EP1124038A1 - Aubage de turbine - Google Patents

Aubage de turbine Download PDF

Info

Publication number
EP1124038A1
EP1124038A1 EP00102717A EP00102717A EP1124038A1 EP 1124038 A1 EP1124038 A1 EP 1124038A1 EP 00102717 A EP00102717 A EP 00102717A EP 00102717 A EP00102717 A EP 00102717A EP 1124038 A1 EP1124038 A1 EP 1124038A1
Authority
EP
European Patent Office
Prior art keywords
turbine
holding
platform part
rail
partner
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Withdrawn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
EP00102717A
Other languages
German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
Michael Dr.-Ing. Strassberger
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 EP00102717A priority Critical patent/EP1124038A1/fr
Priority to JP2001558580A priority patent/JP2003522872A/ja
Priority to CN01804795.5A priority patent/CN1289789C/zh
Priority to US10/203,388 priority patent/US6726452B2/en
Priority to EP01905702A priority patent/EP1254301A2/fr
Priority to PCT/EP2001/000932 priority patent/WO2001059263A2/fr
Publication of EP1124038A1 publication Critical patent/EP1124038A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a turbine blade arrangement with in predetermined distances over an outer circumference of a turbine disk arranged shovel, each one Have blade root, the radially positive in each a groove of the outer circumference of the turbine disk can be used, and each have a blade profile that is on a disc-side End area has a platform on the side.
  • the object of the present invention is therefore a turbine blade arrangement to create an extension of the Blade profiles allows, without or with only one slight increase in local loads from the grooves Turbine disc or blade feet.
  • the object is achieved in that at least part of the Platform by means of a holder that is independent of the blade root is connected to the turbine disc.
  • the platform with the turbine disc is at least part of the centrifugal load caused by the turbine disc rotating blades from the bracket to the Turbine disk to areas lying between the foot areas forwarded.
  • At least part of the centrifugal load thus does not have to be from the blade root or the groove in the foot is inserted, picked up and attached to the turbine disc be passed on. Due to the load redistribution the load is thus introduced more evenly into the turbine disk and the feet of the blades and the grooves into which the feet are pushed in by tension peaks relieves that affect the strength of the areas.
  • bracket Platform part formed separately from the blade the bracket takes over the entire centrifugal load through the platform part. The groove is no longer loaded.
  • Bracket and foot only need to be smaller Forward part of the total centrifugal load. In that area, in which the platform part is separated from the shovel edge, is a less massive formation of the Bucket and the platform part possible than with a one-piece, not additionally connected to the turbine disc Shovel, since not the weight of the platform must be carried. In this way it becomes Total weight of the bucket once by separating the Platform and also due to the less massive training the edges reduced.
  • the foot and the groove must therefore still carry less weight.
  • the blades come with the Bucket profiles and the separately attached platform parts not so easily in critical for blade attachment Vibrations or the vibrations can be dampen more easily than in the case of one-piece training the shovel.
  • the bucket and the platform part to manufacture separately with much less effort. Manufacturing is particularly important when casting the blade the mold and the exact casting execution simplified because the turbine blade almost without the molded platform no longer has a cantilevered component.
  • the isolated Platform part has a simple geometric shape, in generally plate-shaped and is thus of a low Effort can be made.
  • for the shovel and the platform part uses different materials become. As a result, when using a lighter alloy, Weight and, if applicable, material and processing costs be saved.
  • the largest possible area of the platform part achieved that the platform part between the end areas two adjacent blade profiles is used in such a way that it almost completely replaces the platforms. Nearly the entire platform mass is thus through the bracket worn and do not strain the feet or the grooves into which the feet are pushed in. It is therefore an optimal mass distribution reached on foot and bracket.
  • the separation areas, in which the platform part and the bucket are adjacent a lot of material and thus saving weight since it is no longer necessary to intercept lever forces arising from the large platform part.
  • a large material saving is also possible by that the edges of the blade profiles adjacent Platform part adapted to the curvature of the blade profiles are shaped.
  • the production is simplified since now a slim shape of the blade also in the transition area between Foot and profile is present, which is much easier to do is pouring.
  • the bracket consists of at least one pairing of one another engaging holding partners, at least a connecting element having a holding partner separately formed by the platform part and by the turbine disk is.
  • the platform part can by the separate training of Holding partner with different methods and easily interchangeable be attached to the turbine disc.
  • there are different material combinations possible between the parts In particular, the material a separately designed platform part and the separately trained holding partner, as well as the turbine disc and the shovel be different and taking into account of the respective requests and charges cost-optimized to be selected.
  • Form-locking means with the turbine disc can be connected to the platform part easily for example for repair purposes and can be reused afterwards without functional restrictions.
  • the bracket can be easily switched on and also in the event of a possible Remove corrosion attack with little effort, if the holding partner with the platform part and with the Turbine disc is associated with a game. At the same time the bracket with a force attack from different Directions or an alternating force better suitable to react flexibly and get into the appropriate Force direction easier to adjust, causing damage the bracket and the associated positive locking means and the platform part and the turbine disk avoided become.
  • a simple attachment is given by the fact that a holding partner runs straight across a coupling length and one has rail-like cross section and the other holding partner the pairing to the first holding partner in a straight line parallel runs and a the rail-like cross section of the first holding partner with positive cross-section having. Due to the rail-like design of the holding partners There are large support and over the entire coupling length Given contact areas and thus a good power distribution over the entire area of the coupling. Local voltage spikes due to the attacking centrifugal forces are thus reduced. Especially with a curved design of the Platform part sits the platform part through the rail-like Holding partner very reliably on the turbine disc.
