EP0780630A2 - Brûleur pour un générateur de chaleur - Google Patents

Brûleur pour un générateur de chaleur Download PDF

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Publication number
EP0780630A2
EP0780630A2 EP96810827A EP96810827A EP0780630A2 EP 0780630 A2 EP0780630 A2 EP 0780630A2 EP 96810827 A EP96810827 A EP 96810827A EP 96810827 A EP96810827 A EP 96810827A EP 0780630 A2 EP0780630 A2 EP 0780630A2
Authority
EP
European Patent Office
Prior art keywords
burner according
flow
fuel
swirl generator
burner
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.)
Granted
Application number
EP96810827A
Other languages
German (de)
English (en)
Other versions
EP0780630B1 (fr
EP0780630A3 (fr
Inventor
Hans Peter Knöpfel
Thomas Ruck
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.)
ALSTROM (SCHWEIZ) AG
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0780630A2 publication Critical patent/EP0780630A2/fr
Publication of EP0780630A3 publication Critical patent/EP0780630A3/fr
Application granted granted Critical
Publication of EP0780630B1 publication Critical patent/EP0780630B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the present invention relates to a burner according to the preamble of claim 1.
  • the invention seeks to remedy this.
  • the object of the invention is to achieve flame stabilization in a premix burner of the type mentioned at the outset with maximized efficiency and minimization of pollutant emissions.
  • the essential measure of the invention relates to the position of the head-side fuel nozzle, which is set back upstream by a certain distance from the inflow of the combustion air, this distance depending on the spray angle selected.
  • the mouth of the fuel nozzle comes to a standstill in the area of a fixed casing, which means that openings can be provided radially around the nozzle mouth, through which purging air flows into the cross section induced by the fuel nozzle.
  • the flow cross-section of these openings is selected such that the air mass flow flowing through these openings in gas operation is not sufficient to shift the backflow zone further downstream.
  • the fuel spray acts practically as a jet pump, which increases the air mass flow through the openings mentioned. This causes a larger axial impulse that shifts the backflow zone further downstream.
  • Another advantage of the invention is that the fuel spray with a larger cone radius enters the main flow, that is to say into the combustion air flowing through the tangential air inlet slots, due to the setback of the fuel nozzle.
  • the fuel spray has already decayed from a film into drops in this plane and the conical surface area of this fuel spray has increased by a factor of 3 when entering the combustion air area from the tangential air inlet slots. This improves the spread of the fuel spray and does not hinder the inflow of the combustion air.
  • Another important advantage of the invention is that by varying the opening cross sections for the air mass flow in the area of the fuel nozzle, the backflow zone and thus the flame position can be directly influenced during operation.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100a is effective, the design of which is shown and described in more detail in the following FIGS. 2-5.
  • This swirl generator 100a is a conical structure which is acted upon tangentially several times by a tangentially flowing combustion air flow 115.
  • the flow formed here is seamlessly transferred to a transition piece 200 using a transition geometry provided downstream of the swirl generator 100a, in such a way that no separation areas can occur there.
  • the configuration of this transition geometry is described in more detail in FIG. 6.
  • This transition piece 200 is extended on the outflow side of the transition geometry by a tube 20, both parts forming the actual mixing tube 220, also called the mixing section, of the burner.
  • the mixing tube 220 can consist of a single piece, that is to say then that the transition piece 200 and tube 20 are fused into a single coherent structure, the characteristics of each part being retained. Become transition piece 200 and tube 20 from two parts created, they are connected by a bushing ring 10, the same bushing ring 10 serving on the head side as an anchoring surface for the swirl generator 100a. Such a bushing ring 10 also has the advantage that different mixing tubes can be used.
  • the actual combustion chamber 30 is located on the outflow side of the tube 20 and is here only symbolized by the flame tube.
  • the mixing tube 220 fulfills the condition that a defined mixing section is provided downstream of the swirl generator 100a, in which a perfect premixing of fuels of different types is achieved.
  • This mixing section i.e. the mixing tube 220, furthermore enables loss-free flow guidance, so that no backflow zone can initially form even in operative connection with the transition geometry, so that the length of the mixing tube 220 can influence the quality of the mixture for all types of fuel.
  • this mixing tube 220 has yet another property, which consists in the fact that in the mixing tube 220 itself the axial speed profile has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. However, it is correct that with such a configuration this axial speed drops towards the wall.
  • the mixing tube 220 is provided with a number of regularly or irregularly distributed bores 21 of various cross-sections and directions in the flow and circumferential direction, through which an amount of air flows into the interior of the mixing tube 220 and along the wall in the Inducing an increase in speed in the sense of filming.
  • Another possibility of achieving the same effect is that the flow cross section of the mixing tube 220 is narrowed on the downstream side of the transition channels 201, which form the transition geometry already mentioned, as a result of which the overall speed level within the mixing tube 220 is increased.
