 68 in FIG. 1 is shifted to the right, so that the gap widths of the ring openings 36 and 38 and thus the amount of primary air escaping are a minimum.
  • the conditions are reversed, i.e. H. the ring mouthpiece 68 is shifted to the left in FIG. 1, so that the ring openings 36 and 38 are opened to the maximum.
  • the discharge quantity of the "primary" and "secondary" primary air is correspondingly maximum.
  • the outermost gas or air flow through the ring channel 43 serves primarily to reduce the NO x content outside the flame in the combustion chamber 16. Furthermore, this flow limits the radial expansion of the flame and prevents deposits on the side walls of the combustion chamber 16.
  • Powdered fuel e.g. Carbon powder are blown in, mixed with secondary air or instead of the secondary air. This is particularly possible and expedient at full load when energy peaks occur.
  • the core of the device according to the invention is the configuration of the nozzle body 32 with the illustrated arrangement of the inlet openings 10 and 12 'for oil and solid fuels. This configuration is now described in more detail with reference to FIGS. 2 to 4.
  • the fuel inlet is formed by several, namely 16, inlet openings 10, 12 'arranged uniformly distributed over a circular circumference 11 or 13, the inlet openings 10 for liquid fuel, in particular oil, and the inlet openings 12' for solid fuel or a fuel emulsion alternating are arranged along the circumference.
  • the entry openings 10 for liquid fuel are directed radially outward along an inwardly offset circumference 13, while the inlet openings 12 'for solid fuel along an outer circumference 11 or closer to the combustion chamber 16 with respect to the longitudinal axis 14 of the combustion chamber 16 in the flow direction to the outside are inclined.
  • the mouthpieces 24 each comprise a ring with a triangular cross section, an annular edge 28 of this cross section defining or delimiting the inlet opening 12 ′ opening into the combustion chamber 16.
  • compressed air channels 30 are provided which are directed towards the inlet opening 12 ′ and are fluidly connected to the above-mentioned compressed air connecting lines or branches 20 within the nozzle body 32.
  • the fluid connection takes place via an outer annular space which is delimited on the one hand by the nozzle body and on the other hand by an annular groove 21 in the mouthpiece 24, the compressed air connecting line or branch opening into this annular space and also several, approximately uniformly over the circumference, to this annular space of the mouthpiece 24 connect compressed air channels 30 (see FIGS. 2 and 3).
  • the fuel flow is broken up with the formation of a "spray cone".
  • This effect is additionally supported by the injection of compressed air through the compressed air channels 30.
  • the formation of a “spray cone” can be varied or adjusted well to the respectively desired conditions or to the type and quality of the fuel to be burned. Due to the construction described, the fuel introduced is already distributed to several individual nozzles and additionally extremely “broken open” at these, with the result of maximum fine distribution and the creation of a maximum free or combustion-active surface.
  • the mouthpieces 24 are interchangeably arranged in the nozzle body, e.g. screwed in. This enables adaptation to the fuels to be burned.
  • the different nozzle bodies can differ in terms of inlet openings 12 ′ of different sizes and / or different numbers of compressed air channels 30 or differently dimensioned compressed air channels 30. It is also possible to use mouthpieces 24 whose ring edge 28 delimiting the inlet opening 12 'is somewhat rounded, stepped or flattened. However, a pointed ring edge 28 is best suited.
  • the central compressed air inlet 18 can also be arranged within an insert part 19 which can be screwed onto the end face of the nozzle body 32 facing the combustion chamber 16. In this way it is possible to change the free cross-section and the shape of the inlet 18 by using a different insert body 19 (see FIG. 2 in comparison to FIG. 1, where the shape of the inlet 18 corresponds approximately to that of the inlet opening 12 'for solid fuel ).
  • the central compressed air injection through the inlet 18 prevents deposits on the end face of the nozzle body 32 facing the combustion chamber.
  • the centrally recirculating combustion gases which are around 1500 to 1700 ° C., are deflected there and are carried back into the combustion chamber 16 by the fuel introduced, in particular by the solid fuel introduced through the inlet openings 12 ′.
  • the hot combustion gases cause the same to ignite immediately after the relatively cold fuels or fuel emulsion has escaped, so that the combustion process is started relatively close behind the fuel inlet 12 ′, this ignition being additionally supported by - especially during the starting phase the radially introduced oil (through the inlet openings 10).