  • a secure hold is given when a rail-like holding partner with the platform part and a rail-like holding partner is connected to the turbine disc and both Holding partner through a connecting element with two holding partners are connected, the connecting element forming a rail-shaped cross-sections form-fitting H-shaped Has cross section.
  • the holding partners are on one large area positively connected.
  • the Connection is simple to make and easily detachable. Due to the rail-like training of the holding partners can the connecting element with the H-shaped cross section easily inserted between the platform part and the turbine disc and be pulled out. Since no holding partner is a complex Has shape, they are easy and inexpensive producible.
  • a very stable bracket is given if it is constructed in this way is that the turbine disc is a rail-like holding partner and the platform part has a rail-encompassing Holding partner and the two by a connecting element are connected, the one rail-encompassing Holding partner and a rail-like holding partner.
  • FIG. 1 shows a perspective view of a turbine blade arrangement.
  • Working fluid especially hot gas in a gas turbine
  • the blades 4 are like a fir tree trained feet 8 in grooves 9 with a distance 1 in the outer circumference 2 of the turbine disc 3 by pushing it in from the side used.
  • By rotating the turbine disk 3 the blades 4 are directed towards the outside Centrifugal force.
  • This centrifugal force take the 8 foot Blade 4 and the claws 25 of the turbine disk 3 by different teeth 17, 18, 19, 21, 22, 23 on the base 8 are shaped like a fir tree and their corresponding formations find in the claw 25 on.
  • the platform part 10 is separate between two blades 4 used.
  • the bracket 11 is in this Case from two rail-like holding partners 31 and a connecting element 32.
  • the rail-like holding partners 31 are preferably on the outer circumference 2 of the turbine disk 3 almost in the middle between two grooves 9 for the blade feet 8 at a half distance 1 and on the platform part 10 the underside 28 facing the turbine disk 3 is attached.
  • Both rail-like holding partners 31 are parallel to each other and in the radial direction one above the other. They are connected by an H-shaped cross section having connecting element 32 with holding partners 30, the consist of rounded recesses 13 into which the holding partner 31 can be inserted.
  • the elements mentioned can be matched from different ones Materials, especially from another material be made as the turbine disc 3, for example to save costs.
  • the holding partners 30 are preferably 31 and the connecting element 32 are made in one piece, so that the strong attacking forces are no starting point for Find damage.
  • the turbine disc is there for reasons durability and strength from special hardened alloys, which are only ground to a limited extent and can be machined. In particular is however also a one-piece manufacture of the straight line extending, rail-like holding partner 31 with the turbine disc 3, possible. This improves the hold of the holding partner 31 on the turbine disc 3. Attack points for Damages due to the centrifugal force are thereby decreased.
  • the platform part 10 has at its two longer edges 20 a curvature 15.
  • the curvatures of the bilateral anten However, 20 do not necessarily have to match.
  • a corresponding curvature 15 can be found on the radius section longitudinal edges 29 a cross section of the blade profiles 5 in the end region 6 shovel the barrel 4. This way, too the curved course of the edges 29 with respect to the cross-sectional area of the blade profile 5 in the end region 6 optimized Area share of the platform part 10 reached. This relieves the groove area considerably.
  • the damping wires 16 follow the curvature 15 of the platform part 10 and the moving blade 4. For easier insertion of the damping wires 16, these are pre-bent.
  • the edges 20, 29 preferably have one corresponding, constant curvature 15 so that the previously provided with a bending radius corresponding to the curvature 15 Damping wires 16 can be easily inserted.
  • the connecting element 32 shows a connecting element 32 with an H-shaped cross section.
  • the holding partners 30 forming the two courtyards of the H Fig.1, preferably run straight and in the form of simple way rounded recesses 13 in the coupling area 14, which simplifies the manufacture of the elements.
  • the Connecting element 32 has over its entire cross section same shape and dimensions. That way it can can be used from both sides of the turbine disc.
  • the Platform part 10 a holding partner encompassing the rail shape 30 on, while the turbine disc 3 as in the first example has a rail-like holding partner 31.
  • the connecting element 32 now each has a rail-like Stop partner 31 and a rail-spanning stop partner 30. The connecting element 32 can easily be between the platform part 10 and turbine disk 3 are inserted.
  • Fig. 4 shows a distribution of forces due to the centrifugal load within a turbine disc 3 and the one used Blades 4 are formed, in which the invention Bracket technology is used.
  • the maximum notch stresses show up particularly in the claw area below the claw teeth 21 in the region of the recesses 17 ', see Fig. 1.
  • a significant part of the centrifugal force is passed on via the bracket 11 directly into the turbine disk 3 and does not load the claw recesses 17 '.
  • the bracket 11 show medium voltages and the stress peaks in the narrowest cross sections or radii
  • the teeth in the claw area have tension values that are far below move previously achievable values.
  • Through the load-optimized Division of functional areas of the turbine blade arrangement the force distribution is thus smoothed. This allows an overall higher centrifugal force load, for example by extending the blade profiles to improve efficiency. This extension can both go out together with an enlargement an outer turbine outlet cross section, as well as inwards towards the hub area of the Turbine disc.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00102717A 2000-02-09 2000-02-09 Aubage de turbine Withdrawn EP1124038A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP00102717A EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine
JP2001558580A JP2003522872A (ja) 2000-02-09 2001-01-29 タービン翼配置構造
CN01804795.5A CN1289789C (zh) 2000-02-09 2001-01-29 涡轮叶片布置
US10/203,388 US6726452B2 (en) 2000-02-09 2001-01-29 Turbine blade arrangement
EP01905702A EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine
PCT/EP2001/000932 WO2001059263A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00102717A EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine

