[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP1288576A2 - Gasturbinenbrennkammer - Google Patents

Gasturbinenbrennkammer Download PDF

Info

Publication number
EP1288576A2
EP1288576A2 EP02016027A EP02016027A EP1288576A2 EP 1288576 A2 EP1288576 A2 EP 1288576A2 EP 02016027 A EP02016027 A EP 02016027A EP 02016027 A EP02016027 A EP 02016027A EP 1288576 A2 EP1288576 A2 EP 1288576A2
Authority
EP
European Patent Office
Prior art keywords
combustor
cylindrical member
mixing nozzles
mixing
area
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.)
Withdrawn
Application number
EP02016027A
Other languages
English (en)
French (fr)
Other versions
EP1288576A3 (de
Inventor
Shigemi Mitsubishi Heavy Industries Ltd. Mandai
Keijirou Mitsubishi Heavy Industries Ltd Saitoh
Katsunori c/o Mitsubishi Heavy Industries Tanaka
Wataru c/o Mitsubishi Heavy Industries Akizuki
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP1288576A2 publication Critical patent/EP1288576A2/de
Publication of EP1288576A3 publication Critical patent/EP1288576A3/de
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74—Preventing flame lift-off
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • 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

  • the present invention relates to a gas turbine combustor that realizes a low NOx combustion.
  • Figs. 4(a) and (b) schematically show a prior art gas turbine combustor, wherein Fig. 4(a) is a longitudinal cross sectional view showing an interior of the combustor and Fig. 4(b) is a front view of a half portion of the combustor.
  • main fuel 40 flows into eight pre-mixing nozzles 31, that are arranged within a combustor body 36 around a central axis thereof, and is pre-mixed with air, as will be described next, to form a main pre-mixture to be supplied into a combustion zone of a combustor 33.
  • pilot fuel 41 flows into a pilot nozzle 32, that is arranged on the central axis of the combustor body 36, to be jetted into the combustor 33.
  • pilot fuel 41 burns with the main pre-mixture there to effect a combustion.
  • a flame holding cone 34 is provided on the pilot nozzle 32 and flame of the pilot fuel 41 is maintained by a high temperature gas circulating flow 35, that is formed by the flame holding cone 34.
  • the flame of the pilot nozzle 32 is maintained by a diffused flame, that is, the high temperature gas circulating flow 35, formed by the flame holding cone 34 and NOx quantity generated by the pre-mixing nozzles 31 is reduced.
  • NOx quantity generated by the diffused flame of the pilot nozzle 32 cannot be suppressed and realization of a low NOx generation as a whole is limited by that extent.
  • an object of the present invention to provide a gas turbine combustor that is constructed so as to improve a flame holding ability by the high temperature gas circulating flow as well as to improve cooling of the pre-mixing nozzles to thereby reduce pilot fuel quantity as well as to reduce NOx quantity generated of the pilot fuel.
  • the present invention provides means of the following (1) to (4):
  • the diameter of the combustion zone in which a high temperature combustion gas is generated is set such that the cross sectional area inside of the combustion zone and outside of the pitch circle, less the cross sectional area of the pre-mixing nozzles outside of the pitch circle, is a half or more of the cross sectional area of all the pre-mixing nozzles.
  • an inner circulating flow of a high temperature gas generated of the pilot fuel is formed in the central space portion of the combustion zone in front of the pilot nozzle by a flame holding cone.
  • each of the pre-mixing nozzles has its front end projected beyond the base plate so that the base plate may not be directly exposed to the high temperature gas circulating flows. Thereby, the base plate is prevented from being overheated and the effect of the means (1) of the present invention can be realized more securely.
  • each of the pre-mixing nozzles has its front portion made in the double structure having the predetermined gap therein and air is flowable in the gap for cooling the pre-mixing nozzle.
  • the pre-mixing nozzle is prevented from being overheated and the effect of the means (1) of the present invention is further ensured.
  • the combustor body as the outer casing of the combustor comprises therein the inner cylindrical member and the outer cylindrical member.
  • the outer cylindrical member has its inner diameter made larger than the outer diameter of the inner cylindrical member.
  • FIGs. 1(a) and (b) schematically show a gas turbine combustor of the embodiment, wherein Fig. 1(a) is a longitudinal cross sectional view showing an interior of the combustor and Fig. 1(b) is a front view of a half portion of the combustor.
  • numeral 10 designates a combustor body as an outer casing of the combustor and eight pre-mixing nozzles 11 are provided therein being connected to each other around a central axis of the combustor body 10.
  • the pre-mixing nozzles 11 are constructed so as to have their front ends projected beyond a base plate 17, that will be described later.
  • Numeral 12 designates a pilot nozzle, that is arranged on the central axis of the combustor body 10.
  • Numeral 13 designates a combustor, that includes the combustor body 10 and other components arranged therein.
  • the combustor body 10 comprises therein an inner cylindrical member 13a and an outer cylindrical member 13b.
