EP0488556A1 - Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé - Google Patents

Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé Download PDF

Info

Publication number
EP0488556A1
EP0488556A1 EP91310554A EP91310554A EP0488556A1 EP 0488556 A1 EP0488556 A1 EP 0488556A1 EP 91310554 A EP91310554 A EP 91310554A EP 91310554 A EP91310554 A EP 91310554A EP 0488556 A1 EP0488556 A1 EP 0488556A1
Authority
EP
European Patent Office
Prior art keywords
delivery pipe
fuel
axial
diffusion
premix
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
EP91310554A
Other languages
German (de)
English (en)
Other versions
EP0488556B1 (fr
Inventor
Masayoshi Kuwata
Richard Joseph Borkowicz
Cheryl Lynn Mele
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP0488556A1 publication Critical patent/EP0488556A1/fr
Application granted granted Critical
Publication of EP0488556B1 publication Critical patent/EP0488556B1/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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • This invention relates to gas turbine combustors; and, in particular, to improvements in gas turbine combustors for the further diminishment of air pollutants such as nitrogen oxides (NOx).
  • NOx nitrogen oxides
  • the secondary or center nozzle provides the flame source for the operation of the combustor.
  • the specific configuration of the patented invention includes an annular array of primary nozzles each of which discharges into the primary combustion chamber and a central secondary nozzle which discharged into the second combustion chamber. These nozzles may all be described as diffusion nozzles in that each nozzle has an axial fuel delivery pipe and is surrounded at its discharge end by an air swirler which provides air for combustion to the fuel nozzle discharge.
  • a premix swirler is located at the boundary of the secondary flame zone and serves to stabilize and hold the flame in various operating modes.
  • This premix swirler component is, however, exposed to high flame temperatures which can impact the life of the swirler.
  • the invention as described in the above identified parent application is especially applicable to gas turbine combustors of the type which include two combustion chambers separated by a venturi throat region.
  • An annular array of primary nozzles discharge fuel into an upstream or primary combustion chamber.
  • the method of operation dictates that while under base load, the primary nozzles are flamed out whereas the single central or secondary nozzle supports combustion of premix fuel from the primary nozzles.
  • the single central or secondary nozzle which has been characterized as a diffusion nozzle, is replaced by a diffusion piloted premix nozzle which reduces the fuel flow to the central diffusion flame from approximately 20 percent of the total fuel flow to about 2 percent of the total fuel flow for the entire combustor.
  • the design thus simultaneously minimizes the percentage of total fuel flow in the combustor that burns as a diffusion flame (with high NOx emissions) but allows sufficient heat input to ignite the main premixed flow by using the pilot premixed flow (which has low NOx emissions).
  • the premix swirler component previously located at the boundary of the secondary flame zone is now relocated to a point upstream of the fuel injection point.
  • the premix swirler is made an integral part of the secondary fuel nozzle, and is located behind or upstream of the radial fuel distribution tubes.
  • the swirler will preferably comprise a series of vanes circumferentially located at some angle with respect to the axial centerline of the fuel nozzle.
  • a venturi is provided at the discharge end of the secondary premix chamber in order to assist in secondary flame stabilization.
  • a gas turbine 12 includes a compressor 14, a combustor 16 and a turbine 18 represented by a single blade. Although it is not specifically shown, it is well known that the turbine is drivingly connected to the compressor along a common axis.
  • the compressor 14 pressurizes inlet air which is then turned in direction or reverse flowed to the combustor 16 where it is used to cool the combustor and also used to provide air to the combustion process.
  • the gas turbine includes a plurality of the combustors 16 (one shown) which are located about the periphery of the gas turbine. In one particular gas turbine model there are fourteen such combustors.
  • a transition duct 20 connects the outlet end 18 of its particular combustor with the inlet end of the turbine to deliver the hot products of the combustion process to the turbine.
  • each combustor 16 comprises a primary or upstream combustion chamber 24 and a second or downstream combustion chamber 26 separated by a venturi throat region 28.
  • the combustor 16 is surrounded by a combustor flow sleeve 30 which channels compressor discharge air flow to the combustor.
  • the combustor is further surrounded by an outer casing 31 ( Figure 1) which is bolted to the turbine casing 32.
  • Primary nozzles 36 provide fuel delivery to the upstream combustor 24 and are arranged in an annular array around a central secondary nozzle 38.
  • each combustor may include six primary nozzles and one secondary nozzle.
  • fuel is delivered to the nozzles through plumbing 42 in a manner well known in the art and fully described in the aforementioned patent. Ignition in the primary combustor is caused by spark plug 48 shown in Figure 1 and in adjacent combustors by means of crossfire tubes 50 also well known in the art.
  • a diffusion nozzle 36 includes a fuel delivery nozzle 54 and an annular swirler 56.
  • the nozzle 54 delivers only fuel which is then subsequently mixed with swirler air for combustion.
  • the secondary nozzle is also a diffusion nozzle as will be explained further.
  • the dual stage, dual mode combustor is designed to operate in a premix mode such that all of the primary nozzles 36 are simply mixing fuel and air to be ignited by the diffusion flame supported by the secondary or central diffusion nozzle 38.
  • This premixing of the primary nozzle fuel and ignition by the secondary diffusion nozzle led to a lower NOx output in the combustor.
  • the inventors in parent application 07/501,439 discovered that a satisfactory pilot flame for the main premix flow from the upstream premix (primary) nozzles 36 may be sustained by using a minimal diffusion pilot in combination with a central nozzle premix chamber.
  • the invention simultaneously minimizes the percentage of total fuel in the combustor that burns as a diffusion flame (with high NOx emissions) while allowing sufficient heat input to ignite the main premixed flow by using the premixed secondary or pilot flow.
  • the nozzle also referred to as a secondary nozzle, includes a diffusion pilot 62 having a fuel delivery pipe 64.
