EP1268981A1 - Installation de turbine - Google Patents

Installation de turbine

Info

Publication number
EP1268981A1
EP1268981A1 EP01927701A EP01927701A EP1268981A1 EP 1268981 A1 EP1268981 A1 EP 1268981A1 EP 01927701 A EP01927701 A EP 01927701A EP 01927701 A EP01927701 A EP 01927701A EP 1268981 A1 EP1268981 A1 EP 1268981A1
Authority
EP
European Patent Office
Prior art keywords
sealing element
turbine system
turbine
plate elements
adjacent
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
EP01927701A
Other languages
German (de)
English (en)
Other versions
EP1268981B1 (fr
Inventor
Peter Tiemann
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
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 filed Critical Siemens AG
Priority to EP01927701A priority Critical patent/EP1268981B1/fr
Publication of EP1268981A1 publication Critical patent/EP1268981A1/fr
Application granted granted Critical
Publication of EP1268981B1 publication Critical patent/EP1268981B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05005—Sealing means between wall tiles or panels
    • 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
    • F23R2900/00012—Details of sealing 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a turbine system, in particular a gas turbine system.
  • a gas turbine system is understood in the following to mean a system which comprises a combustion chamber and a turbine which is referred to as the gas turbine and is arranged downstream of the combustion chamber.
  • a fuel gas is burned in a gas space, and the hot gas generated is fed to the turbine and flows through it.
  • the flow path of the hot gas through the turbine is also referred to below as the gas space.
  • the turbine has fixed guide vanes, which extend radially from the outside in the gas space, as well as rotor blades attached to a shaft called a rotor, which extend radially outward from the rotor. When viewed in the longitudinal direction of the turbine, the guide vanes and the rotor blades engage with one another in a tooth-like manner.
  • the turbine generally has several turbine stages, with a guide vane ring being arranged in each stage, i.e. several of the guide blades are arranged next to one another in the circumferential direction of the turbine.
  • the individual guide vane rings are arranged one after the other in the axial direction.
  • the gas space is usually clad with plate elements. In the combustion chamber, these are tiles, and in the turbine, the plate elements are formed by so-called base plates of the individual guide vanes.
  • the gas area of the combustion chamber and the turbine should be as tight as possible. Therefore, low leakage losses between the individual plate elements are aimed for. In particular, leakage losses between two turbine stages are to be prevented.
  • Due to the large temperature ranges in the gas space there is the problem that a seal expands the must take up and bridge individual plate elements without significantly affecting the seal. This problem is exacerbated by the fact that both the tiles and the base plates of the guide vane are not fastened at their edge regions to adjacent plate elements, so that the plate edges are more or less free and are subject to bending due to thermal expansion. For example, the tiles are usually fastened in the middle and bend approximately spherically when subjected to thermal stress. A seal must therefore - both because of the conical design of the combustion chamber and the turbine in the axial direction - permit both axial and radial mobility.
  • the base plates are provided with a groove on their end face, a sealing plate being inserted into the grooves of two base plates of guide blades from adjacent turbine stages.
  • the end grooves the axial-radial mobility of the foot plates is achieved in that the grooves have sloping side walls.
  • Such grooves are, however, very expensive to manufacture.
  • such a seal is relatively leaky, since a differently rapid thermal expansion behavior of the foot plates and the so-called turbine guide vane carrier to which they are attached must be taken into account.
  • the turbine guide vane carrier When the turbine starts up, the foot plates expand faster, so that a leakage gap between the foot plates is initially closed. The leakage gap opens again when the turbine guide vane carrier has expanded according to the temperature.