  • the outer cylindrical member 13b has its inner diameter made larger than an outer diameter of the inner cylindrical member 13a as well as larger than an outer diameter of a cylindrical member of the prior art combustor.
  • the outer cylindrical member 13b is arranged surrounding a front end portion of the inner cylindrical member 13a and extending downstream of the inner cylindrical member 13a so as to cover a combustion zone of the combustor 13.
  • Numeral 14 designates a flame holding cone, that has its front end portion eliminated to be made shorter than the prior art flame holding cone.
  • Numeral 17 designates the base plate, that is a member supporting the eight pre-mixing nozzles 11 to an inner circumferential wall surface of the inner cylindrical member 13a.
  • Fig. 2 is an enlarged longitudinal cross sectional view of one of the pre-mixing nozzles 11.
  • the pre-mixing nozzle 11 has its front portion made in a double structure having a pre-mixing nozzle portion 21 of the inner side and an outer sleeve 23 of the outer side. While illustration is omitted, the outer sleeve 23 is supported to the pre-mixing nozzle portion 21 via a plurality of rib members. While the pre-mixing nozzle in the prior art has its front end cut at the position of its base plate without projecting further, the pre-mixing nozzle 11 of the present invention has its front end projected beyond the base plate 17. That is, a front end of the outer sleeve 23 projects frontward beyond the position of the base plate 17.
  • Numeral 14 designates a flame holding cone, that has its front end portion cut by the projection of the outer sleeve 23 to be made shorter.
  • Numeral 22 designates a swirler vane, construction of which is the same as that of the prior art
  • main fuel 40 flows into the eight pre-mixing nozzles 11 and is pre-mixed with air to form a pre-mixture for combustion in the combustion zone of the combustor 13.
  • the air is supplied from a compressor (not shown) to be fed into the combustor 13 flowing through an inner peripheral space portion of the combustor body 10, as shown by arrows 50 in Fig. 1(a), and further flowing through the pre-mixing nozzle portion 21 as well as through an outer peripheral space portion of the pre-mixing nozzle portion 21, as shown by arrows 51 in Fig. 2.
  • pilot fuel 41 is supplied into the combustor 13 through the pilot nozzle 12 of the combustor central position and burns there together with the pre-mixture.
  • a high temperature gas inner circulating flow 15 is generated by the pilot fuel.
  • a high temperature gas outer circulating flow 16 is generated by the pre-mixture coming from the pre-mixing nozzle 11.
  • a gas stagnation area is formed in the inner peripheral space portion of the outer cylindrical member 13b in front of the pre-mixing nozzle 11 by the construction of the combustor 13 comprising the inner cylindrical member 13a and the outer cylindrical member 13b and having the inner diameter of the outer cylindrical member 13b made larger.
  • the high temperature gas outer circulating flow 16 is formed in this gas stagnation area as a circulating flow of a high temperature combustion gas generated by combustion of the main pre-mixture.
  • the flame holding ability is greatly enhanced by the construction of the high temperature gas inner and outer circulating flows 15, 16.
  • the pilot fuel quantity as so far necessitated for the flame holding, can be reduced and thereby the NOx quantity generated of the pilot fuel can be reduced and a very low NOx combustion can be realized.
  • the pre-mixing nozzle 11 comprises the swirler vane 22, the pre-mixing nozzle portion 21 and the outer sleeve 23.
  • the outer sleeve 23 is arranged with a predetermined gap being maintained from the pre-mixing nozzle portion 21 of the inner side thereof and the air, as shown by the arrows 51, flows into the gap, so that the pre-mixing nozzle portion 21 and the outer sleeve 23 that are heated by the high temperature gas can be sufficiently cooled.
  • the front end of the pre-mixing nozzle 11, that is formed by the front end of the outer sleeve 23, projects beyond the base plate 17.
  • the base plate 17, that is directly exposed to the high temperature gas outer circulating flow 16 is prevented from being overheated.
  • L is a projecting distance of the projecting portion, that is, a distance between a front side surface of the base plate 17 and the front end of the pre-mixing nozzle 11, and D is an outer diameter of the pre-mixing nozzle 11, that is, an outer diameter of the outer sleeve 23, if L is set to D/3 or more (L ⁇ D/3), then the effect to prevent the overheat of the base plate 17 can be enhanced.
  • Fig. 3 is the same view as Fig. 1(b) in which a hatched portion is added.
  • letter P is defined as a pitch circle that is a circle on which central axes of all of the pre-mixing nozzles 11 are arranged.
  • An inner diameter of the outer cylindrical member 13b that corresponds to a diameter of the combustion zone in the combustor, is set such that, where an area is taken on a radial directional plane of the combustor, the area inside of the outer cylindrical member 13b and outside of the pitch circle P, less the area taken by the pre-mixing nozzles 11 outside of the pitch circle P, that is, the area shown by the hatched portion in Fig.
  • NOx quantity of 25 PPM in the prior art can be reduced to 10 PPM or less.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP02016027A 2001-08-24 2002-07-18 Gasturbinenbrennkammer Withdrawn EP1288576A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2001254360 2001-08-24
JP2001254360A JP2003065537A (ja) 2001-08-24 2001-08-24 ガスタービン燃焼器

