EP0954680B1 - Aube de turbine et son utilisation dans un systeme de turbine a gaz - Google Patents

Aube de turbine et son utilisation dans un systeme de turbine a gaz Download PDF

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Publication number
EP0954680B1
EP0954680B1 EP97949947A EP97949947A EP0954680B1 EP 0954680 B1 EP0954680 B1 EP 0954680B1 EP 97949947 A EP97949947 A EP 97949947A EP 97949947 A EP97949947 A EP 97949947A EP 0954680 B1 EP0954680 B1 EP 0954680B1
Authority
EP
European Patent Office
Prior art keywords
wall
cooling
turbine blade
region
outlet
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
EP97949947A
Other languages
German (de)
English (en)
Other versions
EP0954680A1 (fr
Inventor
Michael Haendler
Michael Scheurlen
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
Publication of EP0954680A1 publication Critical patent/EP0954680A1/fr
Application granted granted Critical
Publication of EP0954680B1 publication Critical patent/EP0954680B1/fr
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
    • 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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the invention relates to a turbine blade with one of a hot gas flow around wall structure, at least in some areas an outer wall around which the hot gas can flow, one Inner wall and one arranged between the inner wall and outer wall Has cooling area for the flow of a cooling fluid.
  • the invention further relates to the use of a such a turbine blade in a gas turbine plant.
  • a gas turbine vane with a guide from Cooling gas for cooling them is described in US Pat. No. 5,419,039.
  • the guide vane is designed as a casting or composed of two castings. She points inside a supply of cooling air from the compressor to the assigned Gas turbine plant on. In their the hot gas flow exposed to the gas turbine, enclosing the air supply Wall structure are cast-in cool bags that are open on one side intended.
  • the cooler bags are on the outside of the wall structure both in the flow direction of the hot gas and perpendicular to the direction of flow of the hot gas along the Main direction of expansion of the guide vane arranged. In each Cooling bag flows from the cooling air supply over a plurality of holes in the wall structure cooling air into the cooler bag on.
  • Cooling bag can be a base or unspecified can use several unspecified sockets for improvement the heat conduction can be provided.
  • DE 22 41 192 B2 includes a hollow gas turbine blade described an operation.
  • This insert serves as a partition in the cavity enclosed by the turbine blade.
  • the Insert consists of two parts by spacers are spaced from each other.
  • the cavity of the turbine blade is by a longitudinally extending web in an inlet chamber for cooling air and into an outlet chamber divided for cooling air.
  • the two parts of the insert are in the entry chamber made impermeable to cooling air, so that the two parts form a channel, which is only in the inflow area the turbine blade toward the inlet chamber is open.
  • Cooling air therefore flows from the inflow area the turbine blade through the through the two parts of the Insert formed channel in the direction of the trailing edge the turbine blade.
  • the two parts of the insert each have a plurality from openings, through the cooling air into the outlet chamber can leak. Both at the inflow area as well There are openings for at the trailing edge of the turbine blade the exit of cooling air is provided. Through the openings in the inflow area is cooled by film as cooling air escapes reached on the outer surface of the blade wall.
  • Japanese Patent Application Laid-Open 3-130503A is a process for cooling high temperature loaded components of a gas turbine, in particular a gas turbine blade, described using water.
  • the Gas turbine blade is designed as a hollow blade and has a partition on the inside. This partition is via cooling fins with the outer wall of the turbine blade connected. In the interior enclosed by the partition feeds are provided through which under pressure standing water can be blasted into the gap can. The water atomized in this way collides with the partition and thereby cools them. Over the cooling fins by cooling the partition also the outer wall of the Shovel chilled. Both in the outer wall and in the There are a large number of small holes in the partition.
  • the object of the invention is to provide a turbine blade with a specify coolable wall structure. There is another task in using such a turbine blade specify.
  • a turbine blade with a Task directed by hot gas flow around wall structure solved by such a turbine blade that has an inflow area, an outflow area and in between, opposite each other has a pressure side and a suction side and at least in some areas the hot gas can flow around it Outer wall, an inner wall and one between the inner wall and Outside wall arranged cooling area for flow with a Has cooling fluid and the cooling area one of the inner wall assigned inlet and one assigned to the outer wall Has outlet for cooling fluid, wherein in the cooling area of flow around the cooling fluid in a main flow direction Heat transfer elements are arranged one behind the other are thermally connected to the outer wall.
  • the cooling area is preferably designed as a cooling chamber, which is enclosed by the outer wall and the inner wall.