  • the fuel delivery pipe includes an axial pipe portion 66 and a plurality of radial, blind ended fuel distribution tubes 68 which extend radially outwardly from the axial pipe portion. In the preferred embodiment, there are six such fuel distribution tubes.
  • the fuel distribution tubes each include a plurality of fuel discharge holes or orifices 70 which direct fuel downstream toward the discharge end of the combined nozzle.
  • the fuel distribution holes are sized so as to obtain the desired percentage of fuel flow into the premix chamber to be hereinafter described.
  • the diffusion pilot 62 further includes an air delivery pipe 74 coaxial with and surrounding the fuel delivery axial pipe portion 66.
  • the air input into the air delivery pipe 74 is compressor discharge air which is reverse flowed around the combustor 16 into the volume 76 ( Figures 1 and 2) defined by the flow sleeve 30 and the combustion chamber liner 78.
  • the diffusion pilot 62 includes at its discharge end a first or diffusion pilot swirler 82 for the purpose of directing air delivery pipe discharge air to the diffusion pilot flame.
  • a premix chamber 84 is defined by a sleeve-like truncated cone 85 which surrounds the diffusion pilot 62 and includes a discharge end (see flow arrows) terminating adjacent the diffusion pilot discharge end. Compressor discharge air is also reverse flowed into the premix chamber 84 from volume 76 in a manner similar to the manner in which air is supplied to the air delivery pipe 74.
  • the plurality of radial fuel distribution tubes 68 extend through the air delivery pipe 74 and into the premix chamber 84 such that the fuel and air are mixed and delivered to a second or premix chamber swirler annulus 86 between the diffusion pilot 62 and the premix chamber truncated cone 85.
  • a third or central nozzle swirler 90 is located downstream from the discharge end of the secondary nozzle 100 between an extension or cup 92 on the discharge end of the pilot and the centerbody wall 95 of the primary combustion chamber. Compressor air is also reverse flowed to this swirler from the volume 76 surrounding the combustion liners. The purpose of this third swirler 90 is to provide stability for the diffusion and premix nozzle flame when combining with the primary premix flow from the primary combustor.
  • the required design of the first, second and third swirlers 82, 86 and 90, respectively, would be known to practitioners in the combustion art, and therefore requires no further description.
  • the truncated cone 85 which defines the premix chamber 84, is formed of any metal suitable to use within a gas turbine environment.
  • the diffusion piloted premix nozzle includes a diffusion pilot 104 having a fuel delivery pipe 106.
  • the fuel delivery pipe has an axial pipe portion 108 and a plurality of radial fuel distribution tubes 110 which extend radially outwardly from the axial pipe portion 108 and which are closed at their outermost ends.
  • a preferred arrangement includes six such fuel distribution tubes.
  • Each tube 108 also includes a plurality of fuel discharge holes or orifices 112 which direct fuel downstream toward the discharge end of the secondary nozzle.
  • the distribution holes 112 are sized so as to obtain the desired percentage of fuel flow into the premix chamber as described below.
  • the diffusion pilot 104 further includes an air delivery pipe 114 coaxial with and surrounding the fuel delivery pipe 106.
  • the air input into the air delivery pipe 114 is compressor discharge air which is reverse flowed around the combustor as described above in connection with the embodiment illustrated in Figure 3.
  • the diffusion pilot 104 includes at its discharge end a first swirler annulus 116 for directing discharge air from the air delivery pipe into the diffusion pilot flame.
  • a premix chamber 118 is defined by a sleeve 120 which surrounds the diffusion pilot 104 and includes a discharge end 119 terminating adjacent the diffusion pilot discharge end, i.e., adjacent the first swirler 116. Compressor discharge air is also reverse flowed into the premix chamber 118 as described hereinabove.
  • the plurality of radial fuel distribution tubes 110 extend through the air delivery pipe 114 and into the premix chamber. However, in this embodiment, the second swirler annulus 122 is located upstream of the radial fuel distribution tubes 110. By so locating the swirler 122, it is at no time subjected to direct flame contact thereby extending the life of the swirler, while retaining the function of the previously described swirler 86.
  • the air flow is substantially similar to that described in the Figure 3 embodiment in that the same degree of swirling of air and fuel is achieved so as to preserve the flame stability, but the danger of heat damage to the second swirler 122 is minimized.
  • the flame characteristics are identical to the flame characteristics in the previously described embodiment, the result should be an identical or similar performance in premixed combustion as a whole.
  • the second swirler 122 will be an integral part of the secondary fuel nozzle 102, and the swirler will consist of a series of vanes circumferentially located at some angle with respect to the axial center line of the fuel nozzle as will be understood by those of ordinary skill in the art.
  • the vanes may be cast as part of the nozzle or made separately and mechanically attached via welding or brazing to the nozzle.
  • the vanes may be aerodynamic or non-aerodynamic so as to result in an aerodynamic flow or a separated flow from the vanes. While it is presently preferred to utilize a non-aerodynamic scheme, aerodynamic vanes may be utilized as well.
  • a diffusion piloted premix nozzle is disclosed which is identical to that illustrated in Figure 4 but with the addition of a venturi component 124 located at the end of the secondary premixing chamber.
  • the venturi is not an integral part of the secondary fuel nozzle.
  • the venturi 124 will supplement the swirl imparted by the upstream swirler 122 with a recirculating flow which will tend to enhance stabilization of the intense swirling flow.
  • the foregoing invention as described produces less NOx while providing an opportunity to add to the fuel flow through the secondary nozzle because of the lower NOx output whereas the turn down ratio or the ability to operate under varying conditions is considerably widened because the diffusion pilot is subject to the premix flow of the pilot rather than the total overall premix flow from the surrounding primary nozzles.
  • the service life of the premix swirler previously located at the discharge end of the premix chamber has been enhanced by relocation upstream of the fuel injection orifices of the diffusion pilot.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP19910310554 1990-11-27 1991-11-15 Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé Expired - Lifetime EP0488556B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US61824690A 1990-11-27 1990-11-27
US618246 1990-11-27

