EP1219389A1 - Method for smoothing the external surface of a gas turbine blade - Google Patents
Method for smoothing the external surface of a gas turbine blade Download PDFInfo
- Publication number
- EP1219389A1 EP1219389A1 EP00128574A EP00128574A EP1219389A1 EP 1219389 A1 EP1219389 A1 EP 1219389A1 EP 00128574 A EP00128574 A EP 00128574A EP 00128574 A EP00128574 A EP 00128574A EP 1219389 A1 EP1219389 A1 EP 1219389A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine blade
- smoothing
- medium
- grinding
- 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- Withdrawn
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B31/00—Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work and/or the abrasive material is loose; Accessories therefor
- B24B31/003—Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work and/or the abrasive material is loose; Accessories therefor whereby the workpieces are mounted on a holder and are immersed in the abrasive material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B51/00—Arrangements for automatic control of a series of individual steps in grinding a workpiece
Definitions
- the invention relates to a method for smoothing the surface a gas turbine blade, in particular a gas turbine blade with a corrosion protection layer.
- DE-A-39 18 824 and US-A-5,105,525 show an iron soleplate, which is a particularly scratch-resistant, well slidable and easy to clean surface.
- the soleplate is coated with a nickel hard alloy and in one Drag-sanding process ground and polished.
- US-A-4,321,310 describes a process for producing a Coating described on a gas turbine blade.
- the Gas turbine blade has a base made of a cobalt base or nickel-based superalloy.
- an adhesion promoter layer of the MCrAlY type is applied on this basic material.
- M denotes a combination, for example of the metals nickel and cobalt.
- Cr stands for chromium and Al for Aluminum and Y for yttrium.
- On this adhesive layer a ceramic layer made of zirconium oxide is applied, which grew up in the form of a stem, the stem directed essentially perpendicular to the surface of the base body are.
- the adhesive layer is polished until there is a surface roughness of about 1 ⁇ m.
- US-A-5,683,825 also discloses an application method a thermal barrier coating on a component of a gas turbine out.
- Low pressure plasma spraying is applied to a base body a NiCrAlY adhesion promoter layer applied.
- the surface of the adhesion promoter layer is polished, so that it has a surface roughness of about 2 ⁇ m having.
- the bonding agent layer thus polished is coated with a vapor deposition process (PVD, Physical Vapor Deposition) a ceramic thermal barrier coating with yttrium stabilized Zirconia applied.
- PVD Physical Vapor Deposition
- the thermal barrier coating here with the so-called electron beam PVD process applied.
- the thermal barrier coating can also by means of Plasma spraying can be applied.
- US-A-5,498,484 also describes the application of a Thermal insulation layer on an adhesion promoter layer of a component described a gas turbine.
- the average surface roughness the adhesion promoter layer is covered with at least 10 ⁇ m specified.
- US-A-5,645,893 relates to a coated component with a Base body made of a super alloy and with a Adhesion promoter layer and a heat insulation layer.
- the adhesion promoter layer has a platinum aluminide and one on it subsequent thin oxide layer.
- the thin oxide layer has alumina. Bordered by this oxide layer the thermal insulation layer, which by means of the electron beam PVD process is applied. It is stabilized with yttrium Zirconium oxide applied to the adhesive layer. Before the adhesive layer is applied, the Surface of the base body using a coarse sandblasting process cleaned. For material removal processing of the Aluminum oxide sand is used for the base body.
- the object of the invention is to provide a method for smoothing the Specify the surface of a gas turbine blade that is particularly useful efficient and cost effective way to a sufficient smooth surface of the gas turbine blade leads.
- this object is achieved by specifying a Process for smoothing the surface of a gas turbine blade, in which the gas turbine blade with a towing device through an abrasive medium along a towing direction is being towed.
- Figure 1 shows a gas turbine blade 1 with an airfoil 3, a platform 5 and a blade root 7.
- the airfoil 3 has a pressure side 9 and a suction side 11 on an entry edge 13 and a trailing edge 12 contiguous.
