EP0503319A2 - Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux - Google Patents

Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux Download PDF

Info

Publication number
EP0503319A2
EP0503319A2 EP92102736A EP92102736A EP0503319A2 EP 0503319 A2 EP0503319 A2 EP 0503319A2 EP 92102736 A EP92102736 A EP 92102736A EP 92102736 A EP92102736 A EP 92102736A EP 0503319 A2 EP0503319 A2 EP 0503319A2
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
nozzles
inlet openings
interior
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
EP92102736A
Other languages
German (de)
English (en)
Other versions
EP0503319B1 (fr
EP0503319A3 (en
Inventor
Klaus Dr. Döbbeling
Thomas Dr. Sattelmayer
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 Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri 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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0503319A2 publication Critical patent/EP0503319A2/fr
Publication of EP0503319A3 publication Critical patent/EP0503319A3/de
Application granted granted Critical
Publication of EP0503319B1 publication Critical patent/EP0503319B1/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
    • 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
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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 for a premix-like combustion of a liquid fuel. It also relates to a method for operating such a burner.
  • a burner has become known, in the interior of which a fuel nozzle is placed, from which a conical fuel spray is formed, which flows in the direction of flow and flows around combustion air streams flowing tangentially into the interior of the burner and is mixed in the flow direction of the burner becomes.
  • the tangential entry opening into the interior of the burner results from the fact that the burner itself consists of two hollow, conical partial bodies, the central axes of which are offset from one another.
  • the ignition of this air / fuel mixture takes place at the exit of the burner, a backflow zone forming in the area of the burner mouth, which together with the high axial velocity upstream prevents the flame from flashing back from the combustion chamber upstream into the burner.
  • the invention seeks to remedy this.
  • the invention is based on the object of proposing a low-emission, dry combustion of a liquid fuel in a burner and a method of the type mentioned, the interaction between flame radiation and fuel droplets, which leads to a pre-ignition of the mixture leads to prevent.
  • the main advantage of the invention can be seen in the fact that the liquid fuel is injected into an area immediately before it enters the interior and is mixed there with the combustion air flow.
  • the fuel is evaporated essentially only in the inlet openings of the burner, only fuel vapor enters the interior of the burner.
  • the risk of the mixture igniting prematurely is averted, because an evaporated fuel hardly absorbs flame radiation. This enables low-NOx / CO / UHC combustion.
  • FIGS. 1 and 2 Ways of carrying out the invention, commercial usability In order to be able to grasp the structure of the burner better and immediately, it is recommended to use FIGS. 1 and 2 at the same time.
  • the core body of the burner shown in FIG. 1 consists of two half hollow conical partial bodies 1, 2, which are offset from one another and thus form the body according to the application.
  • the displacement of the respective central axes 1a, 2a (see FIG. 2) of the individual partial bodies 1, 2 creates a tangential inlet opening 1b, 2b on both sides of the burner in an axially symmetrical arrangement, through which the inflow of an air / fuel mixture into the Interior 3 of the burner, ie flows into the cone cavity, the direction of flow of the air / fuel mixture through the 180 ° offset inlet openings 1b, 2b into the interior 3 in the clockwise or counterclockwise direction, depending on the plane in which the offset of the central axes 1a, 2a is determined.
  • the conical shape of the partial bodies 1, 2 shown in the flow direction has a certain fixed angle.
  • the partial bodies 1, 2 can describe an increasing taper (convex shape) or a decreasing taper (concave shape) in the direction of flow.
  • the last two forms are not included in the drawing, as they can be easily felt. Which form is ultimately used depends on the various parameters of the combustion process. The form shown here in the drawing will preferably be used.
  • the tangential width of the inlet openings 1b, 2b is a measure that results from the offset of the two central axes 1a, 2a (see FIG. 2) with respect to one another.
  • the two conical partial bodies 1, 2 can each have a cylindrical, not shown initial part, which, analogous to the partial bodies shown, run offset from one another, so that the tangential inlet openings 1b, 2b are present over the entire length of the respective burner.
  • the burner On the burner chamber side 16, the burner has a collar-shaped plate 11, which can form, for example, the inlet front of an annular combustion chamber or a furnace.
  • the plate 11 has a number of bores or openings 12 through which dilution air, combustion air, cooling air etc. can be fed to the front part of the combustion chamber 16.