Publications (2)

Publication Number Publication Date
EP1288576A2 true EP1288576A2 (de) 2003-03-05
EP1288576A3 EP1288576A3 (de) 2004-01-07

Family

ID=19082534

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02016027A Withdrawn EP1288576A3 (de) 2001-08-24 2002-07-18 Gasturbinenbrennkammer

Country Status (5)

Country Link
US (1) US20030037549A1 (de)
EP (1) EP1288576A3 (de)
JP (1) JP2003065537A (de)
CN (1) CN1172116C (de)
CA (1) CA2394118A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109611891A (zh) * 2018-12-16 2019-04-12 中国航发沈阳发动机研究所 一种干低排放燃烧器

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3986348B2 (ja) * 2001-06-29 2007-10-03 三菱重工業株式会社 ガスタービン燃焼器の燃料供給ノズルおよびガスタービン燃焼器並びにガスタービン
US7007477B2 (en) * 2004-06-03 2006-03-07 General Electric Company Premixing burner with impingement cooled centerbody and method of cooling centerbody
US7370466B2 (en) * 2004-11-09 2008-05-13 Siemens Power Generation, Inc. Extended flashback annulus in a gas turbine combustor
US7540152B2 (en) * 2006-02-27 2009-06-02 Mitsubishi Heavy Industries, Ltd. Combustor
DE102006051286A1 (de) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennervorrichtung
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US20100192582A1 (en) * 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
US8613187B2 (en) * 2009-10-23 2013-12-24 General Electric Company Fuel flexible combustor systems and methods
US8733108B2 (en) * 2010-07-09 2014-05-27 General Electric Company Combustor and combustor screech mitigation methods
US8991187B2 (en) * 2010-10-11 2015-03-31 General Electric Company Combustor with a lean pre-nozzle fuel injection system
US8826666B2 (en) * 2011-03-30 2014-09-09 Mitsubishi Heavy Industries, Ltd. Nozzle, and gas turbine combustor having the nozzle
CN102425793A (zh) * 2011-10-19 2012-04-25 中国科学院广州能源研究所 自回热型低热值燃气旋流燃烧装置
JP6002313B2 (ja) * 2012-03-29 2016-10-05 エクソンモービル アップストリーム リサーチ カンパニー ターボ機械用燃焼器組立体
US8966909B2 (en) * 2012-08-21 2015-03-03 General Electric Company System for reducing combustion dynamics
US9151502B2 (en) * 2012-08-21 2015-10-06 General Electric Company System and method for reducing modal coupling of combustion dynamics
RU2570480C2 (ru) * 2012-08-24 2015-12-10 Альстом Текнолоджи Лтд Способ смешивания разбавляющего воздуха в системе последовательного сгорания газовой турбины
JP6037736B2 (ja) * 2012-09-11 2016-12-07 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
JP5946733B2 (ja) 2012-09-24 2016-07-06 三菱日立パワーシステムズ株式会社 燃焼器の隙間計測装置及び隙間計測方法
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9765973B2 (en) * 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
JP6331662B2 (ja) * 2014-05-07 2018-05-30 三浦工業株式会社 ガスバーナ
CN105423342B (zh) * 2016-01-12 2018-08-21 西北工业大学 微型发动机燃烧室凹腔壁面蒸发管
US10415831B2 (en) * 2016-10-27 2019-09-17 General Electric Company Combustor assembly with mounted auxiliary component
CN109340750B (zh) * 2017-11-06 2019-11-12 北京东元同创能源技术有限公司 一种低氮氧化物排放的方法及实现该方法的燃气燃烧器
CN107726317A (zh) * 2017-11-29 2018-02-23 上海钜荷热力技术有限公司 一种带冷却装置的平板燃烧器
CN109654538B (zh) * 2018-12-07 2021-02-12 中国航发沈阳发动机研究所 一种利于降低火焰筒壁温的文丘里管
JP7112342B2 (ja) * 2019-01-25 2022-08-03 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
CN113739204B (zh) * 2021-08-23 2023-02-03 四川航天中天动力装备有限责任公司 一种回流燃烧室用带气动的离心回流式燃油喷嘴
CN115325569B (zh) * 2022-09-02 2023-05-26 华能国际电力股份有限公司 一种燃烧室、燃气轮机及燃烧控制方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4765146A (en) * 1985-02-26 1988-08-23 Bbc Brown, Boveri & Company, Ltd. Combustion chamber for gas turbines
EP0378505A1 (de) * 1989-01-12 1990-07-18 United Technologies Corporation Brenner und Brennstoffinjektor-Anordnung
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US5839283A (en) * 1995-12-29 1998-11-24 Abb Research Ltd. Mixing ducts for a gas-turbine annular combustion chamber
US5899074A (en) * 1994-04-08 1999-05-04 Hitachi, Ltd. Gas turbine combustor and operation method thereof for a diffussion burner and surrounding premixing burners separated by a partition
EP0952392A2 (de) * 1998-04-15 1999-10-27 Mitsubishi Heavy Industries, Ltd. Brennkammer
WO2000009945A1 (en) * 1998-08-11 2000-02-24 Asea Brown Boveri Ab Arrangement for reduction of acoustinc vibrations in a combustion chamber