Publications (1)

Publication Number Publication Date
EP1124038A1 true EP1124038A1 (fr) 2001-08-16

Family

ID=8167814

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00102717A Withdrawn EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine
EP01905702A Withdrawn EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01905702A Withdrawn EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Country Status (5)

Country Link
US (1) US6726452B2 (fr)
EP (2) EP1124038A1 (fr)
JP (1) JP2003522872A (fr)
CN (1) CN1289789C (fr)
WO (1) WO2001059263A2 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1319805A1 (fr) * 2001-12-17 2003-06-18 Techspace aero Rotor ou élément rotorique pour turbocompresseur
EP1898049A1 (fr) 2006-09-11 2008-03-12 Siemens Aktiengesellschaft Aube de turbine
EP2098687A1 (fr) * 2008-03-07 2009-09-09 Siemens Aktiengesellschaft Rotor pour une turbomachine
EP2154334A2 (fr) 2008-08-13 2010-02-17 Rolls-Royce plc Remplissage annulaire entre les aubes d'une turbine
EP2157283A1 (fr) * 2008-08-18 2010-02-24 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
WO2014197105A2 (fr) 2013-03-25 2014-12-11 United Technologies Corporation Segment de plate-forme et pale non solidaire pour un rotor
FR3038344A1 (fr) * 2015-06-30 2017-01-06 Snecma Assemblage aubage utilisant un emboitement
FR3109403A1 (fr) * 2020-04-16 2021-10-22 Safran Aircraft Engines Aube avec organes d’étanchéités améliorés