  • This feed basically serves at least two purposes: first, a medium-like component can be achieved in the combustion chamber 16, second, this feed ensures that the flame front is stabilized in the direction of a compact structure.
  • a plurality of nozzles 9, 10 act, which draw the liquid fuel 5a from a central feed channel 5, 6 assigned to each inlet opening 1b, 2b via nozzle channels 7, 8.
  • the central feed channels 5, 6 are placed upstream of the inlet openings 1b, 2b with respect to the combustion air flow 13.
  • the bridging between the feed line and the air / fuel mixing location along the inlet openings 1b, 2b is taken over by the nozzle channels 7, 8 already mentioned.
  • the number of nozzle channels 7, 8 essentially depends on the length and the power to be provided by the burner.
  • the liquid fuel is injected via the nozzles 9, 10 with a small spray cone angle in the longitudinal direction of the inlet openings 1b, 2b.
  • the nozzles on the extremities of the burner must face each other, i.e. the first nozzle at the burner inlet in the flow direction, the last nozzle at the burner mouth in the counterflow direction.
  • the nozzles in between bridge the spray cone distance in both flow directions to the neighboring nozzles.
  • the nozzles acting in both directions have the reference symbol 9
  • the nozzles acting on the extremities of the burner have the reference symbol 10.
  • the nozzles can also be slightly inclined towards the burner axis, to increase the degree of mixing .
  • the structure of the nozzles can be simple, so they can easily be simple perforated nozzles, such as those found in diesel engine technology.
  • a high-pressure atomization nozzle with a turbulence chamber is preferably provided for the optimal atomization of a liquid fuel.
  • part of the available nozzle pressure is used to generate high levels of turbulence in the fluid to be atomized.
  • Turbulence generation is achieved by means of an abrupt expansion (Carnot diffuser) into the turbulence chamber arranged in front of the actual nozzle hole.
  • the resulting liquid fuel spray is characterized by small angles of spread, corresponding to the relatively small width of the inlet openings, and very small droplet sizes.
  • the fuel is evaporated essentially only in the area of the inlet openings 1b, 2b into the interior 3 of the burner, so that only one fuel vapor enters there.
  • the liquid fuel is assigned very high pressures in the order of more than 100 bar. Furthermore, it is important that the nozzles are arranged in such a way that a uniform fuel vapor distribution is established along the inlet openings 1b, 2b and the surface of the adjacent walls is not wetted, in order to prevent the risk of coking in the course of the combustion.
  • operation with a gaseous fuel can also be provided, in which case the quality of the fuel evaporation can be achieved easily.
  • An additional central fuel nozzle 4 which is fed with a liquid and / or gaseous fuel 4a, is provided at the beginning of the burner and is intended to serve the combustion process with an amount of limit fuel, which is specified at low thermal outputs and low fuel moments, if required driving diffusion-like combustion; then this fuel supply is then completely or at least largely blocked, depending on the type of fuel.
  • This support will, however, be within a tolerance range that does not make the task-specific objectives of the subject matter impossible.
  • the air / fuel mixture 13 / 5a flowing into the interior 3 of the burner through the tangential inlet openings 1b, 2b forms, according to the geometric design of the burner, a conical mixture profile which winds in the direction of flow in a vortex.
  • the optimal, homogeneous fuel concentration is achieved over the cross-section, so there is a very uniform fuel / air mixture in the area of the backflow zone 15.
  • the ignition itself takes place at the tip of the return flow zone 15: a stable flame front 14 can only arise at this point.
  • FIG. 2 is a section through the burner along a plane in the area of the middle nozzle channel 7.
  • the combustion air 13, depending on the fuel, must be coordinated so that the fuel evaporation rate on which it is based can be achieved only in the area of the inlet openings 1b, 2b.
  • the combustion air 13 is an air / exhaust gas mixture: the recirculation of a certain amount of partially cooled exhaust gas proves to be advantageous not only when the burner is used in gas turbine groups, but also when the burner is used in atmospheric combustion plants with a near-stoichiometric driving style, ie when the ratio between the recirculated exhaust gas and fresh air supplied is approximately 0.7.
  • a fresh air temperature of, for example, 15 ° C.
  • a mixed temperature of the air / exhaust gas mixture which is now introduced instead of a pure fresh air flow, will be approximately 400 ° C.
  • these conditions lead, for example, to optimal evaporation conditions, correspondingly to a minimization of the NOx / CO / UHC emissions in the subsequent combustion process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP92102736A 1991-03-12 1992-02-19 Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux Expired - Lifetime EP0503319B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH734/91 1991-03-12
CH734/91A CH682952A5 (de) 1991-03-12 1991-03-12 Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes.

