EP1331361B1 - Gegossene Turbinenleitschaufel mit Hakensockel - Google Patents

Gegossene Turbinenleitschaufel mit Hakensockel Download PDF

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Publication number
EP1331361B1
EP1331361B1 EP02001265A EP02001265A EP1331361B1 EP 1331361 B1 EP1331361 B1 EP 1331361B1 EP 02001265 A EP02001265 A EP 02001265A EP 02001265 A EP02001265 A EP 02001265A EP 1331361 B1 EP1331361 B1 EP 1331361B1
Authority
EP
European Patent Office
Prior art keywords
platform
vane
blade
turbine
outer edge
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
EP02001265A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1331361A1 (de
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 DE50214427T priority Critical patent/DE50214427D1/de
Priority to EP02001265A priority patent/EP1331361B1/de
Priority to AT02001265T priority patent/ATE467749T1/de
Priority to JP2003005500A priority patent/JP4303480B2/ja
Priority to CNB031075010A priority patent/CN100447374C/zh
Priority to US10/345,947 priority patent/US6923620B2/en
Publication of EP1331361A1 publication Critical patent/EP1331361A1/de
Application granted granted Critical
Publication of EP1331361B1 publication Critical patent/EP1331361B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/915—Pump or portion thereof by casting or molding
    • 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

