EP0711953A2 - Brûleur à prémélange - Google Patents

Brûleur à prémélange

Info

Publication number
EP0711953A2
EP0711953A2 EP95810671A EP95810671A EP0711953A2 EP 0711953 A2 EP0711953 A2 EP 0711953A2 EP 95810671 A EP95810671 A EP 95810671A EP 95810671 A EP95810671 A EP 95810671A EP 0711953 A2 EP0711953 A2 EP 0711953A2
Authority
EP
European Patent Office
Prior art keywords
nozzle
burner
conical
fuel
pressure
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
EP95810671A
Other languages
German (de)
English (en)
Other versions
EP0711953B1 (fr
EP0711953A3 (fr
Inventor
Klaus Dr. Döbbeling
Johannes Santner
Christian Dr. Steinbach
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.)
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 EP0711953A2 publication Critical patent/EP0711953A2/fr
Publication of EP0711953A3 publication Critical patent/EP0711953A3/fr
Application granted granted Critical
Publication of EP0711953B1 publication Critical patent/EP0711953B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • 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 
    • 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 invention relates to a low-pollutant premix burner of the double-cone type for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing system with a high-pressure atomization nozzle arranged in the tip of the cone cavity for atomizing liquid fuel, the nozzle being designed with or without turbulence chamber and having at least two nozzle bores with the Interior of the burner communicates.
  • Atomizer burners are known in which the oil which is burned is finely divided mechanically. It is broken down into fine droplets of approximately 10 to 400 ⁇ m in diameter (oil mist), which evaporate and burn in the flame when mixed with the combustion air.
  • pressure atomizers see Lueger - Lexikon dertechnik, Manual Verlags-Anstalt Stuttgart, 1965, Volume 7, p.600
  • the oil is supplied to an atomizing nozzle by an oil pump at a pressure of approx. 4 to 25 bar.
  • the oil enters a swirl chamber via essentially tangential slots and leaves the nozzle via a nozzle bore. It is thereby achieved that the oil particles receive two components of motion, an axial and a radial.
  • Swirl nozzles pressure atomizers
  • air-assisted atomizers of the known types with a pressure of up to approx. 100 bar are hardly suitable for this because they do not allow a small angle of spread, the atomization quality is limited and the impulse of the drop spray is low.
  • This consists of a nozzle body, in which a turbulence chamber is formed, which is connected to an outside space via at least one nozzle bore, and which has at least one supply channel for the liquid to be atomized, which can be supplied under pressure. It is characterized in that the cross-sectional area of the feed channel opening into the turbulence chamber is larger by a factor of 2 to 10 than the cross-sectional area of the nozzle bore.
  • This arrangement makes it possible to generate a high level of turbulence in the turbulence chamber, which does not subside on the way to the point of exit from the nozzle.
  • the fluid jet is caused to decay rapidly by the turbulence generated in front of the nozzle bore in the outside space, that is to say after leaving the nozzle bore, resulting in low angles of propagation of 20 ° and less.
  • the droplet size is also very small. The only disadvantage is the loss of fuel pulse in the turbulence generator, which does not allow directed introduction.
  • the invention tries to avoid all these disadvantages. It is based on the task of creating a low-pollutant premix burner of the double-cone type, which has a high-pressure atomizing nozzle for atomizing liquid fuel, which is of simple construction and with which a very good atomization quality with a high fuel pulse is achieved.
  • the advantages of the invention include in the fact that in the high-pressure atomization nozzle according to the invention, a fine atomization of the fuel is associated with a high fuel pulse and thus rapid evaporation of the fuel and good premixing of the fuel spray with the combustion air are achieved.
  • the high-pressure atomizing nozzle is simple in design, easily accessible inside the burner and is characterized by a small space requirement in the tip of the burner.