Publications (2)

Publication Number Publication Date
EP0488556A1 true EP0488556A1 (fr) 1992-06-03
EP0488556B1 EP0488556B1 (fr) 1997-07-16

Family

ID=24476921

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19910310554 Expired - Lifetime EP0488556B1 (fr) 1990-11-27 1991-11-15 Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé

Country Status (5)

Country Link
EP (1) EP0488556B1 (fr)
JP (1) JP2651304B2 (fr)
DE (1) DE69126846T2 (fr)
NO (1) NO300240B1 (fr)
RU (1) RU2076276C1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564184A1 (fr) * 1992-03-30 1993-10-06 General Electric Company Brûleur simple effet à deux modes d'opération
WO1994000718A1 (fr) * 1992-06-25 1994-01-06 Solar Turbines Incorporated Buse de combustion pour diminuer les emissions polluantes d'une turbine a gaz
FR2706588A1 (fr) * 1993-06-16 1994-12-23 Snecma Système d'injection de carburant pour chambre de combustion.
EP0800041A2 (fr) * 1996-04-03 1997-10-08 ROLLS-ROYCE plc Chambre de combusion de turbine à gaz
WO1998025084A1 (fr) * 1996-12-04 1998-06-11 Siemens Westinghouse Power Corporation VEILLEUSE DE DIFFUSION A PREMELANGE POUR BRULEUR A FAIBLE DEGAGEMENT DE NOx
EP1193448A2 (fr) * 2000-09-29 2002-04-03 General Electric Company Ensemble de vrilles d'une chambre de combustion annulaire comprenant un atomiseur pilote
EP1239219A1 (fr) * 1999-12-15 2002-09-11 Osaka Gas Co., Ltd. Distributeur de fluide, dispositif a bruleur, moteur de turbine a gaz, et systeme cogenerateur
EP1400754A1 (fr) * 2002-09-23 2004-03-24 Siemens Westinghouse Power Corporation Brûleur pilote à prémélange pour une turbine à gaz
DE102008026459A1 (de) * 2008-06-03 2009-12-10 E.On Ruhrgas Ag Brenner, insbesondere für eine Verbrennungseinrichtung in einer Gasturbinenanlage
CN102052682A (zh) * 2009-11-06 2011-05-11 通用电气公司 次燃料喷嘴文丘里管