  • the flame jacket is determined by the equilibrium between the centrifugal forces caused by the rotation as well as the negative pressure caused by the negative pressure prevailing outside the flame jacket in the region of the end wall 33 on the one hand and the counterforce caused by the central negative pressure in front of the nozzle body inside the flame jacket on the other hand.
  • the ring opening 40 is adjusted so that the speed of the exiting air is about 40 m / s.
  • the annular mouthpiece 68 is - as explained - shifted towards the combustion chamber 16, so that the annular gaps between the side walls 60, 62 and 64, 66 are reduced, whereby the quantity of the "primary" and “secondary” primary air escapes at a somewhat increased outlet velocity is reduced. Due to the somewhat increased exit velocity, in particular of the “secondary primary air” from the ring opening 38 directed towards the introduced fuel, a high break-open effect is obtained.
  • the primary air is divided at startup so that about 60 to 70%, preferably 90% thereof, from the ring opening 36 closest to the fuel inlet and only about 30 to 40%, preferably 10%, of the same flow out of the second next ring opening 38.
  • the ratio between «primary primary air» and «secondary primary air» is approximately 3: 7.
  • FIGS. 5 to 7 differs from that according to FIGS. 1 to 4 only by a different structure of the nozzle body. All other measures have remained the same and are also provided with the corresponding reference numerals, so that the description of the nozzle body with reference to FIGS. 6 and 7 can be used below.
  • the nozzle body 32 according to FIGS. 6 and 7 comprises a central feed line 34 for solid fuels, such as pulverized coal with or without water, oil or the like, a ring line 36 ′ concentrically surrounding this feed line for liquid fuel, such as oil or the like, and this oil ring line Concentrically surrounding compressed air supply 38 'in the form of several line bores arranged uniformly distributed over a circumference.
  • the feed lines 34 and 36 'for solid and liquid fuel open into radially directed inlet openings 10 and 12, which are alternately distributed evenly over the circumference, as can be clearly seen in FIG. Overall, just as in the embodiment according to FIGS. 1 to 4, eight inlet openings 10 and 12 are provided for solid and liquid fuel.
  • the compressed air bores 38 ' which extend parallel to the longitudinal axis 14 of the nozzle body 32 or the combustion chamber 16 and which are supplied with "primary primary air” from the gas or air duct 35 immediately surrounding the nozzle body 32, open into one radially open annular gap 22, which lies in the direction of flow behind the radially directed inlet openings 10, 12.
  • the annular gap 22 is formed by a cover disk 23 attached to the end face of the nozzle body 32, with the aforementioned radially extending annular gap 22 being released (see also FIG. 5).
  • the cover plate 23 has a flat end face 56, while the end face 58 of the nozzle body facing the combustion chamber 16 is frustoconical in accordance with FIGS. 1 to 4. A corresponding design of the end face 56 is of course conceivable.
  • the “primary primary air” flowing out radially through the annular gap 22 on the one hand causes a deposit of escaping solid or liquid fuel on the end face 56 and on the other hand deposits of fuels or fuel residues on the boundary wall 62 opposite the fuel inlet of the gas closest to the nozzle body 32. or air inlet opening 36 'safely avoided.
  • a central compressed air injection can be provided in accordance with the embodiment according to FIGS. 1 to 4.
  • the nozzle body 32 it is also conceivable to arrange the nozzle body 32 so that it can be pushed back and forth in the axial direction or in the direction of the longitudinal axis 14 within the gas register, whereby on the one hand the gap width of the ring opening 36 for the exit of the “primary primary air” and on the other hand the sinking of the nozzle body and thus the fuel inlet in the end wall 33 of the combustion chamber 16 are changeable or adjustable depending on the constitution of the fuel and the type of fuel.
  • the outer gas register for secondary air is not necessary for smaller burners.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Air Bags (AREA)
  • Bakery Products And Manufacturing Methods Therefor (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP86104628A 1985-05-20 1986-04-04 Verfahren und Vorrichtung zum Verbrennen flüssiger und/oder fester Brennstoffe in pulverisierter Form Expired EP0202443B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT86104628T ATE48906T1 (de) 1985-05-20 1986-04-04 Verfahren und vorrichtung zum verbrennen fluessiger und/oder fester brennstoffe in pulverisierter form.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853518080 DE3518080A1 (de) 1985-05-20 1985-05-20 Verfahren und vorrichtung zum verbrennen fluessiger und/oder fester brennstoffe in pulverisierter form
DE3518080 1985-05-20