  • the fuel can be injected specifically into zones of high air speed. The need to add water to reduce NOx emissions is eliminated, because due to the above fine atomization, rapid evaporation of the fuel and the good premixing of the fuel spray with the combustion air, the NOx emissions are very low.
  • nozzle bores of the high-pressure atomization nozzle are aligned with the air inlet slots of the conical partial bodies, because in this case the premixing of the fuel spray with the incoming combustion air is most intensive.
  • the high-pressure atomization nozzle is a turbulence-assisted high-pressure nozzle with a turbulence chamber arranged in front of the nozzle bores, the turbulence chamber being delimited by a tube, a conical cover of the tube in which the nozzle bores are arranged, and by a filler with at least one feed opening , which is preferably arranged centrally in the filler.
  • the turbulence generated in front of the nozzle bore causes a rapid disintegration of the liquid jet and a particularly fine drop spray achieved.
  • the resulting drop spray is also characterized by small spreading angles.
  • a high-pressure orifice nozzle is advantageously used as the high-pressure atomizing nozzle, which consists of a tube and a conical cover of the tube in which the nozzle openings are arranged.
  • a very high fuel pulse is achieved, which enables the fuel spray to penetrate deeply into the combustion air.
  • nozzle bores are arranged in the outer third of the conical cover near the wall of the tube. Then very good atomization qualities are achieved.
  • the drawing shows two exemplary embodiments of the invention using a double-cone burner for operating a gas turbine.
  • FIG. 1 schematically shows a section through the premix burner, which essentially consists of two partial cone bodies 1, 2 and whose basic structure is described in EP 0 321 809 B1.
  • FIG. 2 and the sections shown in FIGS. 3 to 5 are used at the same time.
  • Fig. 2 shows a perspective view of the double-cone burner with integrated premixing zone.
  • the two partial cone bodies 1, 2 are arranged radially offset from one another with respect to their longitudinal symmetry axes 1b, 2b. This creates tangential air inlet slots on both sides of the partial cone bodies 1, 2 in the opposite inflow arrangement 19, 20, through which the combustion air 15 flows into the interior 14 of the burner, ie into the cone cavity formed by the two partial cone bodies 1, 2.
  • the partial cone bodies 1, 2 expand in a straight line in the direction of flow, ie they have a constant angle ⁇ with the burner axis 5.
  • the two partial cone bodies 1, 2 each have a cylindrical starting part 1a, 2a, which also run offset.
  • this cylindrical starting part 1a, 2a there is a high-pressure atomization nozzle 3 with at least two nozzle openings 11, which are arranged approximately in the narrowest cross section of the conical interior 14 of the burner.
  • the burner can also be designed without a cylindrical initial part, that is to say purely conical.
  • the two partial cone bodies 1, 2 each have a fuel feed line 8, 9 along the air inlet slots 19, 20, which are provided on the long side with openings 17 through which another fuel 13 (gaseous or liquid) flows.
  • This fuel 13 is mixed with the combustion air 15 flowing through the tangential air inlet slots 19, 20 into the interior of the burner, which is represented by the arrows 16. Mixed operation of the burner via the nozzle 3 and the fuel feeds 8, 9 is possible.
  • a front plate 10 is arranged with openings 11, through which dilution air or cooling air can be supplied to the combustion chamber 22 if necessary. In addition, this air supply ensures that flame stabilization takes place at the burner outlet. There is a stable flame front 7 with a backflow zone 6.
  • guide plates 21 a, 21 b can be seen from FIGS. 3 to 5. These can be opened or closed, for example, about a pivot point 23, so that the original gap size of the tangential air inlet slots is thereby 19, 20 is changed. Of course, the burner can also be operated without these baffles 21a, 21b.