Publications (3)

Publication Number Publication Date
EP0503319A2 true EP0503319A2 (fr) 1992-09-16
EP0503319A3 EP0503319A3 (en) 1993-02-24
EP0503319B1 EP0503319B1 (fr) 1996-04-24

Family

ID=4193954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92102736A Expired - Lifetime EP0503319B1 (fr) 1991-03-12 1992-02-19 Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux

Country Status (6)

Country Link
US (1) US5244380A (fr)
EP (1) EP0503319B1 (fr)
JP (1) JPH04320711A (fr)
CA (1) CA2061746A1 (fr)
CH (1) CH682952A5 (fr)
DE (2) DE4113681A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0592717A1 (fr) * 1992-10-16 1994-04-20 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
WO1995023316A1 (fr) * 1994-02-24 1995-08-31 United Technologies Corporation Buse d'injection de carburant a entree tangentielle
DE19854382A1 (de) * 1998-11-25 2000-05-31 Asea Brown Boveri Verfahren und Vorrichtung zur Zerstäubung flüssigen Brennstoffs für eine Feuerungsanlage
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

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4330083A1 (de) * 1993-09-06 1995-03-09 Abb Research Ltd Verfahren zum Betrieb eines Vormischbrenners
DE4411623A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Vormischbrenner
DE4424599A1 (de) * 1994-07-13 1996-01-18 Abb Research Ltd Verfahren und Vorrichtung zum Betreiben eines kombinierten Brenners für flüssige und gasförmige Brennstoffe
DE4429757A1 (de) * 1994-08-22 1996-02-29 Abb Management Ag Brennkammer
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE4445279A1 (de) * 1994-12-19 1996-06-20 Abb Management Ag Einspritzdüse
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
SE514341C2 (sv) 1998-06-18 2001-02-12 Abb Ab Förfarande för start av en brännaranordning till en gasturbin
EP0981016B1 (fr) * 1998-08-19 2004-01-07 ALSTOM (Switzerland) Ltd Brûleur pour le fonctionnement d'une chambre de combustion
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
WO2003088508A2 (fr) * 2002-04-09 2003-10-23 Sapias, Inc. Plate-forme de gestion de biens
US6623267B1 (en) 2002-12-31 2003-09-23 Tibbs M. Golladay, Jr. Industrial burner
US20040202977A1 (en) * 2003-04-08 2004-10-14 Ken Walkup Low NOx burner
US20050003316A1 (en) * 2003-05-31 2005-01-06 Eugene Showers Counterflow fuel injection nozzle in a burner-boiler system
ATE479054T1 (de) * 2005-03-09 2010-09-15 Alstom Technology Ltd Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches
ATE480737T1 (de) * 2005-06-17 2010-09-15 Alstom Technology Ltd Brenner zur vormischartigen verbrennung
WO2009103671A1 (fr) * 2008-02-20 2009-08-27 Alstom Technology Ltd Turbine à gaz à architecture de refroidissement améliorée
EP2685163B1 (fr) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
DE102014205200B3 (de) * 2014-03-20 2015-06-11 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205203B3 (de) * 2014-03-20 2015-05-21 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205201A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205198A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Brenner und Vorrichtung zur thermischen Nachverbrennung von Abluft
CN106287816B (zh) * 2016-08-12 2019-01-18 中国航空工业集团公司沈阳发动机设计研究所 一种干式低排放燃烧器
CN110195864A (zh) * 2018-06-04 2019-09-03 华帝股份有限公司 一种红外燃烧器

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3890088A (en) * 1970-09-17 1975-06-17 Advanced Tech Lab Apparatus for reducing formation of oxides of nitrogen in combustion processes
US3980422A (en) * 1975-08-11 1976-09-14 Hed Industries, Inc. Oil injection means for liquid fuel burner
JPS61153404A (ja) * 1984-12-27 1986-07-12 Babcock Hitachi Kk 触媒バ−ナ
EP0321809B1 (fr) * 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0433789A1 (fr) * 1989-12-19 1991-06-26 Asea Brown Boveri Ag Procédé d'une combustion à mélange préalable d'un combustible liquide

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3834854A (en) * 1972-11-02 1974-09-10 Phillips Petroleum Co Method and apparatus for charging a burner