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DE10134611A1 (de) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US7300253B2 (en) 2005-07-25 2007-11-27 Siemens Aktiengesellschaft Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
JP4584102B2 (ja) 2005-09-30 2010-11-17 株式会社日立製作所 タービンロータと逆クリスマスツリー型タービン動翼及びそれを用いた低圧蒸気タービン並びに蒸気タービン発電プラント
US20070134094A1 (en) * 2005-12-08 2007-06-14 Stephen Gregory Rotor apparatus and turbine system incorporating same
US7762781B1 (en) 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
FR2913734B1 (fr) * 2007-03-16 2009-05-01 Snecma Sa Soufflante de turbomachine
FR2913735B1 (fr) * 2007-03-16 2013-04-19 Snecma Disque de rotor d'une turbomachine
US7931442B1 (en) 2007-05-31 2011-04-26 Florida Turbine Technologies, Inc. Rotor blade assembly with de-coupled composite platform
GB0802834D0 (en) * 2008-02-18 2008-03-26 Rolls Royce Plc Annulus filler
US9662721B2 (en) 2008-02-26 2017-05-30 United Technologies Corporation Method of generating a curved blade retention slot in a turbine disk
US8257045B2 (en) * 2008-08-15 2012-09-04 United Technologies Corp. Platforms with curved side edges and gas turbine engine systems involving such platforms
GB2463036B (en) * 2008-08-29 2011-04-20 Rolls Royce Plc A blade arrangement
US8277190B2 (en) * 2009-03-27 2012-10-02 General Electric Company Turbomachine rotor assembly and method
GB0908422D0 (en) * 2009-05-18 2009-06-24 Rolls Royce Plc Annulus filler
GB0910752D0 (en) * 2009-06-23 2009-08-05 Rolls Royce Plc An annulus filler for a gas turbine engine
FR2949142B1 (fr) * 2009-08-11 2011-10-14 Snecma Cale amortisseuse de vibrations pour aube de soufflante
GB0914060D0 (en) * 2009-08-12 2009-09-16 Rolls Royce Plc A rotor assembly for a gas turbine
US8496443B2 (en) * 2009-12-15 2013-07-30 Siemens Energy, Inc. Modular turbine airfoil and platform assembly with independent root teeth
US8231354B2 (en) * 2009-12-15 2012-07-31 Siemens Energy, Inc. Turbine engine airfoil and platform assembly
GB0922422D0 (en) * 2009-12-23 2010-02-03 Rolls Royce Plc Annulus Filler Assembly for a Rotor of a Turbomachine
US8545184B2 (en) * 2010-01-05 2013-10-01 General Electric Company Locking spacer assembly
GB2478918B8 (en) * 2010-03-23 2013-06-19 Rolls Royce Plc Interstage seal
US8066479B2 (en) * 2010-04-05 2011-11-29 Pratt & Whitney Rocketdyne, Inc. Non-integral platform and damper for an airfoil
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
KR101250643B1 (ko) * 2010-12-29 2013-04-03 현대중공업 주식회사 복합재료로 이루어진 프로펠러용 블레이드와 프로펠러 보스 연결 구조
CH704825A1 (de) * 2011-03-31 2012-10-15 Alstom Technology Ltd Turbomaschinenrotor.
US8689441B2 (en) 2011-12-07 2014-04-08 United Technologies Corporation Method for machining a slot in a turbine engine rotor disk
FR2987086B1 (fr) * 2012-02-22 2014-03-21 Snecma Joint lineaire de plateforme inter-aubes
FR2991372B1 (fr) * 2012-06-04 2014-05-16 Snecma Roue de turbine dans une turbomachine
US9399922B2 (en) 2012-12-31 2016-07-26 General Electric Company Non-integral fan blade platform
US9845699B2 (en) * 2013-03-15 2017-12-19 Gkn Aerospace Services Structures Corp. Fan spacer having unitary over molded feature
EP3058180B1 (fr) 2013-10-11 2018-12-12 United Technologies Corporation Rotor de soufflante ayant une fixation de plate-forme intégrée
GB201322668D0 (en) 2013-12-20 2014-02-05 Rolls Royce Deutschland & Co Kg Vibration Damper
US9856737B2 (en) * 2014-03-27 2018-01-02 United Technologies Corporation Blades and blade dampers for gas turbine engines
DE112015001620T5 (de) * 2014-04-03 2017-02-09 Mitsubishi Hitachi Power Systems, Ltd. Schaufel-oder Flügelreihe und Gasturbine
US10156151B2 (en) 2014-10-23 2018-12-18 Rolls-Royce North American Technologies Inc. Composite annulus filler
FR3039854B1 (fr) * 2015-08-03 2019-08-16 Safran Aircraft Engines Carter intermediaire de turbomachine comportant des moyens de fixation ameliores
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
CN105909557A (zh) * 2016-06-21 2016-08-31 中国航空工业集团公司沈阳发动机设计研究所 一种风扇转子叶片安装结构
EP3293354B1 (fr) * 2016-09-07 2021-04-14 Ansaldo Energia IP UK Limited Élément d'aubage de turbomachine et procédé de montage d'un tel élément
US11021984B2 (en) * 2018-03-08 2021-06-01 Raytheon Technologies Corporation Gas turbine engine fan platform
CN109469513B (zh) * 2018-12-13 2020-10-27 西安交通大学 一种汽轮机及其错位排布的枞树型叶根轮缘槽结构
CN113623020B (zh) * 2021-08-02 2022-07-08 无锡友鹏航空装备科技有限公司 一种密封性高的涡轮导向装置