  • FIG. 6 shows a turbulence-assisted high-pressure atomization nozzle 3, which, as shown in FIG. 1 or FIG. 2, is arranged in the cone tip of the burner. It consists of a tube 26 which surrounds a feed channel 24 and a turbulence chamber 25. The tube 26 is closed by a conical cover 27 in which there are two nozzle bores 18 in the outer third near the tube wall. These nozzle bores 18 establish the connection between the turbulence chamber 25 located in the tube 26 and the interior 14 (cone cavity) of the burner. The turbulence chamber 25 is delimited next to the pipe 26 by a filler 28 and the cover 27 of the pipe 26.
  • a feed opening 29 for the fuel 12 to be atomized is arranged in the center.
  • This opening can of course also be arranged off-center or there can be a plurality of feed openings 29. It is advantageous if the feed opening 29 has a cross section which narrows in the direction of flow, as shown in FIG. 6.
  • the fuel 12 to be atomized flows under a pressure of greater than 100 bar via the feed line 24 and the opening 29 into the turbulence chamber 25, which has an abruptly widening cross section with respect to the feed opening 29.
  • the fuel jet hits the cone tip of the conical lid 27.
  • a high level of turbulence is generated by intensive shearing and the rebounding of the jets from the surface of the lid, which does not subside on the short path until it emerges from the nozzle.
  • the fluid jet is brought to rapid decay by the turbulence in the burner interior 14 generated in front of the two nozzle bores 18, which results in very small angles of propagation.
  • the fuel 12 is atomized well by the high momentum and the high relative speed to the air. It has a high penetration depth and thus leads to a high level of mixing.
  • the fuel is distributed very well in the combustion air stream 15 along the burner wall. It mixes very well along the cone in the fresh air flow at the end of the burner, so that an excellent premixing is achieved, which has a favorable effect on a low value of the pollutant emissions.
  • Fig. 7 shows a second embodiment.
  • the high-pressure atomizing nozzle 3 is a multi-hole high-pressure orifice nozzle, the structure of which is the same as the above. corresponds to turbulence-assisted nozzle, although of course there is no turbulence chamber in the orifice nozzle.
  • the achievable fuel drop size is somewhat larger under comparable conditions to the first exemplary embodiment (see Fig. 8), but a high fuel pulse can be achieved for this, which also results in the above-mentioned through the targeted injection into zones of high air speed. Advantages leads.
  • the cross section of the nozzle 3, its position and the direction of injection result from the desired throughput (depending on the form) taking into account sufficiently high Reynolds numbers in the nozzle bores 18.
  • the diagram shown in FIG. 8 illustrates the dependence of the droplet diameter d T on the admission pressure p for various Limit diameter of the drop mass distribution.
  • Dx denotes the limit diameter that x mass% of all particles fall below.
  • SMD is the Sauter diameter, i.e. the diameter of a droplet that has the same surface to volume ratio as the total jet.
  • the high pressure atomization nozzle on which the diagram is based was charged with water and had the following parameters: Diameter of the nozzle 10.0 mm Feed channel diameter 8.0 mm Diameter of the feed opening in the filler 1.8 mm Diameter of the nozzle bores 0.6 mm Length of the turbulence chamber 7.0 mm.
  • FIG. 9 shows the dependence of the atmospheric NOx emission values on the flame temperature and the type of nozzle used for atomizing the liquid fuel. Turbulence-assisted two-hole high-pressure nozzles with different angles ⁇ between the fuel injection and the burner axis were examined (11 °, 15 °, 20 °). The cone half angle ⁇ of the burner was 10.95 ° in each case. In comparison to pressure atomizing nozzles (swirl nozzles), when using the high pressure atomizing nozzles 3 according to the invention with two nozzle bores 18 directed towards the air inlet slots 19, 20, premix burners of the double-cone type achieve significantly lower NOx emission values.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)
EP95810671A 1994-11-12 1995-10-30 Brûleur à prémélange Expired - Lifetime EP0711953B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4440558A DE4440558A1 (de) 1994-11-12 1994-11-12 Vormischbrenner
DE4440558 1994-11-12

