EP1099825A1 - Aube de turbine et sa méthode de production - Google Patents

Aube de turbine et sa méthode de production Download PDF

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Publication number
EP1099825A1
EP1099825A1 EP99122577A EP99122577A EP1099825A1 EP 1099825 A1 EP1099825 A1 EP 1099825A1 EP 99122577 A EP99122577 A EP 99122577A EP 99122577 A EP99122577 A EP 99122577A EP 1099825 A1 EP1099825 A1 EP 1099825A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
cooling gas
throttle device
flow
throttle
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Withdrawn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
EP99122577A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Michael Scheurlen
Dirk Anding
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 EP99122577A priority Critical patent/EP1099825A1/fr
Priority to US10/129,850 priority patent/US6631561B1/en
Priority to EP00969567A priority patent/EP1228293B1/fr
Priority to JP2001538649A priority patent/JP4474085B2/ja
Priority to CNB008169950A priority patent/CN1312381C/zh
Priority to PCT/EP2000/010678 priority patent/WO2001036790A1/fr
Priority to DE50009560T priority patent/DE50009560D1/de
Publication of EP1099825A1 publication Critical patent/EP1099825A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the invention relates to a turbine blade, in particular Gas turbine blade, with one head, one foot and one Airfoil area and with an inner channel system individual channels through which cooling gas flows can be passed inside the turbine blade and with a throttle device influencing the flow of the cooling gas, where cooling gas from the foot area through in the channels the airfoil area to the head area and vice versa Direction is diverted, as well as with outlet openings for the discharge of the cooling gas from the turbine blade, which are arranged on the downstream side of the turbine blade are, and the invention relates to a method for manufacturing a turbine blade with the features of the generic term of claim 10.
  • an action fluid especially one operated with a gas
  • the action fluid on a high temperature heated In a gas turbine with one Combustion chamber for the generation of the hot gas are the Nearest guide vanes and blades from one Cooling gas flows through, so that the prevailing high Withstand temperatures that are sometimes above critical Values of the for the manufacture of the turbine blade material used. Through the cooling gas Temperature reduced on and within the turbine blade, so that the mechanical stability and thus the functionality the turbine blade is guaranteed in these conditions is.
  • An outer wall of the turbine blade, around which an action fluid flows encloses a meandering in this type of cooling Channel system that repeats the cooling gas from one Foot area to a head area of the turbine blade and again leads back to the foot area.
  • the area of the cooling gas inlet is called the leading edge area, and the area the cooling gas discharge is referred to as the trailing edge area.
  • the object of the present invention is therefore a Turbine blade with features mentioned at the beginning a throttle device for adjusting the flow of the Cooling gas without affecting the flow of the cooling gas on the Form the leading edge and - as a sub-task - a structurally simple and also individually adaptable process specify for the manufacture of such a turbine blade.
  • the object is achieved in that the throttle device the outlet openings in the rear area of the flow path is upstream.
  • the throttle device can the flow of the cooling gas without adverse effects throttle to the flow of the cooling gas.
  • the flow on the The leading edge is largely undisturbed.
  • the throttling takes place only in a rear area of the flow path.
  • the Cooling gas flow has left most of its path behind and the tasks of heat dissipation that are sufficient Flow rate are coupled, already met.
  • the pressure difference between the first cooling chamber and the surrounding one hot action fluid is retained so that no hot gas entry can occur in the blade, causing severe damage would lead. It is therefore a reliable cooling the turbine blade ensures.
  • the consumption of cooling gas minimized. It just has to have so much cooling gas for the turbine blade can be used as absolutely necessary is to prevent overheating. In this way you get optimal cooling of the turbine blade and at the same time good turbine efficiency.
  • a streamlined control of the cooling gas flow is possible if the throttle device at a reversal point of a Channel is attached. Here you can see the cross section of the canal and thus the flow of the cooling gas simply in a predetermined Set dimensions. Any dimensional differences caused by the production of the gas turbine can be created with the Make the throttle device harmless. So can also different types of turbine blades have the same type of throttle device be used. This reduces the number the required different components of the turbine blade.
  • the throttle device mounted in a through opening for casting is.