  • the Forming an enclosed cooling chamber increases flexibility in the manufacture of inlet and outlet and gives the Possibility of retrofitting the inlet and the outlet of cooling fluid, especially cooling air, according to the requirements to change the turbine blade.
  • the outlet is preferably through one or more holes manufactured. These holes or funnel-shaped openings are preferably opposite the main flow direction inclined, in particular by an angle of less than 45 °, preferably 20 ° to 30 °.
  • the inclination is preferably chosen so that against a flow of the turbine blade hot gas flowing around an acute angle of, for example also 45 ° is formed. By such a point Angle is the formation of a cooling film on the surface the outer wall favors.
  • the direction of the holes or funnel-shaped openings can also be from one level perpendicular to the main axis of the turbine blade by the same Point out the angle.
  • the outer wall can be made with a smaller one Wall thickness should be formed, which makes them special can be effectively cooled via the heat transfer elements.
  • the cross section of the cooling area between the inner wall and the outer wall is preferred to form a high speed of the cooling fluid low trained, and is particularly in the area the wall thickness of the outer wall. Through a small flow Cross section of the cooling area and a so formed high speed of the cooling fluid become very high Heat transfer numbers reached. It also trains cooling air exiting the cooling area on the outer wall cooling film on the surface exposed to the hot gas Outer wall (film cooling).
  • a plurality of heat transfer elements are preferably along a line arranged in a row, the line opposite the main flow direction, preferably at an angle of 90 °.
  • the main direction of flow is preferred essentially perpendicular to a main axis of the turbine blade, along which the turbine blade is directed is. With a turbine blade that is used as a guide blade the main flow direction corresponds to the Flow direction of a flowing around the turbine blade Hot gas or is the opposite.
  • the heat transfer elements are preferred along the line equally spaced.
  • the heat transfer elements are preferably column-like or platform-like and extend from the outer wall to the inner wall. she can also be firmly connected to the inner wall.
  • the cross section of the heat transfer elements is in each case the heat transfer and adaptable to fluidic requirements, for example circular, polygonal or in the manner of a Flow profile trained.
  • the heat transfer elements directly in the main flow direction consecutive rows are preferred offset from each other, especially by half the distance two heat transfer elements arranged along the line. This primarily ensures that the between two heat transfer elements adjacent along the line sub-flows of the cooling fluid flowing essentially completely with one downstream in the main flow direction Heat transfer element for exchanging thermal energy comes into contact.
  • the outlet can also function as a funnel-shaped, towards Outer surface of the outer wall expanding opening is formed his.
  • the subsequent introduction of such a funnel-shaped Opening is, for example, by eroding or working out feasible using laser beams.
  • the funnel-shaped Opening has a cross section, which for example be circular, rectangular or some other simple geometric Can have shape and possibly also over changes the diameter of the outer wall. Through a funnel shape widening opening is a particularly good film cooling accessible from the outer wall.
  • the inlet is preferably directed along an axis, which is inclined towards the outer wall, especially on the Outer wall is vertical. Incoming through the inlet Cooling fluid therefore strikes the outer wall, causing a additional impingement cooling of the outer wall at least in the area of the inlet is reached.
  • the outlet of a cooling area is preferably between the inlet for cooling air and the inflow area the turbine blade arranged. This ensures a so-called counterflow cooling, in which the cooling fluid inside the cooling area against the flow direction of the the hot gas flow flowing around the turbine blade is. This leads in particular to one used as a guide vane Turbine blade for improved film cooling.
  • the cooling area with counterflow is preferably on the Suction side in the vicinity of the outflow area arranged so that the associated outlet for cooling fluid with respect to the Hot gas flow upstream of the lowest area Pressure level of the flowing along the suction side Hot gas lies. This is particularly advantageous aerodynamically, the flow of hot gas in the outflow area is largely unaffected by escaping cooling fluid.
  • a cooling area between an outer wall and an inner wall is arranged as a whole by casting in one Work step can be produced.
  • the turbine blade also contain two or more cast parts, using suitable methods (joining processes) according to Pouring be firmly connected.
  • the inlet is made by casting.
  • the turbine blade preferably has a variety of cooling areas both along their major axis as well as in a plane perpendicular to the main axis.
  • a stationary guide vane Gas turbine can be on the suction side as well as on the Pressure side three times three cooling chambers and depending on what can be achieved Heat transfer also more or less cooling chambers exhibit.