- the airfoil 3 is like that Airfoil 3 facing surface of the platform 5, with provided a corrosion protection layer 15.
- the corrosion protection layer 15 is a metallic alloy of the class MCrAlY. Open on the surface 14 of the airfoil 3 Cooling ducts 17.
- the gas turbine blade 1 contains a hot gas exposed to very high temperatures. Protection against corrosion and oxidation by the hot gas serves the corrosion protection layer 15.
- ceramic thermal barrier coating 19 may be applied.
- the corrosion protection layer 15 also serves as an adhesion promoter layer between the base of the gas turbine blade 1 and the ceramic thermal barrier layer 19.
- the anti-corrosion layer 15 are smoothed. An efficient one and inexpensive smoothing process is based on Figure 2 explained in more detail.
- the cooling medium 18 forms one protective cooling film on the surface 14.
- FIG 2 shows a grinding device 21.
- a first annular container 23 is a liquid grinding medium 27 filled.
- second container 25 is a second liquid abrasive medium 29 filled.
- the grinding medium 27 contains an emulsion Abrasive discs of a certain medium size.
- the second grinding medium 29 contains second emulsion Abrasives that are smaller on average than the abrasives of the grinding medium 27.
- a swivel arm 31 is arranged, which along a Swivel direction 32 is pivotable. Along the swivel direction 32 is the swivel arm 31 from a position above the first container 23 into a position above the second container 25 swiveling.
- a towing device on the swivel arm 31 33 There is a towing device on the swivel arm 31 33 arranged.
- This towing device 33 leads on a support arm 39, a gas turbine blade 1 through the Abrasive medium 27.
- a first axis 35 of movement of the gas turbine blade 1 is a rotation of the Towing device 33 defined. Through this rotation around the The first turbine 35 is the gas turbine blade 1 along a Circular path 43 dragged through the first container 23.
- a second axis 37 is caused by a tilting movement of the support arm 41 and then with the gas turbine blade 1 perpendicular to the defined by the rotational movement about the first axis 35 Drag direction 36 defined.
- a third axis 39 for the Movement of the gas turbine blade 1 is defined by a Rotation of the support arm 41.
- a large number can of course also be attached to the towing device 33 of gas turbine blades 1 are arranged so that a high throughput of gas turbine blades 1 can be achieved.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
Description
Die Erfindung betrifft ein Verfahren zur Glättung der Oberfläche einer Gasturbinenschaufel, insbesondere einer Gasturbinenschaufel mit einer Korrosionsschutzschicht.The invention relates to a method for smoothing the surface a gas turbine blade, in particular a gas turbine blade with a corrosion protection layer.
Die DE-A-39 18 824 und US-A-5,105,525 zeigen eine Bügeleisensohle, die eine besonders kratzfeste, gut gleitfähige und leicht zu reinigende Oberfläche aufweist. Die Bügeleisensohle ist mit einer Nickelhartlegierung beschichtet und in einem Schlepp-Schleif-Verfahren geschliffen und poliert.DE-A-39 18 824 and US-A-5,105,525 show an iron soleplate, which is a particularly scratch-resistant, well slidable and easy to clean surface. The soleplate is coated with a nickel hard alloy and in one Drag-sanding process ground and polished.