  • Through openings, for example, through Core brackets of the casting core can arise during casting this way can be used sensibly. Usually they will just closed with plates.
  • the throttle device fulfills the same closing function and throttles at the same time the cooling gas flow. Through it is an afterthought Adjustment of the flow and compensation of any Dimensional inaccuracies possible after casting. Through use of the lead-through openings can thus be manufacturing steps can be saved, which greatly reduces the production costs.
  • the through opening closed by the throttle device is. If, for example, strong thermal and mechanical Loads on the turbine blade the throttle device shaken off and got into the sewer system, could cause severe damage to the turbine blade respectively lead to complete failure of cooling what failure of the turbine within a short time. Also an outside of the turbine blade inside the Throttle device located in the turbine can cause great damage. In addition, the cooling effect would be reduced that the cooling gas due to the loss of the Throttle device free through opening on a inappropriate place is released into the environment.
  • the throttle device in the foot area is arranged. This makes it easy to achieve Throttle device during inspections of the turbine blade and a control option with regard to your sealing and throttling effect given.
  • a good stability and functionality is given when the Throttle device from a throttle projection of a plug is formed.
  • the plug is designed so that that he has the outside dimensions of the opening in which he is inserted is individually adjusted. This is particularly advantageous if it is a passage opening due to casting production is because their dimensions at different Turbine blade models fluctuate.
  • the throttling happens by means of the throttle projection, which also functions very simple structure.
  • the throttle projection can thus trained stable while ensuring its function be, which means that the throttle device is low-maintenance and works reliably.
  • the throttling is even at high Flow rates of the cooling gas and the associated high Pressures or strongly changing loads are guaranteed.
  • the throttling device from a foot to a plug caulked screw is formed.
  • the screw is in the plug, which is fastened in the lead-through opening, used. In this way, the introduction of a thread avoided in the cast turbine blade.
  • the in the The screw inserted into the plug can be adjusted continuously and enables individual adjustment of the throttling to the flow requirements of the trailing edge area. By caulking the screw, the screw in the desired position locked.
  • the opening can be a through opening due to casting production, but also to one after casting in the turbine blade bsw. by drilling act introduced opening.
  • the place of Throttling device to the model and casting dependent needs be better adapted.
  • the sub-task directed towards the manufacture of a turbine blade is solved in that after the casting process throttle device influencing the flow of the cooling gas in the rear area of the flow path, the outlet openings upstream, introduced and measuring the flow of the cooling gas in a manufacturing-related Through opening is set up that a predetermined Value of a flow parameter of the cooling gas is reached and then the throttle device in the throttle position is permanently attached.
  • the manufacturing process is for different blade types very similar if the casting core is used during the casting process a guide bracket in the base area of the turbine blade in its position is held relative to the cast outer jacket, and that in the through opening caused by the bracket a throttle device is used. That makes it easier Manufacturing process, reduces the conversion time and the number the parts to be used in the manufacture of various Turbine blade types.
  • the channel system 5 shows a longitudinal section through a foot region 2 and a part of a channel system 5 of a gas-cooled turbine blade 1.
  • the channel system 5 is essentially in the blade area 3 of the turbine blade 1. It points an inlet opening 22 at the foot area 2, at the beginning of the flow path 6 of the cooling gas through which the cooling gas enters the duct system 5 is inserted, and outlet openings 8 in Outflow region 21 of the turbine blade 1 through which the cooling gas leaves the channel system 5 at the end of its flow path 6.
  • the cooling gas is meandering in its flow path 6 the channels 12 separated by partitions 21 are, several times from the foot area 2 to not shown Head area and again headed to foot area 2.
  • the Channels 12 are connected to one another by reversal points 13 border the foot area 2 or the head area.
  • the outlet openings 8 upstream there is a flow of the cooling gas influencing throttle device 11.
  • FIG. 2 shows a longitudinal section through the foot region 2 of a Turbine blade with a throttling plug 20.
  • the plug 20 is by means of a shoulder 26 in a through opening 10 held.