  • these bores 21 run under one acute angle with respect to the burner axis 60.
  • the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 220.
  • the transition channels 201 mentioned therefore bridge the respective cross-sectional difference without adversely affecting the flow formed. If the selected precaution triggers an intolerable pressure loss when guiding the pipe flow 40 along the mixing pipe 220, this can be remedied by providing a diffuser (not shown in the figure) at the end of the mixing pipe.
  • a combustion chamber 30 adjoins the end of the mixing tube 220, a cross-sectional jump occurring between the two flow cross sections. Only here does a central backflow zone 50 form, which has the properties of a flame holder.
  • FIG. 2 shows a schematic illustration of a swirl generator 100a, which is described in more detail in the following FIGS. 3-5 becomes.
  • 1 is the representation of the fuel nozzle 103 placed in the center, which is set back upstream relative to the beginning 125 of the conical flow cross section, the path 126 depending on the spray angle 105 selected.
  • the mouth 104 of the fuel nozzle 103 comes to rest in the region of the fixed casing 101a, 102a on the head side.
  • the fuel spray 105 resulting from the displacement of the fuel nozzle 103 enters the area covered by the main flow of the combustion air into the interior 114 of the burner with a larger cone radius, so that the fuel spray 105 no longer behaves as a solid, compact body in this area.
  • radially or quasi-radially arranged openings 124 are provided in the area of the plane of the fuel spray orifice 104, through which a purge air flows into the cross section induced by the size of the fuel nozzle 103.
  • the flow cross-section of these openings 124 is selected such that, in gas operation, the air mass flow flowing through these openings is not sufficient to shift the return flow zone (cf. FIG. 1) further downstream.
  • the fuel spray 105 acts practically as a jet pump, which increases the air mass flow through the openings 124 mentioned. This causes a larger axial impulse, which shifts the backflow zone further downstream, which acts as a good measure against back-ignition of the flame.
  • the schematically illustrated conical partial bodies 101, 102 are discussed in more detail in FIGS. 2-5.
  • the configuration and mode of operation of the tangential air inlet slots 119, 120 are also dealt with in more detail there.
  • FIG. 3 is used at the same time as FIG. 2. Furthermore, in order not to make this FIG. 2 unnecessarily confusing, the guide plates 121a, 121b shown schematically according to FIG. 3 have only been hinted at in it. In the description of FIG. 2, reference is made below to the figures mentioned as required.
  • the first part of the burner according to FIG. 1 forms the swirl generator 100a shown in FIG. 2.
  • This consists of two hollow, conical partial bodies 101, 102 which are nested in one another in a staggered manner.
  • the number of conical partial bodies can of course be greater than two, as shown in FIGS. 4 and 5; This depends on the mode of operation of the entire burner, as will be explained in more detail below. In certain operating constellations, it is not excluded to provide a swirl generator consisting of a single spiral.
  • the offset of the respective central axis or longitudinal symmetry axes 201b, 202b of the tapered partial bodies 101, 102 to one another creates a tangential channel, that is to say an air inlet slot 119, 120 (FIG.
  • the combustion air 115 in Interior of the swirl generator 100a ie flows into the cone cavity 114 of the same.
  • the conical shape of the partial bodies 101, 102 shown in the flow direction has a specific fixed angle.
  • the partial bodies 101, 102 can have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or. Tulip. The last two forms are not included in the drawing, since they can be easily understood by a person skilled in the art.
  • the two conical partial bodies 101, 102 each have a cylindrical starting part 101a, 102a, which likewise, analogously to the conical partial bodies 101, 102, run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the swirl generator 100a.
  • a nozzle 103 is preferably accommodated for a liquid fuel 112, the injection 104 of which coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial bodies 101, 102.
  • the injection capacity and the type of this nozzle 103 depend on the given parameters of the respective burner.
  • the swirl generator 100a can be made purely conical, that is to say without cylindrical starting parts 101a, 102a.
  • the tapered partial bodies 101, 102 further each have a fuel line 108, 109, which are arranged along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through there, such as arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably placed at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture.
  • the fuel 112 brought in through the nozzle 103 is normally a liquid fuel, and it is readily possible to form a mixture with another medium. This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a cone-shaped fuel spray 105 is thus formed from the nozzle 103 and is enclosed by the rotating combustion air 115 flowing in tangentially.
  • the concentration of the injected fuel 112 is continuously reduced by the inflowing combustion air 115 to mix in the direction of evaporation.
  • a gaseous fuel 113 is introduced via the opening nozzles 117, the fuel / air mixture is formed directly at the end of the air inlet slots 119, 120.
  • the combustion air 115 is additionally preheated or, for example, with a recirculated one Enriched with flue gas or exhaust gas, this sustainably supports the evaporation of the liquid fuel 112 before this mixture flows into the downstream stage.
  • liquid fuels should be supplied via lines 108, 109.