Publications (3)

Publication Number Publication Date
EP0202443A2 EP0202443A2 (de) 1986-11-26
EP0202443A3 EP0202443A3 (en) 1987-09-30
EP0202443B1 true EP0202443B1 (de) 1989-12-20

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ID=6271157

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Application Number Title Priority Date Filing Date
EP86104628A Expired EP0202443B1 (de) 1985-05-20 1986-04-04 Verfahren und Vorrichtung zum Verbrennen flüssiger und/oder fester Brennstoffe in pulverisierter Form

Country Status (9)

Country Link
US (1) US4679512A (id)
EP (1) EP0202443B1 (id)
JP (1) JPS6284216A (id)
CN (1) CN86103365A (id)
AT (1) ATE48906T1 (id)
AU (1) AU5719786A (id)
DE (2) DE3518080A1 (id)
DK (1) DK229786A (id)
FI (1) FI861942A (id)

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WO1989001117A1 (en) * 1985-09-09 1989-02-09 Coen Company, Inc. Pulverized fuel slurry burner and method of operating same
DE3776405D1 (de) * 1986-05-07 1992-03-12 Hitachi Ltd Zerstaeuber und damit ausgeruesteter kohle-wasserschlamm-heizkessel.
JP2776572B2 (ja) * 1989-07-17 1998-07-16 バブコツク日立株式会社 微粉炭バーナ
DE4133176A1 (de) * 1991-10-07 1993-04-08 Wulff Maschf Appbau Gmbh Brenner fuer fluessige und/oder gasfoermige brennstoffe
DE4212360A1 (de) * 1992-04-13 1993-10-14 Babcock Energie Umwelt Brennerlanze zum Zerstäuben einer Kohle-Wasser-Suspension
US5363782A (en) * 1993-12-06 1994-11-15 Praxair Technology, Inc. Apparatus and process for combusting fluid fuel containing solid particles
US5542839A (en) * 1994-01-31 1996-08-06 Gas Research Institute Temperature controlled low emissions burner
US5515794A (en) * 1995-01-23 1996-05-14 Texaco Inc. Partial oxidation process burner with recessed tip and gas blasting
US5829369A (en) * 1996-11-12 1998-11-03 The Babcock & Wilcox Company Pulverized coal burner
DE69730702T3 (de) 1996-12-27 2009-01-22 Sumitomo Osaka Cement Co., Ltd. Vorrichtung und verfahren zur verbrennung von brennstoff
FR2780489B1 (fr) * 1998-06-24 2000-09-08 Pillard Chauffage Perfectionnement aux bruleurs comportant au moins trois conduits d'alimentation en air, dont deux axial et en rotation, concentriques avec au moins une alimentation-en combustible, et un stabilisateur central
DE19920535A1 (de) * 1999-05-05 2000-11-16 Keiper Recaro Gmbh Co Fahrzeugsitz, insbesondere für einen Lastkraftwagen
US6315551B1 (en) 2000-05-08 2001-11-13 Entreprise Generale De Chauffage Industriel Pillard Burners having at least three air feed ducts, including an axial air duct and a rotary air duct concentric with at least one fuel feed, and a central stabilizer
US7028622B2 (en) 2003-04-04 2006-04-18 Maxon Corporation Apparatus for burning pulverized solid fuels with oxygen
DE102005032109B4 (de) * 2005-07-07 2009-08-06 Hitachi Power Europe Gmbh Kohlenstaubbrenner für niedrige NOx-Emissionen
MX2009005411A (es) * 2006-11-29 2009-06-01 Smidth As F L Quemador con medio para cambiar la direccion de flujo de combustible.
DE102006060867B4 (de) * 2006-12-22 2020-07-02 Khd Humboldt Wedag Gmbh Drehofenbrenner
DE102007021926A1 (de) * 2007-05-10 2008-11-20 Siemens Ag Öl-/Slurrybrenner mit Injektionszerstäubung
US20090280442A1 (en) * 2008-05-05 2009-11-12 American Air Liquide Inc. Device And Method Of Combusting Solid Fuel With Oxygen
US20100078506A1 (en) * 2008-09-30 2010-04-01 General Electric Company Circumferential fuel circuit divider
DE102009010274B4 (de) * 2009-02-24 2014-06-18 Eisenmann Ag Brenner für eine thermische Nachverbrennungsvorrichtung
CN102086415B (zh) * 2009-12-03 2014-08-20 通用电气公司 进料装置及进料方法
US9017067B2 (en) * 2011-02-16 2015-04-28 Air Products And Chemicals, Inc. Oxygen enrichment of premix air-gas burners
EP2500640A1 (en) * 2011-03-16 2012-09-19 L'AIR LIQUIDE, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Low NOx combustion process and burner therefor
JP6070323B2 (ja) 2013-03-21 2017-02-01 大陽日酸株式会社 燃焼バーナ、バーナ装置、及び原料粉体加熱方法
AT513618B1 (de) * 2013-07-02 2014-06-15 Cotraco Holding Gmbh Lanze für die Verbrennung oder Abfackelung von brennbaren Abgasen
FR3031798B1 (fr) 2015-01-20 2018-08-10 Safran Aircraft Engines Systeme d'injection de carburant pour turbomachine d'aeronef, comprenant un canal de traversee d'air a section variable
FI127083B (en) * 2015-10-30 2017-11-15 Outotec Finland Oy Burner and atomizer for a burner
CN108485716A (zh) * 2018-04-28 2018-09-04 余军 生物质垃圾气化炉

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EP0114062A3 (de) * 1983-01-18 1986-02-19 Stubinen Utveckling AB Verfahren und Vorrichtung zum Verbrennen fester Brennstoffe, insbesondere Kohle, Torf oder dergleichen, in pulverisierter Form

Also Published As

Publication number Publication date
EP0202443A3 (en) 1987-09-30
JPS6284216A (ja) 1987-04-17
DE3518080C2 (id) 1987-07-23
FI861942A0 (fi) 1986-05-09
AU5719786A (en) 1986-11-27
FI861942A (fi) 1986-11-21
DK229786A (da) 1986-11-21
US4679512A (en) 1987-07-14
ATE48906T1 (de) 1990-01-15
CN86103365A (zh) 1986-12-24
EP0202443A2 (de) 1986-11-26
DE3667718D1 (de) 1990-01-25
DE3518080A1 (de) 1986-11-20
JPH0454843B2 (id) 1992-09-01
DK229786D0 (da) 1986-05-16

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