  • a geometrically complex blade preferably has less on the suction side and pressure side Cooling chambers as a comparable guide vane.
  • the task aimed at using the turbine blade is solved in that the turbine blade as a moving blade or guide vane in a gas turbine plant, in particular in the gas turbine, in the temperatures of clearly over 1000 ° C of the hot gas flowing around the turbine blade occur is used.
  • Turbine blade 1 a guide blade of a gas turbine, is shown.
  • This has a wall structure 2 with an inflow area 8, an outflow area 9 and a pressure side 10 and a suction side 11, which are arranged opposite each other are.
  • In the wall structure 2 are both on the suction side 11 as well as three on the pressure side 10 each as cooling chambers 20 formed hollow cooling areas 5, 5a are provided.
  • This Cooling areas 5, 5a are in the wall structure 2 between one Outer wall 3 and an inner wall 4 arranged.
  • the outer wall 3 is in operation of the gas turbine, not shown, of a hot gas 18 (see Figure 2).
  • the turbine blade 1 is designed as a hollow blade, so that one of the inner wall 4 enclosed cooling air supply 21 is formed is.
  • the cooling areas 5, 5a have a length that is clear larger, for example 10 times larger than their cross section is.
  • the outer wall 3 has a significantly smaller wall thickness than the inner wall 4, for example the wall thickness is the outer wall 3 1.0 mm and the wall thickness of the inner wall 4 1.5 mm.
  • the cross section of the cooling areas 5, 5a lies in the area the wall thickness of the outer wall 3 and is, for example in about 1.0 mm.
  • Over the length of each cooling area 5, 5a are a plurality, preferably over five, heat transfer elements 7 arranged. From the cooling air supply 21 leads into each cooling area 5, 5a, a respective inlet 15 into, which is preferably as a bore or a plurality formed from holes or cast and the required Cooling capacity is adjusted.
  • the inlet 15 is along directed an axis 22 which is substantially perpendicular stands on the outer wall 3. This will create an additional one Impact cooling of the outer wall 3 is achieved in the area of the inlet 15.
  • a respective outlet leads from each cooling area 5, 5a 16 to the outer surface of the wall structure 2.
  • the outlet 16 is also preferably through a bore 17 or more Bores 17, depending on the cooling capacity requirement; executed.
  • the outlet 16 can also e.g. by eroding or Machining with a laser beam and be funnel-shaped expand towards the flow of hot gas 18.
  • the Bores 17 are opposite to the flow direction of the Turbine blade 1 hot gas 18 flowing past under a acute angle inclined, which is particularly favorable Form cooling air film on the outer surface of wall structure 2 can.
  • the outlet is in particular on the suction side 11 16 arranged closer to the inflow area 8 than that of the same Cooling chamber 20 assigned inlet 15. This will Cooling air 6 in counterflow to the flow of hot gas 18 in the Cooling chamber 20 out.
  • FIG. 2 and FIG. 3 show an enlarged representation of the wall structure 2 in the area of a cooling chamber 20.
  • the cooling chamber 20 is flowed through by cooling fluid 6, in particular cooling air, along a main flow direction 12.
  • the main flow direction 12 is essentially perpendicular to the main axis 19 of the turbine blade 1.
  • the bores 17 of the outlet 16 can be directed out of a plane perpendicular to the main axis 19.
  • the heat transfer elements 7 are designed as columns with a circular cross section and a diameter d 1 . They are thermally connected to both the inner wall 4 and the outer wall 3.
  • Several heat transfer elements 7 are each arranged along a line 14, which is perpendicular to the main flow direction 12.
  • a plurality of rows 13a, 13b are provided along the main flow direction 12.
  • the distance d 2 between two adjacent rows 13a, 13b is approximately the same or slightly less than the distance d 3 between adjacent heat transfer elements 7 of a row 13a, 13b.
  • the diameter d 1 of a heat transfer element 7 is, for example, 1.0 mm
  • the distance d 2 between two rows 13a, 13b is approximately between 1.5 mm and 1.75 mm
  • the distance d 3 between two heat transfer elements 7 is approximately 1.75 mm
  • the diameter d 1 and the distances d 2 , d 3 can vary from line 14 to line 14, according to the desired heat transfer.
  • the heat transfer elements 7 of immediately adjacent rows 13a, 13b are offset from one another along the respective line 14 by approximately half the distance d 3 .
  • the alternating arrangement of the heat transfer elements 7 thus increases the contact time for heat transfer between the cooling air 6 and the heat transfer element 7 connected to the outer wall 3, so that particularly high heat transfer and thus cooling of the outer wall 3 takes place.
  • the effectiveness of the cooling is further enhanced by the fact that the outer wall 3 is designed with a small wall thickness.
  • the supporting inner wall 4, which is not directly exposed to the hot gas 18, is also cooled.
  • the invention is characterized by a turbine blade a wall structure in which the cooling function essentially on an outer wall and the supporting function essentially is divided on an inner wall.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (12)