  • the plug 20 has a throttle projection 17 on, with the cooling gas flow reduced in the inserted state can be.
  • the plug 20 is at the last reversal point 13 before the cooling gas emerges from the duct system 5 in an opening in the wall 32 of the foot region 2 of the turbine blade 1 attached.
  • the attachment in is advantageous a casting-related opening, because it is a manufacturing step the turbine blade 1 is saved and the Stopper 20 at the same time on a favorable for throttling Place, namely the reversal point 13 of a channel sits. On these places are preferably in the casting, as in Fig.6 shown core holding pieces 29, the casting core 28 relative to the surrounding cast jacket 31 and ensure that predetermined dimensions are adhered to.
  • the flow path 6 is at the reversal point 13 by means of a curved guide rib 18 divided into two partial flow paths, a first cooling gas partial flow path 23, which corresponds to the foot region 2 is directly adjacent and a second cooling gas partial flow path 24, which is separated by the guide rib 18.
  • the passed through Cooling gas partial flows are after passing the guide rib 18 reunited and leave the turbine blade 1 through the outlet openings 8.
  • the throttle device 11 throttles the first cooling gas partial flow.
  • the second Cooling gas partial flow flows regardless of the strength of the Throttling through the plug 20 a side channel 25 constant Size. This ensures a minimum flow of cooling gas.
  • FIG. 3 shows a perspective top view of a foot region 2 a turbine blade which is a casting-related Feedthrough opening 10 and a closing this Has plug 20.
  • This passage opening 10 is created as shown in Fig. 6, when casting the turbine blade 1. It has the negative form of a guide bracket 29 through which the casting core 28, which forms the channel system 5, is connected to the cast outer jacket 31 so that the cast core 28 during the casting and subsequent cooling of the Casting material keeps the desired position.
  • the lead-through opening 10 is elongated in this case with four side walls 19 formed.
  • FIG. 4 shows a detailed view of a reversal point 13 with a Throttle device consisting of a plug 20 and a throttle screw 14 is constructed.
  • the plug 20 is in the Feed-through opening 10 attached, preferably welded.
  • the Throttle screw 14 is screwed into the plug 20. It sticks out with her foot 16 serving as a throttle projection from the stopper 20 out in the throttle area 15 and thus in the first Cooling gas partial flow 23 into it.
  • the position of the throttle screw 14, or its foot 16 is continuously changeable. In a flow meter, not shown the flow of the cooling gas measured and the position of the Throttle screw 14 changed until a desired Flow is reached. Then the throttle screw 14 fixed in the plug 20. For this, the screw is caulked, soldered or welded.
  • FIG. 5 shows a longitudinal section through the foot area 2 at a 90 ° angle. Angle to the longitudinal section from Fig. 4.
  • the throttle screw 14 is in the throttle position, screwed into the stopper 20, which is fastened in the through opening 10.
  • the Throttle projection 17 closes the throttle region 15 by which the first cooling gas partial flow flows.
  • the foot 16 of the screw becomes only part of the flow path closed, as shown in Fig. 5. It is also a precise adaptation of the foot to the throttle area is possible, thereby blocking the entire flow path in the area is.
  • FIG. 6 shows a casting mold 27 with a casting core 28 and a casting outer jacket 31.
  • the cast core 28 is with the cast outer jacket 31 via guide brackets 29, called core brands.
  • the casting material is via casting channels 30 into the interior of the casting mold 27 guided and frozen.
  • the guide bracket 29 ensures that the casting core 28 during the casting process and when cooling the casting material maintains the correct position and the dimensional requirements are fulfilled. After the casting process the guide bracket 29 removed and created in its place thus a through opening due to casting production 10 in the foot region 2 of the turbine blade 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99122577A 1999-11-12 1999-11-12 Aube de turbine et sa méthode de production Withdrawn EP1099825A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP99122577A EP1099825A1 (fr) 1999-11-12 1999-11-12 Aube de turbine et sa méthode de production
US10/129,850 US6631561B1 (en) 1999-11-12 2000-10-30 Turbine blade and method for producing a turbine blade
EP00969567A EP1228293B1 (fr) 1999-11-12 2000-10-30 Procede de fabrication d'une ailette de turbine
JP2001538649A JP4474085B2 (ja) 1999-11-12 2000-10-30 タービン翼とその製造方法
CNB008169950A CN1312381C (zh) 1999-11-12 2000-10-30 透平叶片和制造透平叶片的方法
PCT/EP2000/010678 WO2001036790A1 (fr) 1999-11-12 2000-10-30 Ailette de turbine et procede de fabrication d'une ailette de turbine
DE50009560T DE50009560D1 (de) 1999-11-12 2000-10-30 Verfahren zur herstellung einer turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99122577A EP1099825A1 (fr) 1999-11-12 1999-11-12 Aube de turbine et sa méthode de production