  • the conical partial bodies 101, 102 with regard to the cone angle and the width of the tangential air inlet slots 119, 120, narrow limits must be observed per se so that the desired flow field of the combustion air 115 can be set at the outlet of the swirl generator 100a.
  • reducing the tangential air inlet slots 119, 120 already favors the faster formation of a backflow zone in the area of the swirl generator.
  • the axial speed within the swirl generator 100a can be changed by a corresponding supply, not shown, of an axial combustion air flow.
  • a corresponding swirl generation prevents the formation of flow separations within the mixing tube downstream of the swirl generator 100a.
  • the design of the swirl generator 100a is furthermore particularly suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operational bandwidth can be recorded without changing the overall length of the swirl generator 100a.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which an overlap thereof can even be provided. It is also possible to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement. It is thus possible to vary the shape, size and configuration of the tangential air inlet slots 119, 120 as desired, with which the swirl generator 100a can be used universally without changing its overall length.
  • the guide plates 121a, 121b have a flow initiation function whereby, depending on their length, they extend the respective end of the tapered partial bodies 101, 102 in the direction of flow towards the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can be optimized by opening or closing the guide plates 121a, 121b about a pivot point 123 located in the region of the entry of this channel into the cone cavity 114, in particular this is necessary if the original gap size of the tangential air inlet slots 119, 120 should be changed dynamically.
  • these dynamic arrangements can also be provided statically, in that guide baffles as required form a fixed component with the tapered partial bodies 101, 102.
  • the swirl generator 100a can also be operated without baffles, or other aids can be provided for this.
  • the swirl generator 100a is now composed of four partial bodies 130, 131, 132, 133.
  • the associated longitudinal symmetry axes for each partial body are marked with the letter a.
  • this configuration it should be said that, due to the lower swirl strength generated in this way and in cooperation with a correspondingly enlarged slot width, it is ideally suited to prevent the vortex flow from bursting in the mixing tube on the downstream side of the swirl generator, so that the mixing tube can best fulfill the role intended for it .
  • FIG. 6 differs from FIG. 5 in that the partial bodies 140, 141, 142, 143 have a blade profile shape which is provided to provide a certain flow. Otherwise the mode of operation of the swirl generator has remained the same.
  • the admixture of the fuel 116 in the combustion air flow 115 takes place from the inside of the blade profiles, ie the fuel line 108 is now integrated in the individual blades. Also here the longitudinal symmetry axes to the individual partial bodies are marked with the letter a.
  • the transition geometry is constructed for a swirl generator 100a with four partial bodies, corresponding to FIG. 4 or 5. Accordingly, the transition geometry as a natural extension of the upstream partial body four transition channels 201, whereby the conical quarter surface of the partial body is extended until it the wall of the tube 20 or. of the mixing tube 220 cuts.
  • the same considerations also apply if the swirl generator is constructed from a principle other than that described under FIG. 2.
  • the surface of the individual transition channels 201 which runs downward in the flow direction has a shape which runs spirally in the flow direction and which describes a crescent-shaped course, corresponding to the fact that in the present case the flow cross section of the transition piece 200 widens conically in the flow direction.
  • the swirl angle of the transition channels 201 in the flow direction is selected such that the pipe flow then still has a sufficiently large distance up to the cross-sectional jump at the combustion chamber inlet in order to achieve a perfect premixing with the injected fuel. Furthermore, the above-mentioned measures also increase the axial speed on the mixing tube wall downstream of the swirl generator. The transition geometry and the measures in the area of the mixing tube bring about a significant increase in the axial speed profile towards the center of the mixing tube, so that the risk of early ignition is decisively counteracted.
  • the flow cross section of the tube 20 receives a transition radius R in this area, the size of which basically depends on the flow within the Tube 20 depends.
  • This radius R is selected so that the flow is applied to the wall and the swirl number can increase sharply.
  • the size of the radius R can be quantitatively defined so that it is> 10% of the inner diameter d of the tube 20.
  • the backflow bladder 50 now increases enormously.
  • This radius R extends to the exit plane of the tube 20, the angle ⁇ between the beginning and end of the curvature being ⁇ 90 °.
  • the tear-off edge A runs along one leg of the angle ⁇ into the interior of the tube 20 and thus forms a tear-off step S with respect to the front point of the tear-off edge A, the depth of which is> 3 mm.
  • the edge running parallel to the exit plane of the tube 20 can be brought back to the exit plane level by means of a curved course.
  • the angle ⁇ ' which extends between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20, is the same size as the angle ⁇ .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP96810827A 1995-12-21 1996-11-27 Brûleur pour un générateur de chaleur Expired - Lifetime EP0780630B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19547912A DE19547912A1 (de) 1995-12-21 1995-12-21 Brenner für einen Wärmeerzeuger
DE19547912 1995-12-21