  1. Aube (1) de turbine dotée d'une structure (2) de paroi sur laquelle peut passer un flux de gaz (18) chauds, qui comporte une région (8) d'admission, une région (9) d'échappement et, se faisant face entre ces régions, un côté (10) de refoulement et un côté (11) d'aspiration, et qui comporte au moins sectoriellement une paroi (3) extérieure sur laquelle peut passer le flux de gaz (18) chauds, une paroi (4) intérieure et une région (5) de refroidissement disposée entre la paroi (4) intérieure et la paroi (3) extérieure pour le passage d'un fluide (6) de refroidissement, chaque région (5) de refroidissement comportant une entrée (15), traversant la paroi (4) intérieure, et une sortie (16), traversant la paroi (3) extérieure, pour le fluide (6) de refroidissement,
    caractérisée en ce que des éléments (7) de transmission de chaleur sont disposés en succession dans la région (5) de refroidissement, éléments sur lesquels le fluide (6) de refroidissement peut passer dans une direction (12) principale d'écoulement et qui sont reliés thermiquement à la paroi (3) extérieure, et la région (5) de refroidissement est réalisée sous la forme d'une chambre (20) de refroidissement enfermée par la paroi (3) extérieure et la paroi (4) intérieure.
  2. Aube (1) de turbine suivant la revendication 1, caractérisée en ce que la sortie (16) est réalisée par un perçage (17) ou plusieurs perçages (17).
  3. Aube (1) de turbine suivant la revendication 1 ou 2, caractérisée en ce que plusieurs éléments (7) de transmission de chaleur sont disposés en une rangée (13) le long d'une ligne (14), la ligne (14) étant inclinée par rapport à la direction (12) principale d'écoulement, de préférence d'un angle de 90°.
  4. Aube (1) de turbine suivant la revendication 3, caractérisée en ce que plusieurs rangées (13) sont disposées en parallèle, et les éléments (7) de transmission de chaleur de rangées (13a, 13b) directement voisines sont mutuellement décalés le long de la ligne (14).
  5. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que la paroi (4) intérieure est plus épaisse que la paroi extérieure, notamment du facteur 1,5.
  6. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que la sortie (16) possède une section qui s'élargit depuis la chambre (20) de refroidissement vers la surface de la paroi (3) extérieure qui peut être contournée par le flux de gaz (18) chauds.
  7. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que l'entrée (15) est orientée le long d'un axe (22) qui est incliné par rapport à la paroi (3) extérieure, notamment d'un angle d'environ 90°.
  8. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que, au moins pour une région (5a) de refroidissement, la sortie (16) est disposée entre l'entrée (15) et la région (8) d'admission.
  9. Aube (1) de turbine suivant la revendication 8, caractérisée en ce que la région (5a) de refroidissement est disposée sur le côté (11) d'aspiration, dans l'environnement de la région (9) d'échappement, de telle sorte que la sortie (16) se trouve entre une région ayant le niveau de pression le plus bas lors du contournement par le flux de gaz (18) chauds et la région (8) d'admission.
  10. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que la paroi (3) extérieure, la paroi (4) intérieure et les éléments (7) de transmission de chaleur sont fabriqués en une même étape de moulage.
  11. Aube (1) de turbine suivant l'une des revendications précédentes, qui est une aube mobile ou une aube directrice pour une turbine à gaz.
  12. Utilisation d'une aube (1) de turbine suivant la revendication 11r dans un système à turbine à gaz.
EP97949947A 1996-12-02 1997-11-18 Aube de turbine et son utilisation dans un systeme de turbine a gaz Expired - Lifetime EP0954680B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19649924 1996-12-02
DE19649924 1996-12-02
PCT/DE1997/002702 WO1998025009A1 (fr) 1996-12-02 1997-11-18 Aube de turbine et son utilisation dans un systeme de turbine a gaz