  • the invention has for its object to enable a seal that overcomes the disadvantages described.
  • the object is achieved according to the invention by a turbine system, in particular a gas turbine system, with a gas space which is delimited on the outside by adjacent plate elements, a sealing element being assigned to each other adjacent plate elements and connecting them together in a clamp-like manner on their rear sides facing away from the gas space ,
  • the main advantage is the clamp-like design of the sealing element.
  • the sealing element therefore spans the two plate elements. In the case of thermal expansion, the sealing element follows the plate elements without leaving a gap. The sealing by the sealing element is therefore largely unaffected by thermal expansion.
  • the sealing element preferably enables the plate elements to be movable both in the axial and in the radial direction.
  • the sealing element is therefore particularly elastic, both in the axial and in the radial direction.
  • the axial direction here means an extension in the longitudinal direction of the turbine system and the radial direction is an extension perpendicular to the longitudinal axis.
  • the sealing element preferably has two legs, each of which engages in a groove of adjacent plate elements. This enables the sealing elements to be fastened in a manner that is simple to manufacture.
  • the groove preferably extends essentially radially from the rear side of the respective plate element.
  • the legs therefore protrude radially outward from the grooves. This configuration of the groove enables simple
  • the sealing element is preferably constructed in several parts.
  • the legs of the multi-part sealing element preferably overlap over a common circumferential length. This circumferential length is dimensioned sufficiently large to largely avoid leakages.
  • the sealing element is U-shaped, which is easy to implement both in terms of production technology and assembly technology.
  • the sealing element has a corrugated structure in the manner of a bellows for absorbing expansions.
  • the sealing element expediently has this corrugated structure in several directions, so that it can absorb strains in different directions.
  • the sealing element has a double S-shape.
  • the sealing element is arranged between adjacent tiles of a combustion chamber. This ensures a secure seal between the tiles, even if they bend spherically due to the thermal load.
  • the sealing element is arranged between the base plates of adjacent guide blades of a turbine, in particular between the Base plates of guide blades of neighboring turbine stages.
  • the individual base plates are therefore connected to one another in the axial or longitudinal direction of the turbine via clamp-like sealing elements.
  • the clamp-like sealing element described is preferably for the sealing in the axial direction and another for the sealing in the circumferential direction Sealing element provided.
  • differently designed sealing elements are used, in particular for assembly reasons.
  • the further sealing element preferably has a receiving area into which the plate elements extend.
  • the sealing element is H-shaped in cross section.
  • FIG. 1 shows a turbine system with a combustion chamber and turbine
  • FIG. 3 different conventional sealing variants
  • FIG. 4 the sealing variant according to the invention
  • FIG. 5-7 different variants of a sealing element
  • FIG. 8 shows a seal provided in particular for plate elements arranged next to one another in the longitudinal direction.
  • a turbine system 2 in particular a gas turbine system of a turbine set for a power plant for energy generation, comprises a combustion chamber 4 and a turbine 6, which is arranged in the longitudinal or axial direction 8 of the turbine system 2 after the combustion chamber 4. Both the combustion chamber 4 and the turbine 6 are shown cut open in a partial area. This allows a view into the gas space 10 of the combustion chamber 4 and into the gas space 12 of the turbine 6.
  • the combustion chamber 4 is supplied with a fuel gas BG via a gas supply 14, which is burned in the gas space 10 of the combustion chamber 4 and forms a hot gas HG.
  • the gas space 10 is lined with a large number of tiles 13 designed as plate elements.
  • the hot gas HG flows through the turbine 6 and leaves it as a cold gas KG via a gas discharge line 16.