Publications (3)

Publication Number Publication Date
EP0711953A2 true EP0711953A2 (fr) 1996-05-15
EP0711953A3 EP0711953A3 (fr) 1997-09-03
EP0711953B1 EP0711953B1 (fr) 2001-07-25

Family

ID=6533228

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810671A Expired - Lifetime EP0711953B1 (fr) 1994-11-12 1995-10-30 Brûleur à prémélange

Country Status (4)

Country Link
US (1) US5586878A (fr)
EP (1) EP0711953B1 (fr)
JP (1) JPH08210606A (fr)
DE (2) DE4440558A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0902233A1 (fr) 1997-09-15 1999-03-17 Abb Research Ltd. Buse de pulvérisation par pression combinée
WO2005121648A1 (fr) * 2004-06-08 2005-12-22 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide et procede pour faire fonctionner un bruleur a premelange
US7694521B2 (en) 2004-03-03 2010-04-13 Mitsubishi Heavy Industries, Ltd. Installation structure of pilot nozzle of combustor
CN103542412A (zh) * 2012-07-10 2014-01-29 阿尔斯通技术有限公司 用于燃气涡轮的多锥体式预混合喷燃器

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE10055408A1 (de) * 2000-11-09 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brenstoffeinspritzung in einen Brenner
DE10247764A1 (de) * 2002-10-14 2004-04-22 Robert Bosch Gmbh Zerstäuberdüse
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
CN100590355C (zh) * 2004-02-12 2010-02-17 阿尔斯通技术有限公司 具有限定圆锥形涡旋室的涡旋发生器的、传感器监视的预混合燃烧器
EP1802915B1 (fr) 2004-10-18 2016-11-30 General Electric Technology GmbH Bruleur pour turbine a gaz
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle
DE102008015577A1 (de) * 2008-03-18 2009-10-22 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur schadstoffarmen Verbrennung mit flüssigem Brennstoff und Brennkammervorrichtung
US8683804B2 (en) * 2009-11-13 2014-04-01 General Electric Company Premixing apparatus for fuel injection in a turbine engine
JP5448762B2 (ja) * 2009-12-02 2014-03-19 三菱重工業株式会社 ガスタービン用燃焼バーナ
KR101489579B1 (ko) * 2013-05-30 2015-02-03 현대하이스코 주식회사 미세 분무 노즐을 이용한 액상 연료 개질 장치

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
FR2239162A5 (en) * 1973-07-27 1975-02-21 Utilisation Ration Gaz Nozzle for liquified petroleum gas burner - is conical with ring of outlet holes and restricted inlet passage
US4128206A (en) * 1977-05-31 1978-12-05 Delavan Corporation Low drift flat spray nozzle and method
FR2406725A1 (fr) * 1977-10-24 1979-05-18 Proizv Ob Procede de brulage de carburant dans une chambre de combustion et chambre de combustion annulaire pour la mise en oeuvre dudit procede
US4348168A (en) * 1975-04-22 1982-09-07 Christian Coulon Process and apparatus for atomizing and burning liquid fuels
EP0210462A1 (fr) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Chambre de combustion double
EP0518072A1 (fr) * 1991-06-14 1992-12-16 Asea Brown Boveri Ag Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH680467A5 (fr) * 1989-12-22 1992-08-31 Asea Brown Boveri
DE59105449D1 (de) * 1991-01-23 1995-06-14 Asea Brown Boveri Hochdruckzerstäubungsdüse.
CH682952A5 (de) * 1991-03-12 1993-12-15 Asea Brown Boveri Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes.
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
FR2239162A5 (en) * 1973-07-27 1975-02-21 Utilisation Ration Gaz Nozzle for liquified petroleum gas burner - is conical with ring of outlet holes and restricted inlet passage
US4348168A (en) * 1975-04-22 1982-09-07 Christian Coulon Process and apparatus for atomizing and burning liquid fuels
US4128206A (en) * 1977-05-31 1978-12-05 Delavan Corporation Low drift flat spray nozzle and method
FR2406725A1 (fr) * 1977-10-24 1979-05-18 Proizv Ob Procede de brulage de carburant dans une chambre de combustion et chambre de combustion annulaire pour la mise en oeuvre dudit procede
EP0210462A1 (fr) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Chambre de combustion double
EP0518072A1 (fr) * 1991-06-14 1992-12-16 Asea Brown Boveri Ag Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0902233A1 (fr) 1997-09-15 1999-03-17 Abb Research Ltd. Buse de pulvérisation par pression combinée
US6378787B1 (en) 1997-09-15 2002-04-30 Alstom Combined pressure atomizing nozzle
US7694521B2 (en) 2004-03-03 2010-04-13 Mitsubishi Heavy Industries, Ltd. Installation structure of pilot nozzle of combustor
DE112004002704B4 (de) * 2004-03-03 2011-04-07 Mitsubishi Heavy Industries, Ltd. Verbrennungsanlage
WO2005121648A1 (fr) * 2004-06-08 2005-12-22 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide et procede pour faire fonctionner un bruleur a premelange
US7997896B2 (en) 2004-06-08 2011-08-16 Alstom Technology Ltd Premix burner with staged liquid fuel supply and also method for operating a premix burner
CN103542412A (zh) * 2012-07-10 2014-01-29 阿尔斯通技术有限公司 用于燃气涡轮的多锥体式预混合喷燃器
CN103542412B (zh) * 2012-07-10 2016-02-03 阿尔斯通技术有限公司 用于燃气涡轮的多锥体式预混合喷燃器
US9441837B2 (en) 2012-07-10 2016-09-13 General Electric Technology Gmbh Premix burner of the multi-cone type for a gas turbine