In der US-A-4,321,310 ist ein Verfahren zur Herstellung einer Beschichtung auf einer Gasturbinenschaufel beschrieben. Die Gasturbinenschaufel weist einen Grundkörper aus einer Kobaltbasis- oder Nickelbasis-Superlegierung auf. Auf dieses Grundmaterial wird eine Haftvermittlerschicht der Art MCrAlY aufgebracht. Dabei bezeichnet M beispielsweise eine Kombination der Metalle Nickel und Kobalt. Cr steht für Chrom und Al für Aluminium sowie Y für Yttrium. Auf diese Haftvermittlerschicht wird eine keramische Schicht aus Zirkonoxid aufgebracht, die stengelförmig aufgewachsen ist, wobei die Stengel im wesentlichen senkrecht zur Oberfläche des Grundkörpers gerichtet sind. Vor dem Aufbringen der als Wärmedämmschicht dienenden Zirkonoxidschicht auf der Haftvermittlerschicht wird die Haftvermittlerschicht poliert, bis sich eine Oberflächenrauhigkeit von etwa 1 µm einstellt.US-A-4,321,310 describes a process for producing a Coating described on a gas turbine blade. The Gas turbine blade has a base made of a cobalt base or nickel-based superalloy. On this basic material an adhesion promoter layer of the MCrAlY type is applied. M denotes a combination, for example of the metals nickel and cobalt. Cr stands for chromium and Al for Aluminum and Y for yttrium. On this adhesive layer a ceramic layer made of zirconium oxide is applied, which grew up in the form of a stem, the stem directed essentially perpendicular to the surface of the base body are. Before applying the as a thermal barrier coating serving zirconium oxide layer on the adhesion promoter layer the adhesive layer is polished until there is a surface roughness of about 1 µm.
Aus der US-A-5,683,825 geht ebenfalls ein Verfahren zum Aufbringen einer Wärmedämmschicht auf ein Bauteil einer Gasturbine hervor. Auf einen Grundkörper wird durch Niederdruck-Plasmaspritzen eine NiCrAlY-Haftvermittlerschicht aufgebracht. Die Oberfläche der Haftvermittlerschicht wird poliert, so dass diese eine Oberflächenrauhigkeit von etwa 2 µm aufweist. Auf die so polierte Haftvermittlerschicht wird mittels eines Aufdampfverfahrens (PVD, Physical Vapour Deposition) eine keramische Wärmedämmschicht mit Yttrium-stabilisiertem Zirkonoxid aufgebracht. Vorzugsweise wird die Wärmedämmschicht hierbei mit dem sogenannten Elektronenstrahl-PVD-Verfahren aufgebracht. Die Wärmedämmschicht kann auch mittels Plasmaspritzens aufgebracht werden.US-A-5,683,825 also discloses an application method a thermal barrier coating on a component of a gas turbine out. Low pressure plasma spraying is applied to a base body a NiCrAlY adhesion promoter layer applied. The surface of the adhesion promoter layer is polished, so that it has a surface roughness of about 2 µm having. The bonding agent layer thus polished is coated with a vapor deposition process (PVD, Physical Vapor Deposition) a ceramic thermal barrier coating with yttrium stabilized Zirconia applied. Preferably the thermal barrier coating here with the so-called electron beam PVD process applied. The thermal barrier coating can also by means of Plasma spraying can be applied.
In der US-A-5,498 484 wird ebenfalls das Aufbringen einer Wärmedämmschicht auf eine Haftvermittlerschicht eines Bauteils einer Gasturbine beschrieben. Die mittlere Oberflächenrauhigkeit der Haftvermittlerschicht wird mit zumindest über 10 µm angegeben.US-A-5,498,484 also describes the application of a Thermal insulation layer on an adhesion promoter layer of a component described a gas turbine. The average surface roughness the adhesion promoter layer is covered with at least 10 µm specified.
Die US-A-5,645,893 betrifft ein beschichtetes Bauteil mit einem Grundkörper aus einer Superlegierung sowie mit einer Haftvermittlerschicht und einer Wärmedämmschicht. Die Haftvermittlerschicht weist ein Platinaluminid sowie eine daran sich anschließende dünne Oxidschicht auf. Die dünne Oxidschicht weist Aluminiumoxid auf. An diese Oxidschicht grenzt die Wärmedämmschicht an, welche mittels dem Elektronenstrahl-PVD-Verfahren aufgebracht wird. Dabei wird mit Yttrium stabilisiertes Zirkonoxid auf die Haftvermittlerschicht aufgebracht. Vor dem Aufbringen der Haftvermittlerschicht wird die Oberfläche des Grundkörpers mittels eines Grob-Sandstrahlverfahrens gereinigt. Zur materialabtragende Bearbeitung des Grundkörpers wird dabei Aluminiumoxidsand eingesetzt.US-A-5,645,893 relates to a coated component with a Base body made of a super alloy and with a Adhesion promoter layer and a heat insulation layer. The adhesion promoter layer has a platinum aluminide and one on it subsequent thin oxide layer. The thin oxide layer has alumina. Bordered by this oxide layer the thermal insulation layer, which by means of the electron beam PVD process is applied. It is stabilized with yttrium Zirconium oxide applied to the adhesive layer. Before the adhesive layer is applied, the Surface of the base body using a coarse sandblasting process cleaned. For material removal processing of the Aluminum oxide sand is used for the base body.
