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EP1534997B1 - Brûleur d'une turbine à gaz - Google Patents

Brûleur d'une turbine à gaz Download PDF

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Publication number
EP1534997B1
EP1534997B1 EP03794901.3A EP03794901A EP1534997B1 EP 1534997 B1 EP1534997 B1 EP 1534997B1 EP 03794901 A EP03794901 A EP 03794901A EP 1534997 B1 EP1534997 B1 EP 1534997B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
swirl blade
channel
radial direction
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.)
Expired - Lifetime
Application number
EP03794901.3A
Other languages
German (de)
English (en)
Other versions
EP1534997A2 (fr
Inventor
Peter Berenbrink
Malte Blomeyer
Werner Krebs
Bernd Prade
Holger Streb
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP03794901.3A priority Critical patent/EP1534997B1/fr
Publication of EP1534997A2 publication Critical patent/EP1534997A2/fr
Application granted granted Critical
Publication of EP1534997B1 publication Critical patent/EP1534997B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a burner according to the preamble of claim 1.
  • Such combustion instabilities can be actively suppressed, for example by increasing the power of the pilot flame, or passively, for example by resonators.
  • the EP 0 870 989 discloses differently sized fuel outlets for stabilizing the flame at low load conditions, with the openings being smallest in an upstream region.
  • the EP 1 207 350 discloses for magnification of the operating range of a combustion chamber, the injection of differently controlled fuel / air mixture jets into different target spaces within a mixing zone.
  • the DE 199 48 673 discloses a method for preventing thermoacoustic combustion instabilities, in which regions of different average flow velocity are generated in the gas flow and the fuel is injected into these regions.
  • the EP 0 672 865 describes a fuel nozzle for diffusion and premixing operation.
  • the US 6,092,363 discloses a low NOx burner suitable for operation with various fuels.
  • the burner includes concentrically arranged cylindrical passages with annular fuel nozzle channels at the respective upstream end.
  • the US 5,511,375 shows a device for mixing fuel with air for a gas turbine combustor, in which extending for the radial fuel distribution through the hollow blades of a diagonal grid fuel passages.
  • FIG. 1 shows a burner 1, in particular a premix burner 1, in particular for a gas turbine.
  • the burner 1 has a burner longitudinal axis 46. Along the burner longitudinal axis 46, for example, a diffusion or pilot burner 43 is arranged centrally. In the pre-mixing operation, the pilot burner 43 is operated to support the burner 1.
  • a Vormisch zone 10 and / or a combustion chamber 19 is supplied to the longitudinal axis 46 .
  • oxygen or other gas can be supplied, which results in the fuel 7, a combustible fuel-gas mixture.
  • air 4 is first supplied to the duct 13 and then the fuel 7.
  • the air 4 flows in the channel 13, for example, past at least one swirl blade 16, the swirl blade 16, for example, supplying fuel 7 to the channel 13.
  • the swirl vanes 16 are, for example, annular, in particular equidistant, arranged around the burner longitudinal axis 46 (FIG. Fig. 6 ).
  • the air 4 and the fuel 7 mix in the premix 10, which is indicated by dashed lines.
  • FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13th
  • the fuel 7 is supplied to the channel 13 via at least two fuel nozzles 31 and flows there in a flow direction 88.
  • the fuel supply via fuel nozzles 31, which are arranged in the swirl vane 16.
  • the fuel 7 can also be supplied to the channel 13 via other distribution units.
  • the combustion instabilities result from a distribution of the fuel concentration 58 according to the prior art.
  • concentration of the fuel is approximately equal.
  • the operating range is extended according to the invention, in that an outflow angle ⁇ of a medium, ie the angle between resulting speed and peripheral speed ( Fig. 5 ), for example of the air / fuel mixture 7, in a radial direction 55 from a maximum value to a minimum Value decreases from the inside out. This is done by a twist of the swirl blade 16 as in FIG. 4 described.
  • the outflow angle ⁇ is also the angle between the flow direction of the medium flowing in the channel (air, oxygen, fuel, mixtures thereof) and a plane whose normal is the burner longitudinal axis 46.
  • an additional fuel concentration distribution 52 which is not constant in the radial direction 55 at least at a point in time during the operation of the burner 1, the intensity of the combustion oscillations is reduced. In this way, the operating range for the burner 1 can be extended.
  • the fuel concentration changes, for example, in the radial direction 55 as viewed from the center, i. from the burner longitudinal axis 46, to the outside, in particular, the fuel concentration, for example, decreases linearly or to.
  • FIG. 3 shows a swirl blade 16, with which this can be realized.
  • FIG. 3 shows a swirl blade 16 for a burner.
  • the swirl blade 16 has a leading edge 67 and a trailing edge 70.
  • the medium flows in the flow direction 88 first past the leading edge 67 and then past the trailing edge 70.
  • a core 73 is present, in which a feed 64 for fuel 7 is present.
  • the feeder 64 is, for example, a blind hole.
  • 64 holes are present in the supply, which constitute the fuel nozzles 31. Through these fuel nozzles 31, the fuel 7 enters the channel 13.
  • the diameter of the holes of the fuel nozzles 31 of the built-in burner swirl blade 1 change in the radial direction 55 according to the concentration distribution 52 and takes, for example. In the radial direction 55 seen from the inside outwards.
  • the medium which flows past the swirl blade 16, experiences an outflow angle ⁇ .
  • FIG. 4 shows a swirl blade 16 for a burner 1 according to the invention.
  • the swirl blade 16 is, for example, with respect to the size and distribution of the fuel nozzles 31 as the swirl blade in FIG. 3 educated.
  • the airfoil 61 is still wound around a winding axis 76.
  • the winding axis 76 forms with the flow direction 88 a non-zero cutting angle and is in particular at 90 °.
  • a gas or a fuel-air mixture which flows at the swirl blade 16 from the leading edge 67 to the outflow edge 70, experiences in the radial direction 55 different outflow angles ⁇ , i.
  • a different outflow angle ⁇ 1 is generated than at the other end, an outflow angle ⁇ 2 (not equal to ⁇ 1), viewed in the direction of a longitudinal axis of the feed 64.
  • the outflow angle ⁇ decreases linearly. There may also be a non-linear increase or decrease.
  • This distribution in the radial direction 55 of the outflow angle ⁇ also suppresses combustion instabilities, so that the operating range for the burner 1 is widened.
  • the flowing medium forms at the swirl blade 16 with the flow direction 88 in the channel 13 the outflow angle ⁇ .
  • the swirl blade 16 is wound according to the invention and may also have different diameters for the fuel nozzles.
  • FIG. 5 shows the arrangement of the various flow vectors of the gas flowing in the channel 13.
  • the vector 79 represents the meridional velocity component.
  • the vector 82 represents the peripheral velocity, resulting in a resulting velocity sector 85.
  • the angle between the resulting speed 85 and the peripheral speed 82 represents the outflow angle ⁇ .
  • the angle 90 ° - ⁇ is the complementary angle.
  • the outflow angle ⁇ is also the angle between the flow direction of the flowing medium and a plane which is perpendicular to the burner longitudinal axis 46.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Air Supply (AREA)