Also Published As

Publication number Publication date
US5586878A (en) 1996-12-24
DE4440558A1 (de) 1996-05-15
EP0711953B1 (fr) 2001-07-25
EP0711953A3 (fr) 1997-09-03
JPH08210606A (ja) 1996-08-20
DE59509445D1 (de) 2001-08-30

Similar Documents

Publication Publication Date Title
EP0892212B1 (fr) Buse de pulvérisation par pression
EP0794383B1 (fr) Méthode d'exploitation d'une buse de pulvérisation par pression
EP0433790B1 (fr) Brûleur
DE69519849T2 (de) Brennstoffdüse mit tangentialer einspritzung
EP0503319B1 (fr) Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux
EP0902233B1 (fr) Buse de pulvérisation par pression combinée
DE69718253T2 (de) Vorrichtung zur Einspritzung von mit Luft zerstäubten Einzelstrahlen aus flüssigem Brennstoff
EP0911583B1 (fr) Procédé de mise en oeuvre d'un brûleur à prémélange
EP0711953B1 (fr) Brûleur à prémélange
EP0276696A2 (fr) Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
EP2423597A2 (fr) Brûleur à prémélange pour une turbine à gaz
EP0924460B1 (fr) Buse de pulvérisation par pression à deux étages
DE3609960A1 (de) Vorrichtung und verfahren zum zerstaeuben von fluessigem brennstoff
EP0433789A1 (fr) Procédé d'une combustion à mélange préalable d'un combustible liquide
EP0394800B1 (fr) Brûleur à mélange préalable pour la génération de gaz chaud
EP0718550B1 (fr) Gicleur
EP0692674A2 (fr) Procédé et dispositif pour la répartition du combustible dans un brûleur adapté aux combustibles liquides ainsi que gazeux
EP0742411B1 (fr) Alimentation en air pour une chambre de combustion à prémélange
EP0924461B1 (fr) Buse de pulvérisation par pression à deux étages
EP0911582B1 (fr) Procédé d'utilisation d'un brûleur à prémélange et brûleur à prémélange
EP0496016B1 (fr) Buse de pulvérisation haute-pression
DE2552864A1 (de) Verfahren und brenner zum verbrennen von fluessigen brennstoffen
DE4033710A1 (de) Brenner fuer brennkraftmaschine
DE19854382B4 (de) Verfahren und Vorrichtung zur Zerstäubung flüssigen Brennstoffs für eine Feuerungsanlage
DE4401097A1 (de) Verfahren zur Reduzierung der NOX-Emissionen sowie Vorrichtung zur Durchführung des Verfahrens

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): DE FR GB

17P Request for examination filed

Effective date: 19980202

17Q First examination report despatched

Effective date: 19991119

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20010725

Ref country code: FR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20010725

REF Corresponds to:

Ref document number: 59509445

Country of ref document: DE

Date of ref document: 20010830

EN Fr: translation not filed
GBV Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed]

Effective date: 20010725

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF THE APPLICANT RENOUNCES

Effective date: 20101102

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20101029

Year of fee payment: 16