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002031343A (ja) 2000-07-13 2002-01-31 Mitsubishi Heavy Ind Ltd 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン
US7284378B2 (en) 2004-06-04 2007-10-23 General Electric Company Methods and apparatus for low emission gas turbine energy generation
US7757491B2 (en) * 2008-05-09 2010-07-20 General Electric Company Fuel nozzle for a gas turbine engine and method for fabricating the same
US8240150B2 (en) * 2008-08-08 2012-08-14 General Electric Company Lean direct injection diffusion tip and related method
US20100192582A1 (en) * 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
US20140318139A1 (en) * 2013-04-25 2014-10-30 Khalid Oumejjoud Premixer assembly for gas turbine combustor
JP6945468B2 (ja) * 2018-02-06 2021-10-06 三菱パワー株式会社 ガスタービン燃焼器、ガスタービン及びガスタービン燃焼器の制御方法
RU2765667C2 (ru) * 2019-12-30 2022-02-01 Публичное акционерное общество "ОДК-Кузнецов" (ПАО "ОДК-Кузнецов") Устройство перепуска воздуха и газотурбинный двигатель, содержащий устройство перепуска воздуха

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899881A (en) * 1974-02-04 1975-08-19 Gen Motors Corp Combustion apparatus with secondary air to vaporization chamber and concurrent variance of secondary air and dilution air in a reverse sense
EP0108361A1 (fr) * 1982-11-08 1984-05-16 Kraftwerk Union Aktiengesellschaft Brûleur de prémélange avec brûleur à diffusion intégré
EP0269824A2 (fr) * 1986-11-25 1988-06-08 General Electric Company Brûleur combiné à diffusion et à prémélange pour veilleuse

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH076630B2 (ja) * 1988-01-08 1995-01-30 株式会社日立製作所 ガスタービン燃焼器
JP2865684B2 (ja) * 1989-01-06 1999-03-08 株式会社日立製作所 ガスタービン燃焼器

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899881A (en) * 1974-02-04 1975-08-19 Gen Motors Corp Combustion apparatus with secondary air to vaporization chamber and concurrent variance of secondary air and dilution air in a reverse sense
EP0108361A1 (fr) * 1982-11-08 1984-05-16 Kraftwerk Union Aktiengesellschaft Brûleur de prémélange avec brûleur à diffusion intégré
EP0269824A2 (fr) * 1986-11-25 1988-06-08 General Electric Company Brûleur combiné à diffusion et à prémélange pour veilleuse

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564184A1 (fr) * 1992-03-30 1993-10-06 General Electric Company Brûleur simple effet à deux modes d'opération
WO1994000718A1 (fr) * 1992-06-25 1994-01-06 Solar Turbines Incorporated Buse de combustion pour diminuer les emissions polluantes d'une turbine a gaz
FR2706588A1 (fr) * 1993-06-16 1994-12-23 Snecma Système d'injection de carburant pour chambre de combustion.
US5437159A (en) * 1993-06-16 1995-08-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Fuel injection system for a gas turbine combustor including radial fuel spray arms and V-gutter flameholders
EP0800041A3 (fr) * 1996-04-03 2000-06-14 ROLLS-ROYCE plc Chambre de combusion de turbine à gaz
EP0800041A2 (fr) * 1996-04-03 1997-10-08 ROLLS-ROYCE plc Chambre de combusion de turbine à gaz
WO1998025084A1 (fr) * 1996-12-04 1998-06-11 Siemens Westinghouse Power Corporation VEILLEUSE DE DIFFUSION A PREMELANGE POUR BRULEUR A FAIBLE DEGAGEMENT DE NOx
US6832483B2 (en) 1999-12-15 2004-12-21 Osaka, Gas Co., Ltd. Fluid distributor, burner apparatus, gas turbine engine and co-generation system
US6951097B2 (en) 1999-12-15 2005-10-04 Osaka Gas Co., Ltd. Fluid distributor, burner apparatus, gas turbine engine and co-generation system
EP1239219A1 (fr) * 1999-12-15 2002-09-11 Osaka Gas Co., Ltd. Distributeur de fluide, dispositif a bruleur, moteur de turbine a gaz, et systeme cogenerateur
EP1239219A4 (fr) * 1999-12-15 2003-03-12 Osaka Gas Co Ltd Distributeur de fluide, dispositif a bruleur, moteur de turbine a gaz, et systeme cogenerateur
US6684641B2 (en) 1999-12-15 2004-02-03 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6854258B2 (en) 1999-12-15 2005-02-15 Osaka Gas Co., Ltd. Fluid distributor, burner apparatus, gas turbine engine and co-generation system
US6829897B2 (en) 1999-12-15 2004-12-14 Osaka Gas Co., Ltd. Fluid distributor, burner apparatus, gas turbine engine and co-generation system
EP1193448A3 (fr) * 2000-09-29 2003-05-28 General Electric Company Ensemble de vrilles d'une chambre de combustion annulaire comprenant un atomiseur pilote
EP1193448A2 (fr) * 2000-09-29 2002-04-03 General Electric Company Ensemble de vrilles d'une chambre de combustion annulaire comprenant un atomiseur pilote
US6848260B2 (en) 2002-09-23 2005-02-01 Siemens Westinghouse Power Corporation Premixed pilot burner for a combustion turbine engine
EP1400754A1 (fr) * 2002-09-23 2004-03-24 Siemens Westinghouse Power Corporation Brûleur pilote à prémélange pour une turbine à gaz
DE102008026459A1 (de) * 2008-06-03 2009-12-10 E.On Ruhrgas Ag Brenner, insbesondere für eine Verbrennungseinrichtung in einer Gasturbinenanlage
CN102052682A (zh) * 2009-11-06 2011-05-11 通用电气公司 次燃料喷嘴文丘里管