Aufgabe der Erfindung ist es, ein Verfahren zur Glättung der Oberfläche einer Gasturbinenschaufel anzugeben, das in besonders effizienter und kostengünstiger Weise zu einer ausreichend glatten Oberfläche der Gasturbinenschaufel führt.The object of the invention is to provide a method for smoothing the Specify the surface of a gas turbine blade that is particularly useful efficient and cost effective way to a sufficient smooth surface of the gas turbine blade leads.
Erfindungsgemäß wird diese Aufgabe gelöst durch Angabe eines Verfahrens zur Glättung der Oberfläche einer Gasturbinenschaufel, bei dem die Gasturbinenschaufel mit einer Schleppvorrichtung durch ein Schleifmedium entlang einer Schlepprichtung geschleppt wird.According to the invention, this object is achieved by specifying a Process for smoothing the surface of a gas turbine blade, in which the gas turbine blade with a towing device through an abrasive medium along a towing direction is being towed.
Mit der Erfindung wird also erstmals vorgeschlagen, eine Gasturbinenschaufel
durch ein Schlepp-Schleif-Verfahren zu glätten.
Überraschenderweise ist es mit einem solchen Schlepp-Schleif-Verfahren
möglich, in sehr kurzer Zeit eine qualitativ
hochwertige Glättung der Gasturbinenschaufel-Oberfläche
zu erreichen, und zwar ohne einen inhomogenen Materialabtrag.
Ein solcher inhomogener Materialabtrag wäre eigentlich aufgrund
der komplexen und strömungstechnisch optimierten Form
der Turbinenschaufel bei einem solchen Schlepp-Schleiff-Verfahren
zu erwarten. Ein solcher inhomogener Materialabtrag
würde zudem die Schutzwirkung der MCrAlY-Schicht lokal in unzulässiger
Weise beeinträchtigen.
Die Ausführungen gemäß der Punkte A) bis E) können auch in beliebiger Weise untereinander kombiniert werden.The statements according to points A) to E) can also be made in can be combined with each other in any way.
Die Erfindung wird anhand der Zeichnung beispielhaft näher erläutert. Es zeigen teilweise schematisch und nicht maßstäblich:
- FIG 1
- eine Gasturbinenschaufel und
- FIG 2
- eine Schleifvorrichtung und ein Verfahren zur Oberflächenbehandlung einer Gasturbinenschaufel.
- FIG. 1
- a gas turbine blade and
- FIG 2
- a grinding device and a method for surface treatment of a gas turbine blade.
Gleiche Bezugszeichen haben in den verschiedenen Figuren die gleiche Bedeutung.The same reference numerals have in the different figures same meaning.