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
US5836164A (en) * 1995-01-30 1998-11-17 Hitachi, Ltd. Gas turbine combustor
US6082111A (en) * 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4765146A (en) * 1985-02-26 1988-08-23 Bbc Brown, Boveri & Company, Ltd. Combustion chamber for gas turbines
EP0378505A1 (de) * 1989-01-12 1990-07-18 United Technologies Corporation Brenner und Brennstoffinjektor-Anordnung
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US5899074A (en) * 1994-04-08 1999-05-04 Hitachi, Ltd. Gas turbine combustor and operation method thereof for a diffussion burner and surrounding premixing burners separated by a partition
US5839283A (en) * 1995-12-29 1998-11-24 Abb Research Ltd. Mixing ducts for a gas-turbine annular combustion chamber
EP0952392A2 (de) * 1998-04-15 1999-10-27 Mitsubishi Heavy Industries, Ltd. Brennkammer
WO2000009945A1 (en) * 1998-08-11 2000-02-24 Asea Brown Boveri Ab Arrangement for reduction of acoustinc vibrations in a combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109611891A (zh) * 2018-12-16 2019-04-12 中国航发沈阳发动机研究所 一种干低排放燃烧器

Also Published As

Publication number Publication date
CA2394118A1 (en) 2003-02-24
US20030037549A1 (en) 2003-02-27
JP2003065537A (ja) 2003-03-05
EP1288576A3 (de) 2004-01-07
CN1403745A (zh) 2003-03-19
CN1172116C (zh) 2004-10-20

Similar Documents

Publication Publication Date Title
EP1288576A2 (de) Gasturbinenbrennkammer
US6915637B2 (en) Gas turbine combustor
US6983600B1 (en) Multi-venturi tube fuel injector for gas turbine combustors
JP5911672B2 (ja) タービンエンジン用の燃焼器ライナ
US7540153B2 (en) Combustor
JP5476462B2 (ja) マルチプレミキサ燃料ノズル
EP1288577A2 (de) Gasturbine und Brennkammer dafür
EP2873922B1 (de) Gasturbinenbrennkammer
JP2005061823A (ja) 改良型デフレクタプレートを有するガスタービンエンジンの燃焼器ドーム組立体
JP2005061822A (ja) 輪郭付きスワーラを有するガスタービンエンジンの燃焼器ドーム組立体
US7316117B2 (en) Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
JP2006300448A (ja) ガスタービンの燃焼器
JP2007232347A (ja) 燃焼器
US6742338B2 (en) Gas turbine combustor
JP2017227430A (ja) 予混合パイロットノズルおよび燃料ノズルアセンブリ
KR102512583B1 (ko) 가스 터빈의 연소기 및 이것을 구비한 가스 터빈
CN110651154B (zh) 燃烧器及具备该燃烧器的燃气涡轮
KR101820869B1 (ko) 유체 가이드를 포함한 연소기
KR101898403B1 (ko) 연소기, 가스 터빈
JP2016530478A (ja) 炎管終端領域を有する管状燃焼チャンバ及びガスタービン
US20230061373A1 (en) Combustion tube and combustor for gas turbine, and gas turbine
CA2567432C (en) Gas turbine combustor

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

17P Request for examination filed

Effective date: 20020718

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

AKX Designation fees paid

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

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20060513