Also Published As

Publication number Publication date
NO914632D0 (no) 1991-11-26
NO300240B1 (no) 1997-04-28
NO914632L (no) 1992-05-29
JPH04283316A (ja) 1992-10-08
DE69126846D1 (de) 1997-08-21
EP0488556B1 (fr) 1997-07-16
JP2651304B2 (ja) 1997-09-10
RU2076276C1 (ru) 1997-03-27
DE69126846T2 (de) 1998-02-12

Similar Documents

Publication Publication Date Title
US5193346A (en) Premixed secondary fuel nozzle with integral swirler
US4982570A (en) Premixed pilot nozzle for dry low Nox combustor
JP5400936B2 (ja) ガスタービンエンジン内で燃料を燃焼させるための方法及び装置
EP0602901B1 (fr) Système d'injection de combustible tertiaire pour brûleur à faible production de NOx
KR100247097B1 (ko) 가스터어빈용 이중방식 연소기
US7185494B2 (en) Reduced center burner in multi-burner combustor and method for operating the combustor
EP0550218B1 (fr) Chambre de combustion pour turbine à gaz
EP0269824B1 (fr) Brûleur combiné à diffusion et à prémélange pour veilleuse
US5685139A (en) Diffusion-premix nozzle for a gas turbine combustor and related method
EP0488556B1 (fr) Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé
US8959921B2 (en) Flame tolerant secondary fuel nozzle
US5729968A (en) Center burner in a multi-burner combustor
US5199265A (en) Two stage (premixed/diffusion) gas only secondary fuel nozzle
US8171735B2 (en) Mixer assembly for gas turbine engine combustor
EP1106928A1 (fr) Configuration d'un système d'alimentation et méthode d'alimentation étagée en carburant pour turbines à gaz utilisant à la fois des carburants gazeux et liquides
JP2849348B2 (ja) 燃焼器のバーナ
CN110440287A (zh) 一种流量调节套筒

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: A1

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

17P Request for examination filed

Effective date: 19921123

17Q First examination report despatched

Effective date: 19940427

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): 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: 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: 19970716

ET Fr: translation filed
REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: CH

Ref legal event code: NV

Representative=s name: RITSCHER & SEIFERT PATENTANWAELTE VSP

REF Corresponds to:

Ref document number: 69126846

Country of ref document: DE

Date of ref document: 19970821

ITF It: translation for a ep patent filed

Owner name: SAIC BREVETTI S.R.L.

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
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: 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: FR

Payment date: 20101202

Year of fee payment: 20

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

Ref country code: CH

Payment date: 20101124

Year of fee payment: 20

Ref country code: DE

Payment date: 20101126

Year of fee payment: 20

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

Ref country code: IT

Payment date: 20101124

Year of fee payment: 20

Ref country code: GB

Payment date: 20101124

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69126846

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69126846

Country of ref document: DE

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: PE20

Expiry date: 20111114

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: 20111114

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 EXPIRATION OF PROTECTION

Effective date: 20111116