  • the hot gas HG is guided in the turbine 6 via guide vanes 18 and rotor blades 20.
  • a shaft 22 is driven on which the moving blades 20 are arranged.
  • the shaft 22 is connected to a generator 24.
  • the blades 20 extend radially outward from the shaft 22.
  • the guide vanes 18 have a base plate 32 and an attached blade 21.
  • the guide vanes 18 are each fastened via their base plates 32 on the outside of the turbine 6 to a so-called guide vane carrier 26 and extend radially into the gas space 12. Seen in the longitudinal direction 8, the guide vanes 18 and the rotor blades 20 engage in a tooth-like manner.
  • Several of the moving blades 20 and the guide blades 18 are each combined to form a ring, each guide blade ring representing a turbine stage.
  • the second turbine stage 28 and the third turbine stage 30 are shown as examples.
  • the base plates 32 of the individual guide blades 18, like the tiles 13, are designed as plate elements which adjoin one another both in the axial direction 8 and in the circumferential direction 33 of the turbine 6 and limit the gas space 12.
  • the location marked with a circle in FIG. 1 is shown enlarged in FIGS. 2 to 4.
  • the seal described for these figures between two foot plates 32, which are arranged next to one another in particular in the longitudinal direction 8, can also be transferred analogously as a seal for the tiles 13 of the combustion chamber 4.
  • the sealing takes place without a special sealing element solely on the basis of an overlap of mutually adjacent foot plates 32.
  • the two foot plates 32 are designed step-like. With thermal stress and the associated expansion, the two foot plates 32 shift relative to one another in a movement superimposed in the longitudinal direction 8 and in the radial direction 36. As a result, the leakage gap 38 formed between the two foot plates 32 varies. The sealing effect therefore depends crucially on the expansion behavior of the foot plates 32.
  • the foot plates 32 according to FIGS. 2 to 4 each have a hooking on their rear side 39 facing away from the gas space 12. element 40, via which the foot plates 32 are held on the guide vane support 26 (see FIG. 1).
  • Each footplate 32 typically has two interlocking elements 40, which are designed differently and enable both mobility in the axial direction 8 and in the radial direction 36.
  • a further conventional sealing arrangement has a sealing plate 41 which is inserted into grooves 44 in the adjacent foot plates 32.
  • the grooves 44 are incorporated in the end faces 46 of the foot plates 32. They have an opening angle ⁇ of approximately 15 ° in order to enable the foot plates 32 to move in the radial direction 36.
  • a leakage gap 38 is formed between the sealing plate 41 and the foot plates 32, which varies with the expansion due to the thermal load. This variation is due, among other things, to the fact that the base plates 32 expand faster than the guide vane carrier 26 to which they are attached.
  • a U-shaped sealing element 42A with its two legs 52 is introduced into the grooves 44 and in particular fastened.
  • the attachment takes place, for example, by clamping action or also by welding.
  • the sealing element 42A is designed in particular as a sheet metal element. Its legs 52 essentially extend outward in the radial direction, so that the arch 54 connecting the two legs 52 is spaced apart from the rear side 39. This stretched out guidance enables an elastic behavior of the sealing element 42A, ie it follows the thermal expansions of the foot plates 32. The thermal mobility of the foot plates 32 is thus ensured by the flexible or stretchable sealing element 42A. The mobility is therefore independent of the special design of the grooves 44, so that they can be adapted to the legs 52 in a very precise manner. No or only a very small leakage gap 38 is therefore formed between the legs 52 and the grooves 44, which is independent of the thermal stress on the foot plates 32.
  • a sealing element 42B is formed from two separate legs 52, each of which has an arc 54 and overlaps over a circumferential length L.
  • the multi-part design of the sealing element 42B simplifies the assembly, since, for example, the individual legs 52 are simply attached to the corresponding grooves 44 of the respective base plates 32 before the guide vanes 18 are installed, and these are subsequently attached to the guide vane carrier 26.