Publications (2)

Publication Number Publication Date
EP0954680A1 EP0954680A1 (fr) 1999-11-10
EP0954680B1 true EP0954680B1 (fr) 2002-02-06

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP97949947A Expired - Lifetime EP0954680B1 (fr) 1996-12-02 1997-11-18 Aube de turbine et son utilisation dans un systeme de turbine a gaz

Country Status (4)

Country Link
EP (1) EP0954680B1 (fr)
JP (1) JP4027430B2 (fr)
DE (1) DE59706345D1 (fr)
WO (1) WO1998025009A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564484A1 (fr) 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Paroi de composant d'un composant à gaz chaud

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6126397A (en) * 1998-12-22 2000-10-03 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
US6254334B1 (en) * 1999-10-05 2001-07-03 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
EP1136651A1 (fr) 2000-03-22 2001-09-26 Siemens Aktiengesellschaft Système de refroidissement pour une aube de turbine à gaz
EP1188902A1 (fr) 2000-09-14 2002-03-20 Siemens Aktiengesellschaft Paroi refroidie par jet
JP4586265B2 (ja) * 2000-12-07 2010-11-24 株式会社Ｉｈｉ タービン翼のトランスピレーション冷却伝熱促進構造
US6511293B2 (en) 2001-05-29 2003-01-28 Siemens Westinghouse Power Corporation Closed loop steam cooled airfoil
US6896487B2 (en) * 2003-08-08 2005-05-24 United Technologies Corporation Microcircuit airfoil mainbody
US7364405B2 (en) * 2005-11-23 2008-04-29 United Technologies Corporation Microcircuit cooling for vanes
EP1930544A1 (fr) * 2006-10-30 2008-06-11 Siemens Aktiengesellschaft Aube de turbine
US9638057B2 (en) 2013-03-14 2017-05-02 Rolls-Royce North American Technologies, Inc. Augmented cooling system
US10683762B2 (en) 2016-07-12 2020-06-16 Rolls-Royce North American Technologies Inc. Gas engine component with cooling passages in wall
CN109139128A (zh) * 2018-10-22 2019-01-04 中国船舶重工集团公司第七0三研究所 一种船用燃气轮机高压涡轮导叶冷却结构

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3003347A1 (de) * 1979-12-20 1981-06-25 BBC AG Brown, Boveri & Cie., Baden, Aargau Gekuehlte wand
US5405242A (en) 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5690472A (en) * 1992-02-03 1997-11-25 General Electric Company Internal cooling of turbine airfoil wall using mesh cooling hole arrangement
US5328331A (en) * 1993-06-28 1994-07-12 General Electric Company Turbine airfoil with double shell outer wall
US5702232A (en) * 1994-12-13 1997-12-30 United Technologies Corporation Cooled airfoils for a gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564484A1 (fr) 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Paroi de composant d'un composant à gaz chaud
US11220915B2 (en) 2018-05-04 2022-01-11 Siemens Energy Global GmbH & Co. KG Component wall of a hot gas component

Also Published As

Publication number Publication date
WO1998025009A1 (fr) 1998-06-11
JP4027430B2 (ja) 2007-12-26
EP0954680A1 (fr) 1999-11-10
DE59706345D1 (de) 2002-03-21
JP2001505275A (ja) 2001-04-17

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