Definitions

  • the invention relates to a turbine guide vane with a profiled, along a blade axis extended airfoil, to the end of a transverse to the blade axis extending platform is formed.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the flow medium.
  • To guide the flow medium in the turbine unit also commonly associated guide blade rows are arranged between adjacent blade rows with the turbine housing.
  • the turbine blades, in particular the guide vanes typically have a profiled airfoil extending along a blade axis for suitable guidance of the working medium, to which end a transversely to the end face for attachment of the turbine blade to the respective support body Blade axis extending, formed in at least one end region as a hook base platform is formed.
  • such gas turbines are usually thermodynamic reasons for particularly high outlet temperatures of the off of the combustion chamber and designed in the inflowing into the turbine unit working fluid of about 1200 ° C to about 1300 ° C.
  • the components of the gas turbine in particular the turbine blades, are exposed to comparatively high thermal loads.
  • the affected components are usually formed coolable.
  • the turbine blades are usually designed as a so-called hollow profile in modern gas turbines.
  • the profiled airfoil has for this purpose in its inner region also referred to as a vane core cavities in which a cooling medium can be performed.
  • a cooling medium can be performed.
  • the respective turbine blade can be flowed through in multiple channels, with a plurality of coolant channels, which can be acted upon by coolant and are separated from one another by comparatively thin partitions, being provided in the interior of the blade profile.
  • Such turbine blades are usually made by casting.
  • a casting mold adapted in its contour to the desired blade profile is poured out with wax.
  • core elements for example of ceramic material are arranged during casting in the mold, which are removed after the casting from the wax model for the blade body, so that the desired for the coolant channels cavities arise.
  • the wax model obtained in the first casting step is then provided with a ceramic coating by repeated immersion. Once this, if necessary after several dipping operations, has a sufficient thickness, the provided with the ceramic coating wax model is burned out, wherein the ceramic solidifies and the wax is burned out. This results in a ceramic mold for the blade, in which the core elements for cooling ducts or the like. are included.
  • this ceramic casting mold is poured out with blade material.
  • the wax model and in particular of its blade and the molded structural parts such as the platform or a hook base correspondingly shaped mask elements or slides are arranged in the mold for the first casting step, that during the casting process a cavity corresponding to the mold to be produced for receiving the wax remains.
  • the invention has for its object to provide a turbine vane of the above type, on the one hand for a particularly high thermal and mechanical strength is designed, and on the other hand, a reliable cooling with relatively little need for coolant is possible.
  • the invention is based on the consideration that the turbine guide vane should be designed for a particularly favorable manufacturability in monocrystalline construction.
  • a turbine guide vane in monocrystalline construction is in fact already relatively high load capacity due to the material properties.
  • a monocrystalline construction is more advantageous, in particular through the use of also referred to as a slider mask elements for the casting, especially since alternatively usable so-called lost inserts would contribute to the nucleation of polycrystalline material and thus are not suitable for monocrystalline blades.
  • the turbine guide vane should thus be designed in its contouring in such a way that positioning is possible in a comparatively simple manner and removal of the mask elements or slides used for forming platform depressions is possible after casting.
  • the turbine guide vane should be designed for a comparatively low demand for coolant. This can be achieved, among other things, by designing the platform designed to absorb the thermal loads to be comparatively thin-walled and thus with only a low material consumption. This can also be achieved under the specified specifications by arranging a plurality of mask elements in the casting mold before casting the turbine guide vane, whereby a mask element for reducing the platform thickness can be introduced into the space area provided for this. In order to enable the corresponding propulsion in this space area, bypassing moldings to be arranged above the platform and also in a space area particularly close to the blade center, the Turbine vane designed for beveled side walls in the region of the arranged on the platform outer ring.
  • a separation of functions between the components intended to receive the mechanical load on the one hand and to absorb the thermal load on the other hand is carried out.
  • a hook base is integrally formed on the blade of the turbine vane in the end above the platform.
  • the platform and the hook base are structurally decoupled from each other in the region of entanglement of the turbine vane.
  • the integrally formed on the blade platform only serves to compensate for the thermal load by the guided in the interior of the gas turbine hot working medium without this would be a mechanical load connected.
  • the platform is preferably designed comparatively thin-walled, which is in particular made possible by the fact that the platform is not exposed to any mechanical stress.
  • the mechanical load is carried out via a hook base arranged above the platform, which is suspended in a corresponding structural part on the turbine wall.
  • the hook base is expediently dimensioned sufficiently for receiving the mechanical load, wherein an impact of the hook base is avoided by thermal stress through the platform. The cooling requirement for the hook base is thus comparatively low.
  • the turbine guide vane has a nose-like projection delimiting the platform pocket, which remains in the region of the platform.
  • This projection is used in a particularly favorable manner as a support or fixative for an impingement cooling plate use.
  • the outer edge of the platform can in particular have an outer side wall which is essentially rectilinearly guided with respect to the blade axis, that is to say it is aligned parallel to it in cross section.
  • the outer edge is thus made comparatively thick in its region facing the platform floor and tapers in cross section steadily up to its end remote from the platform floor.
  • special means should be provided for acting on the comparatively thick lower space region of the outer edge.
  • the outer edge of the platform is advantageously provided in its bottom region with a number of cooling holes.
  • the cooling holes are guided in a further advantageous embodiment, the output side in a common cooling gap.
  • the turbine vane is preferably designed for a stationary gas turbine.
  • a casting system for producing such a turbine guide vane has a first mask element which can be positioned in a casting mold and has a recess which predefines an interface surface of the platform base.
  • a substantially flat trained second mask element in a tilted by an angle of more than 10 ° and less than 80 °, preferably of less than 60 ° relative to the boundary surface predetermined recess displaced direction.
  • the production of a platform pocket with bevelled side walls is also possible without the use of a "lost use”.
  • the casting system is thus suitable in particular for the production of monocrystalline turbine blades, especially since a deliberate omission of the use of "lost operations" nucleation for polycrystalline regions is kept particularly low.
  • the second mask element has an end face tilted relative to its base surface by an adjusted angle of more than 10 ° and less than 80 °, which forms a casting mask for the platform bottom together with the recess of the first mask element.
  • the advantages achieved by the invention are in particular that an obliquely guided side wall of the platform pocket, which is arranged by the first mask member or the circumferential slide arranged in the circumferential direction obliquely seated second mask member or the Separatschieber, an undercut of the ribbing of the profile for entanglement can be avoided.