Claims (8)

  1. Brûleur (1),
    auquel on apporte de l'air et/ou de l'oxygène (4),
    qui s'écoule dans un sens (88) d'écoulement,
    le brûleur (1) ayant un canal (13), dans lequel s'écoule un fluide, au moins une pale (16) de tourbillonnement étant disposée dans le canal (13), la pale (16) de tourbillonnement ayant une lame (61), qui est tordue autour d'un axe (76) de torsion, de manière à ce que le gaz, passant sur la pale (16) de tourbillonnement, dans le sens (88) d'écoulement, ait le long d'un bord de la lame (61) de la pale, qui a, avec le sens (88) d'écoulement, un angle d'intersection différent de zéro,
    des angles (α) de sortie différents, de manière à ce que l'air et/ou l'oxygène (4) aient, dans un plan perpendiculaire au sens (88) d'écoulement, une répartition d'un angle de sortie et la répartition de l'angle de sortie n'est pas constante pour empêcher des instabilités de combustion, lorsque le brûleur (1) fonctionne, le brûleur (1) ayant un axe (46) longitudinal, qui représente la partie intérieure du brûleur (1),
    le brûleur (1) ayant une direction (55) radiale, disposée perpendiculairement à l'axe (46) longitudinal du brûleur,
    dans lequel l'angle (α) de sortie, entre son sens (88) d'écoulement et un plan perpendiculaire à l'axe (46) longitudinal du brûleur d'un gaz passant sur une pale (16) de tourbillonnement, a, dans la direction (55) radiale, sur la pale (16) de tourbillonnement, des angles (α) de sortie différents, caractérisé en ce que l'angle (α) de sortie diminue dans la direction (55) radiale de l'intérieur à l'extérieur.
  2. Brûleur suivant la revendication 1,
    caractérisé en ce que le combustible (7) peut être apporté au canal (13), par au moins une buse (31) à combustible dans la pale (16) de tourbillonnement, en ce que la pale (16) de tourbillonnement a des buses (31) à combustible de diamètres différents, de manière à ce que la répartition (52) de concentration du combustible (7) ne soit pas constante et se modifie dans la direction (55) radiale.
  3. Brûleur suivant la revendication 2,
    caractérisé en ce que le diamètre des buses (31) à combustible de la pale (16) de tourbillonnement montée diminue dans la direction (55) radiale de l'intérieur vers l'extérieur, de sorte que la répartition (52) de concentration du combustible (7) diminue de l'intérieur vers l'extérieur.
  4. Brûleur suivant la revendication 1,
    caractérisé en ce que le combustible (7) ou l'air ou l'oxygène (4) peut être apporté au canal (13) et
    le canal (13) est constitué de manière annulaire autour de l'axe (46) longitudinal du brûleur.
  5. Brûleur suivant la revendication 4,
    caractérisé en ce qu'un mélange de combustible et de gaz s'écoule dans le canal (13).
  6. Brûleur suivant la revendication 1,
    caractérisé en ce que le brûleur (1) est un brûleur de turbine à gaz.
  7. Brûleur suivant la revendication 1,
    caractérisé en ce que le brûleur (1) a un brûleur (43) de diffusion ou pilote.
  8. Brûleur suivant la revendication 1,
    caractérisé en ce que le brûleur (1) est un brûleur de mélange préalable.
EP03794901.3A 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz Expired - Lifetime EP1534997B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03794901.3A EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02019530 2002-09-02
EP02019530A EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur
PCT/EP2003/009222 WO2004025183A2 (fr) 2002-09-02 2003-08-20 Bruleur
EP03794901.3A EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1534997A2 EP1534997A2 (fr) 2005-06-01
EP1534997B1 true EP1534997B1 (fr) 2015-07-29