Publications (3)

Publication Number Publication Date
EP0780630A2 true EP0780630A2 (fr) 1997-06-25
EP0780630A3 EP0780630A3 (fr) 1998-07-29
EP0780630B1 EP0780630B1 (fr) 2001-09-26

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810827A Expired - Lifetime EP0780630B1 (fr) 1995-12-21 1996-11-27 Brûleur pour un générateur de chaleur

Country Status (5)

Country Link
US (1) US5876196A (fr)
EP (1) EP0780630B1 (fr)
JP (1) JP3904644B2 (fr)
CN (1) CN1111672C (fr)
DE (2) DE19547912A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0833104A3 (fr) * 1996-09-25 1998-07-29 Abb Research Ltd. Brûleur pour le fonctionnement d'une chambre de combustion
EP0833105A3 (fr) * 1996-09-30 1998-10-21 Abb Research Ltd. Brûleur à prémélange
EP0903540A1 (fr) * 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0909921A1 (fr) * 1997-10-14 1999-04-21 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6102692A (en) * 1997-08-25 2000-08-15 Abb Alstom Power (Switzerland) Ltd Burner for a heat generator
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
DE102014205200B3 (de) * 2014-03-20 2015-06-11 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
WO2015140084A1 (fr) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Dispositif de postcombustion thermique d'air d'échappement