  • the common circumferential length L is chosen to be as large as possible in order to keep the leakage gap 38 formed between them low for all temperature and operating states.
  • a sealing element 42D is provided with a corrugated structure 58, which replaces the simply designed arch 54 according to FIGS. 4 to 6.
  • This corrugated structure 58 preferably extends in several directions, in particular the two parallel to the foot plates 32.
  • the legs 52 can also be corrugated.
  • the sealing element 42D is thus designed in the manner of a bellows and enables even large thermal expansions to be absorbed in several directions without the leakage gap 38 being enlarged.
  • the sealing elements 42A to 42D preferably connect the base plates 32 of guide vane 18 of adjacent turbine stages 28, 30.
  • a further sealing element 60 is provided for guide vanes 18 of a guide vane ring which are adjacent to one another in the circumferential direction 33.
  • the further sealing element 60 is preferably H-shaped in cross section and has two longitudinal legs 62 which are connected to one another via a transverse leg 64. Between the two longitudinal legs 62, two receiving regions 65 are formed, separated from the transverse leg 64, into which the foot plates 32 extend. The side edges 66 of the foot plates 32 are bent outwards approximately vertically from the gas space 12 and nestle directly against the cross leg 64.
  • This configuration with the receiving areas 65 for the foot plates 32 advantageously enables a material thickness that is homogeneous over the entire foot plate 32, so that uniform cooling of the foot plate 32 is ensured and thermal stresses do not occur in the foot plate 32.
  • a closed cooling system 68 with steam as cooling medium is provided, which is shown in detail in FIG.
  • This closed cooling system 68 has an inflow channel 70 and one
  • the inflow duct 70 is formed between an outer baffle 74 and a baffle 76, which ches between baffle 74 and the base plate 32 is arranged.
  • the baffle plate 76 has flow openings 78 which are designed in the manner of nozzles, so that the cooling medium supplied via the inflow channel 70 passes into the return flow channel 72 along the arrows shown. Due to the nozzle-like mode of operation of the flow openings 78, the coolant is directed against the rear side 80 of the base plate 32 at high speed, so that an effective heat transfer between the coolant and the base plate 21 is realized.
  • the baffle plate 76 is supported against the base plate 32 and held at a distance via support elements 82, for example in the form of welding spots or welding webs.
  • the baffle plate 70 is attached directly to the side edge 66 of the foot plate 32, in particular welded on, and the baffle plate 68 is attached to the baffle plate 70.
  • a flow path 84 in the form of a leakage gap is formed between the further sealing element 60 and at least one of the base plates 32, so that, for example, air can flow from the gas space 12 away from the outer space 86 via the flow path 84 into the gas space 12 and thus the sealing area, i.e. the sealing element 60 and the side edges 66 cools.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Dans le cas d'une installation de turbine (2), notamment d'une installation de turbine à gaz, notamment les embases (32) de pales fixes (18) d'étages de turbines adjacents (28,30) sont reliées sur leurs faces arrière (48) opposées au compartiment de gaz (12) par un élément d'étanchéité en forme d'agrafe (42A à 42D). Cela permet d'obtenir entre des embases adjacentes (32) une étanchéité qui soit simple et efficace indépendamment de la dilatation thermique des embases (32). L'élément d'étanchéité de type agrafe (42A à 42D) est également approprié pour assurer l'étanchéité entre les carreaux (13) d'une chambre de combustion (4) de l'installation turbine (2).
EP01927701A 2000-03-02 2001-02-23 Installation de turbine Expired - Lifetime EP1268981B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01927701A EP1268981B1 (fr) 2000-03-02 2001-02-23 Installation de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00104346 2000-03-02
EP00104346A EP1130219A1 (fr) 2000-03-02 2000-03-02 Turbine avec joints d'étanchéitée entre les panneaux des parois
PCT/EP2001/002094 WO2001065073A1 (fr) 2000-03-02 2001-02-23 Installation de turbine
EP01927701A EP1268981B1 (fr) 2000-03-02 2001-02-23 Installation de turbine