Family

ID=31197882

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur
EP03794901.3A Expired - Lifetime EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur

Country Status (6)

Country Link
US (1) US7753677B2 (fr)
EP (2) EP1394471A1 (fr)
JP (2) JP4369370B2 (fr)
CN (1) CN100432531C (fr)
ES (1) ES2550096T3 (fr)
WO (1) WO2004025183A2 (fr)

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004059882A1 (de) * 2004-12-10 2006-06-22 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner mit integriertem Stützbrenner
JP4476176B2 (ja) * 2005-06-06 2010-06-09 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
US20070269755A2 (en) * 2006-01-05 2007-11-22 Petro-Chem Development Co., Inc. Systems, apparatus and method for flameless combustion absent catalyst or high temperature oxidants
US20080078182A1 (en) * 2006-09-29 2008-04-03 Andrei Tristan Evulet Premixing device, gas turbines comprising the premixing device, and methods of use
KR100820233B1 (ko) * 2006-10-31 2008-04-08 한국전력공사 연소기 및 이를 포함하는 멀티 연소기, 그리고 연소방법
EP1992878A1 (fr) * 2007-05-18 2008-11-19 Siemens Aktiengesellschaft Distributeur de combustible
US9016601B2 (en) 2007-05-18 2015-04-28 Siemens Aktiengesellschaft Fuel distributor
EP2042807A1 (fr) * 2007-09-25 2009-04-01 Siemens Aktiengesellschaft Etage de prémélange pour brûleur de turbine à gaz
JP5172468B2 (ja) * 2008-05-23 2013-03-27 川崎重工業株式会社 燃焼装置および燃焼装置の制御方法
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
KR101049359B1 (ko) * 2008-10-31 2011-07-13 한국전력공사 삼중 스월형 가스터빈 연소기
US20100180599A1 (en) * 2009-01-21 2010-07-22 Thomas Stephen R Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle
IT1393555B1 (it) * 2009-04-07 2012-04-27 Ansaldo Energia Spa Impianto a turbina a gas e metodo per operare detto impianto a turbina a gas
EP2270398A1 (fr) * 2009-06-30 2011-01-05 Siemens Aktiengesellschaft Brûleur notamment pour turbines à gaz
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
DE102009038848A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
CA2773951A1 (fr) * 2009-09-13 2011-03-17 Lean Flame, Inc. Agencements de cavites de combustion pour etagement de combustible dans des chambres de combustion a tourbillon piege
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
US9163841B2 (en) * 2011-09-23 2015-10-20 Siemens Aktiengesellschaft Cast manifold for dry low NOx gas turbine engine
CN104471317B (zh) * 2012-08-06 2016-09-07 西门子公司 在带有具有在外部区域内交叉的叶片端部的旋流生成器的燃烧器内的空气和燃料混合的局部改进
EP2728260A1 (fr) * 2012-11-06 2014-05-07 Alstom Technology Ltd Dispositif de tourbillonnement axial
US20150316266A1 (en) 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
EP2966350B1 (fr) * 2014-07-10 2018-06-13 Ansaldo Energia Switzerland AG Dispositif de tourbillonnement axial
CN107514636B (zh) * 2017-10-10 2023-09-08 安徽科达洁能股份有限公司 一种悬浮焙烧炉用烧嘴及其应用
DE102018205874A1 (de) * 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
PT3794283T (pt) * 2018-05-15 2024-04-11 Air Prod & Chem Sistema e procedimento para melhoramento da estabilidade de combustão numa turbina a gás
US11976830B2 (en) 2019-01-22 2024-05-07 Mitsubishi Electric Corporation Air-conditioning apparatus
EA039073B1 (ru) * 2020-09-07 2021-11-30 Некоммерческое Акционерное Общество "Алматинский Университет Энергетики И Связи Имени Гумарбека Даукеева" Двухъярусная горелка
US12454909B2 (en) 2021-12-03 2025-10-28 General Electric Company Combustor size rating for a gas turbine engine using hydrogen fuel
US12331932B2 (en) * 2022-01-31 2025-06-17 General Electric Company Turbine engine fuel mixer