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DE59709446D1 (de) * 1997-10-31 2003-04-10 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE59710788D1 (de) * 1997-11-13 2003-10-30 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
JP4524902B2 (ja) * 2000-10-25 2010-08-18 株式会社Ｉｈｉ 予混合燃料噴射弁を備えた低ＮＯｘ燃焼器
DE50110801D1 (de) * 2000-12-23 2006-10-05 Alstom Technology Ltd Brenner zur Erzeugung eines Heissgases
DE50212351D1 (de) * 2001-04-30 2008-07-24 Alstom Technology Ltd Vorrichtung zum Verbrennen eines gasförmigen Brennstoff-Oxidator-Gemischs
EP1714081B1 (fr) * 2004-02-12 2008-04-09 Alstom Technology Ltd Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
US7097448B2 (en) * 2004-05-07 2006-08-29 Peter Chesney Vortex type gas lamp
JP4977522B2 (ja) * 2007-04-25 2012-07-18 株式会社日立製作所 ガスタービン燃焼器
DE102008000050A1 (de) * 2007-08-07 2009-02-12 Alstom Technology Ltd. Brenner für eine Brennkammer einer Turbogruppe
GB0902221D0 (en) * 2009-02-11 2009-03-25 Edwards Ltd Pilot
CA2786597A1 (fr) 2010-01-06 2011-07-14 The Outdoor Greatroom Company LLLP Ensemble brasero
JP5203489B2 (ja) * 2011-06-15 2013-06-05 中外炉工業株式会社 燃焼装置
FR3011911B1 (fr) 2013-10-14 2015-11-20 Cogebio Bruleur de gaz pauvre
CN108006695B (zh) * 2016-11-01 2019-12-06 北京华清燃气轮机与煤气化联合循环工程技术有限公司 优化用于燃气轮机的预混合燃料喷嘴的方法

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0833104A3 (fr) * 1996-09-25 1998-07-29 Abb Research Ltd. Brûleur pour le fonctionnement d'une chambre de combustion
EP0833105A3 (fr) * 1996-09-30 1998-10-21 Abb Research Ltd. Brûleur à prémélange
US6102692A (en) * 1997-08-25 2000-08-15 Abb Alstom Power (Switzerland) Ltd Burner for a heat generator
EP0903540A1 (fr) * 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US5944511A (en) * 1997-09-19 1999-08-31 Abb Research Ltd. Burner for operating a heat generator
EP0909921A1 (fr) * 1997-10-14 1999-04-21 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US5954495A (en) * 1997-10-14 1999-09-21 Abb Research Ltd. Burner for operating a heat generator
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
DE102014205200B3 (de) * 2014-03-20 2015-06-11 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
WO2015140084A1 (fr) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Dispositif de postcombustion thermique d'air d'échappement
DE102014205198A1 (de) * 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Brenner und Vorrichtung zur thermischen Nachverbrennung von Abluft
WO2015140085A1 (fr) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Dispositif de postcombustion thermique d'air d'échappement
CN106415126A (zh) * 2014-03-20 2017-02-15 Kba金属印刷有限公司 用于以热学方式后续燃烧废气的装置
CN106461209A (zh) * 2014-03-20 2017-02-22 Kba金属印刷有限公司 用于以热学方式后续燃烧废气的装置
CN106415126B (zh) * 2014-03-20 2018-08-31 杜尔***股份公司 具有工业设备和后续燃烧装置的装置
CN106461209B (zh) * 2014-03-20 2018-10-16 杜尔***股份公司 具有工业设备和后续燃烧装置的装置

Also Published As

Publication number Publication date
CN1157893A (zh) 1997-08-27
DE59607769D1 (de) 2001-10-31
DE19547912A1 (de) 1997-06-26
US5876196A (en) 1999-03-02
JPH09178121A (ja) 1997-07-11
JP3904644B2 (ja) 2007-04-11
EP0780630B1 (fr) 2001-09-26
CN1111672C (zh) 2003-06-18
EP0780630A3 (fr) 1998-07-29

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