Publications (1)

Publication Number Publication Date
EP1099825A1 true EP1099825A1 (fr) 2001-05-16

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ID=8239379

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EP99122577A Withdrawn EP1099825A1 (fr) 1999-11-12 1999-11-12 Aube de turbine et sa méthode de production
EP00969567A Expired - Lifetime EP1228293B1 (fr) 1999-11-12 2000-10-30 Procede de fabrication d'une ailette de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP00969567A Expired - Lifetime EP1228293B1 (fr) 1999-11-12 2000-10-30 Procede de fabrication d'une ailette de turbine

Country Status (6)

Country Link
US (1) US6631561B1 (fr)
EP (2) EP1099825A1 (fr)
JP (1) JP4474085B2 (fr)
CN (1) CN1312381C (fr)
DE (1) DE50009560D1 (fr)
WO (1) WO2001036790A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1843007A1 (fr) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Aube de turbine avec élément de fermeture séparé
EP2003291A1 (fr) * 2007-06-15 2008-12-17 ALSTOM Technology Ltd Aube de turbine à gaz moulée et procédé de production
EP2476863A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
EP2628900A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Aube directrice de turbine dotée d'un élément d'étranglement
CN106435355A (zh) * 2016-08-31 2017-02-22 南京赛达机械制造有限公司 一种水冷型汽轮机叶片

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US7216694B2 (en) * 2004-01-23 2007-05-15 United Technologies Corporation Apparatus and method for reducing operating stress in a turbine blade and the like
US7137782B2 (en) * 2004-04-27 2006-11-21 General Electric Company Turbulator on the underside of a turbine blade tip turn and related method
US7210906B2 (en) * 2004-08-10 2007-05-01 Pratt & Whitney Canada Corp. Internally cooled gas turbine airfoil and method
EP1869289B1 (fr) * 2005-04-11 2014-12-03 Alstom Technology Ltd Support d'aubes directrices
US8985940B2 (en) 2012-03-30 2015-03-24 Solar Turbines Incorporated Turbine cooling apparatus
US9546554B2 (en) 2012-09-27 2017-01-17 Honeywell International Inc. Gas turbine engine components with blade tip cooling
US9670797B2 (en) * 2012-09-28 2017-06-06 United Technologies Corporation Modulated turbine vane cooling
EP2826955A1 (fr) 2013-07-15 2015-01-21 Siemens Aktiengesellschaft Aube de turbine moulée avec une ouverture fermée par un bouchon et procédé de fermeture d'une ouverture d'une aube de turbine moulée
EP2832953A1 (fr) * 2013-07-29 2015-02-04 Siemens Aktiengesellschaft Aube de turbine
CN103586634A (zh) * 2013-11-01 2014-02-19 哈尔滨汽轮机厂有限责任公司 一种燃气轮机透平空心静叶片导流芯的制备方法
EP2918775A1 (fr) 2014-03-11 2015-09-16 Siemens Aktiengesellschaft Procédé d'obturation d'une ouverture d'une aube de turbine et bouchon approprié pour ce faire
EP3081751B1 (fr) * 2015-04-14 2020-10-21 Ansaldo Energia Switzerland AG Profil aérodynamique refroidi et procédé de fabrication dudit profil aérodynamique
EP3147455A1 (fr) 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Aube directrice de turbine ayant un agencement d'étranglement
KR102193940B1 (ko) * 2018-01-22 2020-12-22 두산중공업 주식회사 베인 링 조립체, 이의 조립방법 및 이를 포함하는 가스터빈
EP3862537A1 (fr) * 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Tuyère de turbine refoidie et segment d'aube de guidage de turbine
GB202213805D0 (en) * 2022-09-22 2022-11-09 Rolls Royce Plc Platform for stator vane