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1126654A (en) * 1915-01-26 Babcock & Wilcox Co Apparatus for burning finely-divided fuel.
US746525A (en) * 1902-11-21 1903-12-08 Peter M Kling Hydrocarbon-burner.
US1086715A (en) * 1911-07-03 1914-02-10 Babcock & Wilcox Co Apparatus for burning finely-divided fuel.
US1102510A (en) * 1911-07-15 1914-07-07 Babcock & Wilcox Co Apparatus for burning finely-divided fuel.
JPS6099933A (ja) * 1983-11-04 1985-06-03 Mitsubishi Heavy Ind Ltd スワラの製作方法
DE3446211A1 (de) * 1984-12-19 1986-07-03 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen Zahnradgetriebe
JPH0780216B2 (ja) * 1987-08-13 1995-08-30 東芝機械株式会社 樹脂材料の焼け，分解防止方法
JPH0647954B2 (ja) * 1988-09-07 1994-06-22 株式会社日立製作所 ガスタービンの予混合器
CH687347A5 (de) * 1993-04-08 1996-11-15 Abb Management Ag Wärmeerzeuger.
US5435126A (en) 1994-03-14 1995-07-25 General Electric Company Fuel nozzle for a turbine having dual capability for diffusion and premix combustion and methods of operation
JPH07332621A (ja) 1994-06-13 1995-12-22 Hitachi Ltd ガスタービン燃焼器用旋回バーナ
US5511375A (en) 1994-09-12 1996-04-30 General Electric Company Dual fuel mixer for gas turbine combustor
JPH08158892A (ja) * 1994-12-02 1996-06-18 Ishikawajima Harima Heavy Ind Co Ltd ガスタービン用燃料噴射弁
DE19640818B4 (de) * 1996-10-02 2006-04-27 Siemens Ag Vorrichtung und Verfahren zur Verbrennung eines Brennstoffs in Luft
WO1998011383A2 (fr) * 1996-09-09 1998-03-19 Siemens Aktiengesellschaft Dispositif et procede pour la combustion d'un combustible dans l'air
GB2324147B (en) * 1997-04-10 2001-09-05 Europ Gas Turbines Ltd Fuel-injection arrangement for a gas turbine combuster
JPH1183016A (ja) 1997-09-10 1999-03-26 Mitsubishi Heavy Ind Ltd ３次元スワーラ
DE69916911T2 (de) * 1998-02-10 2005-04-21 Gen Electric Brenner mit gleichmässiger Brennstoff/Luft Vormischung zur emissionsarmen Verbrennung
US6092363A (en) * 1998-06-19 2000-07-25 Siemens Westinghouse Power Corporation Low Nox combustor having dual fuel injection system
DE19948673B4 (de) 1999-10-08 2009-02-26 Alstom Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
EP1710504A2 (fr) * 1999-12-15 2006-10-11 Osaka Gas Co., Ltd. Brûleur, moteur de turbine à gaz et système de cogénération
DE10056243A1 (de) 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
DE10064893A1 (de) * 2000-12-23 2002-11-14 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeindüsung
DE10108560A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer

Also Published As

Publication number Publication date
EP1534997A2 (fr) 2005-06-01
CN100432531C (zh) 2008-11-12
ES2550096T3 (es) 2015-11-04
US7753677B2 (en) 2010-07-13
US20060035188A1 (en) 2006-02-16
JP4369370B2 (ja) 2009-11-18
EP1394471A1 (fr) 2004-03-03
JP2008256357A (ja) 2008-10-23
WO2004025183A3 (fr) 2005-01-20
CN1678871A (zh) 2005-10-05
JP4841587B2 (ja) 2011-12-21
WO2004025183A2 (fr) 2004-03-25
JP2006507466A (ja) 2006-03-02

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