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EP0787890A2 (fr) * 1996-02-02 1997-08-06 ROLLS-ROYCE plc Rotor pour turbine à gaz

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US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB2006883A (en) * 1977-10-27 1979-05-10 Rolls Royce Fan or Compressor Rotor Stage
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US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
GB2186639A (en) * 1986-02-19 1987-08-19 Rolls Royce Improvements in or relating to bladed structures for fluid flow propulsion engines
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EP0787890A2 (fr) * 1996-02-02 1997-08-06 ROLLS-ROYCE plc Rotor pour turbine à gaz

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1319805A1 (fr) * 2001-12-17 2003-06-18 Techspace aero Rotor ou élément rotorique pour turbocompresseur
EP1898049A1 (fr) 2006-09-11 2008-03-12 Siemens Aktiengesellschaft Aube de turbine
EP2098687A1 (fr) * 2008-03-07 2009-09-09 Siemens Aktiengesellschaft Rotor pour une turbomachine
EP2154334A2 (fr) 2008-08-13 2010-02-17 Rolls-Royce plc Remplissage annulaire entre les aubes d'une turbine
EP2154334A3 (fr) * 2008-08-13 2013-04-10 Rolls-Royce plc Remplissage annulaire entre les aubes d'une turbine
EP2157283A1 (fr) * 2008-08-18 2010-02-24 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
WO2010020568A1 (fr) * 2008-08-18 2010-02-25 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
WO2014197105A2 (fr) 2013-03-25 2014-12-11 United Technologies Corporation Segment de plate-forme et pale non solidaire pour un rotor
EP2978937A4 (fr) * 2013-03-25 2016-12-28 United Technologies Corp Segment de plate-forme et pale non solidaire pour un rotor
US10590798B2 (en) 2013-03-25 2020-03-17 United Technologies Corporation Non-integral blade and platform segment for rotor
FR3038344A1 (fr) * 2015-06-30 2017-01-06 Snecma Assemblage aubage utilisant un emboitement
FR3109403A1 (fr) * 2020-04-16 2021-10-22 Safran Aircraft Engines Aube avec organes d’étanchéités améliorés

Also Published As

Publication number Publication date
US20030012654A1 (en) 2003-01-16
US6726452B2 (en) 2004-04-27
CN1289789C (zh) 2006-12-13
EP1254301A2 (fr) 2002-11-06
WO2001059263A2 (fr) 2001-08-16
JP2003522872A (ja) 2003-07-29
CN1398322A (zh) 2003-02-19
WO2001059263A3 (fr) 2002-09-19

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