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GB374377A (en) * 1931-01-19 1932-06-09 Bbc Brown Boveri & Cie Improvements in and relating to turbine blades
GB375226A (en) * 1931-01-19 1932-06-23 Bbc Brown Boveri & Cie Improvements in and relating to the blades of steam and gas turbines
US2906494A (en) * 1956-06-12 1959-09-29 Daniel J Mccarty Heat responsive means for blade cooling
US3807892A (en) * 1972-01-18 1974-04-30 Bbc Sulzer Turbomaschinen Cooled guide blade for a gas turbine
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US4456428A (en) * 1979-10-26 1984-06-26 S.N.E.C.M.A. Apparatus for cooling turbine blades
GB2078596A (en) * 1980-06-19 1982-01-13 Rolls Royce Method of Making a Blade
US5243759A (en) * 1991-10-07 1993-09-14 United Technologies Corporation Method of casting to control the cooling air flow rate of the airfoil trailing edge

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1843007A1 (fr) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Aube de turbine avec élément de fermeture séparé
EP2003291A1 (fr) * 2007-06-15 2008-12-17 ALSTOM Technology Ltd Aube de turbine à gaz moulée et procédé de production
WO2008151900A2 (fr) * 2007-06-15 2008-12-18 Alstom Technology Ltd Aubes de turbine
WO2008151900A3 (fr) * 2007-06-15 2009-02-19 Alstom Technology Ltd Aubes de turbine
US8137069B2 (en) 2007-06-15 2012-03-20 Alstom Technology Ltd Turbine blades
EP2476863A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
EP2628900A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Aube directrice de turbine dotée d'un élément d'étranglement
WO2013120560A1 (fr) * 2012-02-14 2013-08-22 Siemens Aktiengesellschaft Aube directrice de turbine équipée d'un élément d'étranglement
CN104126054A (zh) * 2012-02-14 2014-10-29 西门子公司 具有节流元件的涡轮机导向叶片
CN104126054B (zh) * 2012-02-14 2016-02-03 西门子公司 具有节流元件的涡轮机导向叶片
RU2615091C2 (ru) * 2012-02-14 2017-04-03 Сименс Акциенгезелльшафт Направляющая лопатка турбины, снабженная дроссельным элементом
US9856738B2 (en) 2012-02-14 2018-01-02 Siemens Aktiengesellschaft Turbine guide vane with a throttle element
CN106435355A (zh) * 2016-08-31 2017-02-22 南京赛达机械制造有限公司 一种水冷型汽轮机叶片

Also Published As

Publication number Publication date
JP2003515024A (ja) 2003-04-22
US6631561B1 (en) 2003-10-14
EP1228293A1 (fr) 2002-08-07
JP4474085B2 (ja) 2010-06-02
DE50009560D1 (de) 2005-03-24
CN1312381C (zh) 2007-04-25
WO2001036790A1 (fr) 2001-05-25
EP1228293B1 (fr) 2005-02-16
CN1409800A (zh) 2003-04-09

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