Publications (2)

Publication Number Publication Date
EP1268981A1 true EP1268981A1 (fr) 2003-01-02
EP1268981B1 EP1268981B1 (fr) 2005-05-11

Family

ID=8168008

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00104346A Withdrawn EP1130219A1 (fr) 2000-03-02 2000-03-02 Turbine avec joints d'étanchéitée entre les panneaux des parois
EP01927701A Expired - Lifetime EP1268981B1 (fr) 2000-03-02 2001-02-23 Installation de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00104346A Withdrawn EP1130219A1 (fr) 2000-03-02 2000-03-02 Turbine avec joints d'étanchéitée entre les panneaux des parois

Country Status (5)

Country Link
EP (2) EP1130219A1 (fr)
JP (1) JP4637435B2 (fr)
CN (1) CN1272525C (fr)
DE (1) DE50106206D1 (fr)
WO (1) WO2001065073A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018206306A1 (fr) * 2017-05-08 2018-11-15 Siemens Aktiengesellschaft Procédé d'entretien d'une turbomachine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1302723A1 (fr) 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Revêtement pour parois intérieures de chambre de combustion
DE10155420A1 (de) 2001-11-12 2003-05-22 Rolls Royce Deutschland Hitzeschildanordnung mit Dichtungselement
FR2868119B1 (fr) * 2004-03-26 2006-06-16 Snecma Moteurs Sa Joint d'etancheite entre les carters interieurs et exterieurs d'une section de turboreacteur
US7870738B2 (en) 2006-09-29 2011-01-18 Siemens Energy, Inc. Gas turbine: seal between adjacent can annular combustors
DE102010031124A1 (de) * 2010-07-08 2012-01-12 Man Diesel & Turbo Se Strömungsmaschine
CH704185A1 (de) * 2010-12-06 2012-06-15 Alstom Technology Ltd Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.
DE102010063594A1 (de) 2010-12-20 2012-06-21 Mtu Aero Engines Gmbh Dichtanordnung und Turbomaschine mit einer derartigen Dichtanordnung
US8544852B2 (en) * 2011-06-03 2013-10-01 General Electric Company Torsion seal
JP6133416B2 (ja) * 2012-06-18 2017-05-24 ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ タービンの静止した部品間のシール
DE102015201782A1 (de) * 2015-02-02 2016-08-18 MTU Aero Engines AG Leitschaufelring für eine Strömungsmaschine
CN109653816B (zh) * 2019-01-23 2024-05-10 江苏核电有限公司 一种用于汽轮机自带围带叶片的撑顶工具及其撑顶方法

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US2991045A (en) * 1958-07-10 1961-07-04 Westinghouse Electric Corp Sealing arrangement for a divided tubular casing
US2999631A (en) * 1958-09-05 1961-09-12 Gen Electric Dual airfoil
US4199151A (en) * 1978-08-14 1980-04-22 General Electric Company Method and apparatus for retaining seals
CA2031085A1 (fr) * 1990-01-16 1991-07-17 Michael P. Hagle Etancheite entre anneaux de distributeur de turbine
US5158305A (en) * 1992-01-31 1992-10-27 Eg&G Pressure Science, Inc. Pressure-energized two-element seal
GB9305012D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Sealing structures for gas turbine engines
US5735671A (en) * 1996-11-29 1998-04-07 General Electric Company Shielded turbine rotor
US6076835A (en) * 1997-05-21 2000-06-20 Allison Advanced Development Company Interstage van seal apparatus
JPH1150805A (ja) * 1997-08-06 1999-02-23 Mitsubishi Heavy Ind Ltd ガスタービン静翼シュラウドのシール構造
GB2335470B (en) * 1998-03-18 2002-02-13 Rolls Royce Plc A seal

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018206306A1 (fr) * 2017-05-08 2018-11-15 Siemens Aktiengesellschaft Procédé d'entretien d'une turbomachine
US10927675B2 (en) 2017-05-08 2021-02-23 Siemens Aktiengesellschaft Method for maintaining a turbomachine

Also Published As

Publication number Publication date
CN1272525C (zh) 2006-08-30
JP2003525381A (ja) 2003-08-26
EP1268981B1 (fr) 2005-05-11
EP1130219A1 (fr) 2001-09-05
WO2001065073A1 (fr) 2001-09-07
DE50106206D1 (de) 2005-06-16
CN1408048A (zh) 2003-04-02
JP4637435B2 (ja) 2011-02-23

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