  • both mask elements are removable after the completion of the casting process, so that the use of a "lost use” is not required.
  • By arranged in the outer edge of the platform cooling holes also reliable cooling of all areas of the space platform with comparatively low coolant requirement is possible, in particular by the comparatively broad base of the outer edge of the platform, the significant for the coolant consumption impact-cooled surface can be kept relatively small.
  • FIG. 1 a turbine vane according to the invention in longitudinal section
  • FIG. 2 schematically indicated elements of a casting system.
  • the turbine vane 1 according to the FIG. 1 has a profiled airfoil 2 extending along a blade axis 4.
  • the blade 2 is arched and / or curved for suitable influencing of a flowing in an associated turbine unit flow medium.
  • the turbine vane 1 in the embodiment is designed as a guide vane for a gas turbine. This is the end of the in the presentation of the FIG. 1 upper end of the airfoil 2 formed on this one transverse to the blade axis 4 extending platform 6.
  • a hook base 8 is formed, which can be fastened in a manner not shown on a turbine housing.
  • the hook base 8 can be brought into engagement with an adjacent structural element, so that attachment of the turbine guide vane 1 to a carrier body is made possible in a particularly simple manner.
  • the turbine guide vane 1 is provided for use in the second guide vane row of the gas turbine seen in the flow direction of the working medium, so that the hook base 8 is configured both on the front side and on the rear side for a suspension in a structural element.
  • the turbine guide vane 1 is designed for use in a thermally comparatively highly loaded space region of the gas turbine.
  • a consequent functional separation of the absorption of thermal loads and mechanical loads of the turbine guide vane 1 by different structural parts is provided. This is ensured by the separate arrangement of the platform 6 and the hook base 8. Namely, the platform 6 serves exclusively to absorb the thermal load emanating from the hot working medium flowing through the gas turbine, without the platform 6 being exposed to mechanical loads.
  • the turbine vane 1 is also designed to be coolable.
  • the blade 2 is designed in the manner of an internal profiling with a cavity 10, via which a coolant such as cooling air or cooling steam can be guided.
  • the platform 6 has a comparatively thin-walled platform floor 12 which, in its planar configuration, acts essentially as a radiation shield for the heat output delivered by the working medium flowing through the turbines.
  • the platform 6 is designed with a thickened edge or ribbing and has a thickened compared to the platform bottom 12 outer edge 14 , By the outer edge 14 and the platform bottom 12 thus created in the manner of a depression, a so-called platform pocket.
  • the turbine vane 1 is designed such that even while avoiding an undercut with the protruding into the respective space area hook base 8 and thus under the leadership of the respective hook base 8, the reversible introduction of a molding in the space region of the recess formed by the outer edge 14 together with the platform bottom 12 is made possible.
  • the side wall 16 of the outer edge 14 facing the blade axis 4 is guided in a bevelled manner with respect to the blade axis 4.
  • the angle ⁇ characterizing this bevel is too more than 10 ° and less than 80 °, namely in the exemplary embodiment to about 45 ° selected.
  • the outer edge 14 thus has, in its bottom region facing the platform bottom 12, a comparatively broad cross-section which increasingly tapers in the direction of its end 18 facing away from the platform bottom 12. Especially in this upper end region of the outer edge 14 is thus reliably cooled due to the relatively minor amount of material with relatively simple means and in particular using only a limited amount of coolant.
  • the outer edge 14 is provided in this area with a number of acted upon by a coolant cooling holes 20. These open in their outlet in a common cooling gap 22nd
  • the turbine vane 1 is designed for high thermal capacity with high mechanical strength.
  • the turbine guide vane 1 is designed in monocrystalline construction.
  • the turbine vane 1 is using a in the FIG. 2 only partially illustrated casting system 30 produced by casting.
  • the casting system 30, which is used essentially in the creation of a wax model for the turbine guide vane 1, comprises as a basic element a non-illustrated mold. In this mold, a number of mask elements are positioned, which leave in their entirety a cavity corresponding to the contour of the turbine blade 1 to be produced, which can be filled in a subsequent step with pourable wax.
  • the casting system 30 comprises, in particular, a first mask element 32, which can be used in the manner of a circumferential slide.
  • the first mask element 32 comprises, in addition to other structure-determining form elements, a recess 34 which predetermines the interface of the platform floor 12.
  • the first mask element 32 is supplemented for final shaping of the platform 6 by a second mask element 36, which is formed substantially flat and slidably guided in the first mask member 32.
  • pouring position protrudes the second mask member 36 into the recess 34 of the first mask member 32 in that only one adapted to the final shape of the platform 6 space area is released. This thus provides both the platform floor 12 and the outer edge 14 of the platform 6.
  • the second mask element 36 is at an angle ⁇ of about 45 ° to the interface of the Platform bottom 12 predetermining recess 34 tilted, arranged by the double arrow 38 direction arranged displaceable. In this way, a removal of the second mask member 36 from the wax model of the turbine blade 1 after its casting by simply moving in the direction of the double arrow 38 allows, without this being affected by the hook base 8.
  • the hook base 8 is dimensioned in such a way for its lateral extent that it does not affect the space indicated by the line 40 for the second mask member 36.
  • the second mask element 36 also has an end face 44 tilted at an angle ⁇ of approximately 45 ° in the exemplary embodiment, which together with the recess 34 of the first mask element forms a casting mask for forms the platform floor 12.
  • the second mask element 36 can first be removed by simple displacement of the resulting molded body by such a configuration and the interaction of the first mask member 32 with the second mask member 36, without this by an undercut, for example with the hook base 8 would be disabled. Subsequently, the first mask element 32 can be removed by displacement in the direction indicated by the double arrow 46 circumferential direction, ie substantially parallel to the orientation of the platform floor 12.
  • a reliable casting of the wax model of the turbine vane 1 is made possible only using sliders and without the use of "lost inserts", so that in a particularly favorable manner, the production of monocrystalline turbine vanes 1 is possible.
  • a nose-like projection 50 of the platform 6, which delimits the platform pocket, remains behind in the area of the blade axis 4.
  • This projection 50 is used in a particularly advantageous manner as a support or fixing means for a baffle cooling plate use.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP02001265A 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel Expired - Lifetime EP1331361B1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50214427T DE50214427D1 (de) 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel
EP02001265A EP1331361B1 (de) 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel
AT02001265T ATE467749T1 (de) 2002-01-17 2002-01-17 Gegossene turbinenleitschaufel mit hakensockel
JP2003005500A JP4303480B2 (ja) 2002-01-17 2003-01-14 タービン翼とその鋳造装置
CNB031075010A CN100447374C (zh) 2002-01-17 2003-01-17 透平机叶片以及制造透平机叶片的铸造组件
US10/345,947 US6923620B2 (en) 2002-01-17 2003-04-30 Turbine blade/vane and casting system for manufacturing a turbine blade/vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02001265A EP1331361B1 (de) 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel

Publications (2)

Publication Number Publication Date
EP1331361A1 EP1331361A1 (de) 2003-07-30
EP1331361B1 true EP1331361B1 (de) 2010-05-12

Family

ID=8185294

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02001265A Expired - Lifetime EP1331361B1 (de) 2002-01-17 2002-01-17 Gegossene Turbinenleitschaufel mit Hakensockel

Country Status (6)

Country Link
US (1) US6923620B2 (ja)
EP (1) EP1331361B1 (ja)
JP (1) JP4303480B2 (ja)
CN (1) CN100447374C (ja)
AT (1) ATE467749T1 (ja)
DE (1) DE50214427D1 (ja)

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Publication number Priority date Publication date Assignee Title
CA2535263C (en) 2003-08-14 2012-03-06 Lg Electronics Inc. Recording medium, method of configuring control information thereof, recording and reproducing method using the same, and apparatus thereof
EP1591625A1 (en) * 2004-04-30 2005-11-02 ALSTOM Technology Ltd Gas turbine blade shroud
US7819629B2 (en) * 2007-02-15 2010-10-26 Siemens Energy, Inc. Blade for a gas turbine
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8739404B2 (en) 2010-11-23 2014-06-03 General Electric Company Turbine components with cooling features and methods of manufacturing the same
EP3147452B1 (en) * 2015-09-22 2018-07-25 Ansaldo Energia IP UK Limited Turboengine blading member
CN107755637A (zh) * 2017-09-18 2018-03-06 东方电气集团东方汽轮机有限公司 一种消除定向凝固铸件缺陷的方法
US10544699B2 (en) * 2017-12-19 2020-01-28 Rolls-Royce Corporation System and method for minimizing the turbine blade to vane platform overlap gap
CN113560544B (zh) * 2021-06-28 2022-10-25 深圳市万泽中南研究院有限公司 一种定向叶片及其柱状晶组织优化方法
CN115055645B (zh) * 2022-06-07 2023-10-17 中国航发航空科技股份有限公司 导向器叶片毛坯的浇注系统

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US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part
US4902198A (en) 1988-08-31 1990-02-20 Westinghouse Electric Corp. Apparatus for film cooling of turbine van shrouds
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EP0789806B1 (en) * 1994-10-31 1998-07-29 Westinghouse Electric Corporation Gas turbine blade with a cooled platform
CA2262064C (en) * 1998-02-23 2002-09-03 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade platform
EP1073827B1 (de) * 1998-04-21 2003-10-08 Siemens Aktiengesellschaft Turbinenschaufel
DE10004714C2 (de) * 2000-02-03 2002-03-14 Karl Walter Formen Fa Vorrichtung zum Gießen eines Formteils
EP1145784A1 (de) * 2000-04-12 2001-10-17 Siemens Aktiengesellschaft Gussvorrichtung, insbesondere zur Herstellung von Turbinenschaufeln
DE10024278A1 (de) * 2000-05-17 2001-11-22 Weidmueller Interface Kunststoffgehäuse mit einer Aufnahme sowie Verfahren zu dessen Herstellung
US6454526B1 (en) * 2000-09-28 2002-09-24 Siemens Westinghouse Power Corporation Cooled turbine vane with endcaps
DE10060141A1 (de) * 2000-12-04 2002-06-06 Alstom Switzerland Ltd Verfahren zur Herstellung eines Gussteils, Modellform und keramischer Einsatz zum Gebrauch in diesem Verfahren

Also Published As

Publication number Publication date
US20050111963A1 (en) 2005-05-26
CN1451846A (zh) 2003-10-29
JP2003232205A (ja) 2003-08-22
US6923620B2 (en) 2005-08-02
ATE467749T1 (de) 2010-05-15
CN100447374C (zh) 2008-12-31
JP4303480B2 (ja) 2009-07-29
DE50214427D1 (de) 2010-06-24
EP1331361A1 (de) 2003-07-30

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