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3890088A (en) * 1970-09-17 1975-06-17 Advanced Tech Lab Apparatus for reducing formation of oxides of nitrogen in combustion processes
US3980422A (en) * 1975-08-11 1976-09-14 Hed Industries, Inc. Oil injection means for liquid fuel burner
JPS61153404A (ja) * 1984-12-27 1986-07-12 Babcock Hitachi Kk 触媒バ−ナ
EP0321809B1 (fr) * 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0433789A1 (fr) * 1989-12-19 1991-06-26 Asea Brown Boveri Ag Procédé d'une combustion à mélange préalable d'un combustible liquide

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 357 (M-540)2. Dezember 1986 & JP-A-61 153 404 ( BABCOCK HITACHI ) *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0592717A1 (fr) * 1992-10-16 1994-04-20 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
US5482457A (en) * 1992-10-16 1996-01-09 Asea Brown Boveri Ltd. Gas-operated premixing burner
WO1995023316A1 (fr) * 1994-02-24 1995-08-31 United Technologies Corporation Buse d'injection de carburant a entree tangentielle
DE19854382A1 (de) * 1998-11-25 2000-05-31 Asea Brown Boveri Verfahren und Vorrichtung zur Zerstäubung flüssigen Brennstoffs für eine Feuerungsanlage
US6360971B1 (en) 1998-11-25 2002-03-26 Alstom Method and appliance for atomizing liquid fuel for a firing installation
DE19854382B4 (de) * 1998-11-25 2009-01-02 Alstom Verfahren und Vorrichtung zur Zerstäubung flüssigen Brennstoffs für eine Feuerungsanlage
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

Also Published As

Publication number Publication date
US5244380A (en) 1993-09-14
EP0503319B1 (fr) 1996-04-24
CA2061746A1 (fr) 1992-09-13
JPH04320711A (ja) 1992-11-11
DE4113681A1 (de) 1992-09-17
CH682952A5 (de) 1993-12-15
DE59206081D1 (de) 1996-05-30
EP0503319A3 (en) 1993-02-24

Similar Documents

Publication Publication Date Title
EP0503319B1 (fr) Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux
EP0433790B1 (fr) Brûleur
EP0436113B1 (fr) Procédé pour le fonctionnement d'une installation de combustion
EP0902233B1 (fr) Buse de pulvérisation par pression combinée
EP0387532B1 (fr) Chambre de combustion d'une turbine à gaz
EP0401529B1 (fr) Chambre de combustion d'une turbine à gaz
EP1828684A1 (fr) Bruleur de premelange dote d'un parcours de melange
DE4326802A1 (de) Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
EP0629817A2 (fr) Foyer
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
EP0816759B1 (fr) Brûleur à prémélange et procédé de mise en oeuvre du brûleur
EP0777081A2 (fr) Brûleur à prémélange
EP0641971A2 (fr) Procédé pour commander un brûleur à prémélange
EP0711953B1 (fr) Brûleur à prémélange
EP0742411B1 (fr) Alimentation en air pour une chambre de combustion à prémélange
DE4445279A1 (de) Einspritzdüse
EP0483554B1 (fr) Procédé pour la réduction au minimum des émissions de NOx dans une combustion
DE4409918A1 (de) Brenner zum Betrieb einer Brennkammer
EP0807787B1 (fr) Brûleur
DE4242003A1 (de) Prozesswärmeerzeuger
DE4422535A1 (de) Verfahren zum Betrieb einer Feuerungsanlage
EP0730121A2 (fr) Brûleur à prémélange
EP0543155B1 (fr) Procédé pour une combustion peu polluante dans une chaudère de centrale électrique

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): CH DE FR GB IT LI NL

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): CH DE FR GB IT LI NL

17P Request for examination filed

Effective date: 19930719

17Q First examination report despatched

Effective date: 19940719

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI NL

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.SCRIBED TIME-LIMIT

Effective date: 19960424

Ref country code: NL

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: 19960424

REF Corresponds to:

Ref document number: 59206081

Country of ref document: DE

Date of ref document: 19960530

ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19960627

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Effective date: 19970228

Ref country code: LI

Effective date: 19970228

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
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: DE

Payment date: 20020207

Year of fee payment: 11

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: 20020923

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Ref country code: FR

Ref legal event code: CA

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

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

Ref country code: FR

Payment date: 20110201

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20110124

Year of fee payment: 20

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20120218

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 EXPIRATION OF PROTECTION

Effective date: 20120218