Figur 1 zeigt eine Gasturbinenschaufel 1 mit einem Schaufelblatt
3, einer Plattform 5 und einem Schaufelfuß 7. Das
Schaufelblatt 3 weist eine Druckseite 9 und eine Saugseite 11
auf, die an einer Eintrittskante 13 und einer Abströmkante 12
aneinandergrenzen. Das Schaufelblatt 3 ist, wie auch die dem
Schaufelblatt 3 zugewandte Oberfläche der Plattform 5, mit
einer Korrosionsschutzschicht 15 versehen. Die Korrosionsschutzschicht
15 ist eine metallische Legierung der Klasse
MCrAlY. An der Oberfläche 14 des Schaufelblatts 3 münden
Kühlkanäle 17.Figure 1 shows a
Im Betrieb ist die Gasturbinenschaufel 1 einem Heißgas mit
sehr hoher Temperatur ausgesetzt. Dem Schutz vor Korrosion
und Oxidation durch das Heißgas dient die Korrosionsschutzschicht
15. Für einen Einsatz bei besonders hohen Temperaturen
kann auf die Korrosionsschutzschicht 15 auch noch eine
keramische Wärmedämmschicht 19 aufgebracht sein. In diesem
Fall dient die Korrosionsschutzschicht 15 auch als eine Haftvermittlerschicht
zwischen dem Grundkörper der Gasturbinenschaufel
1 und der keramischen Wärmedämmschicht 19. Vor dem
Aufbringen einer solchen keramischen Wärmedämmschicht 19 muss
die Korrosionsschutzschicht 15 geglättet werden. Ein effizienter
und kostengünstiger Glättungsprozess wird anhand von
Figur 2 näher erläutert. Zur Kühlung der Gasturbinenschaufel
1 wird ein Kühlmedium 18, vorzugsweise Kühlluft, aus den
Kühlkanälen 17 herausgeleitet. Das Kühlmedium 18 bildet einen
schützenden Kühlfilm auf der Oberfläche 14.In operation, the
Figur 2 zeigt eine Schleifvorrichtung 21. In einem ersten
ringförmigen Behälter 23 ist ein flüssiges Schleifmedium 27
eingefüllt. In einem neben dem ersten Behälter 23 angeordneten
zweiten Behälter 25 ist ein zweites flüssiges Schleifmedium
29 eingefüllt. Das Schleifmedium 27 enthält emulsionsartig
Schleifkörper einer bestimmten mittleren Größe. Das
zweite Schleifmedium 29 enthält emulsionsartig zweite
Schleifkörper, die im Mittel kleiner sind als die Schleifkörper
des Schleifmediums 27. Zwischen und über den Behältern
23, 25 ist ein Schwenkarm 31 angeordnet, der entlang einer
Schwenkrichtung 32 schwenkbar ist. Entlang der Schwenkrichtung
32 ist der Schwenkarm 31 von einer Position oberhalb des
ersten Behälters 23 in eine Position oberhalb des zweiten Behälters
25 schwenkbar. An dem Schwenkarm 31 ist eine Schleppvorrichtung
33 angeordnet. Diese Schleppvorrichtung 33 führt
an einem Trägerarm 39 eine Gasturbinenschaufel 1 durch das
Schleifmedium 27. Eine erste Achse 35 der Bewegung der Gasturbinenschaufel
1 wird dabei durch eine Rotation der
Schleppvorrichtung 33 definiert. Durch diese Rotation um die
erste Achse 35 wird die Gasturbinenschaufel 1 entlang einer
Kreisbahn 43 durch den ersten Behälter 23 geschleppt. Eine
zweite Achse 37 wird durch eine Kippbewegung des Trägerarms
41 und dann mit der Gasturbinenschaufel 1 senkrecht zu der
durch die Rotationsbewegung um die erste Achse 35 definierten
Schlepprichtung 36 definiert. Eine dritte Achse 39 für die
Bewegung der Gasturbinenschaufel 1 ist definiert durch eine
Rotation des Trägerarms 41.Figure 2 shows a grinding
Durch die Geschwindigkeit der Schleppbewegung entlang der
Schlepprichtung 36 kann die Stärke des Materialabtrags eingestellt
werden. Durch die relativen Geschwindigkeiten der Bewegungen
um die Achsen 35, 37, 39 kann die Homogenität des
Materialabtrages auf der Oberfläche 14 der Gasturbinenschaufel
1 eingestellt werden.By the speed of the towing movement along the
Nach einer ausreichenden Glättung im Schleifmedium 27 wird
die Schleppvorrichtung 33 mit dem Schwenkarm 31 über den
zweiten Behälter 25 geschwenkt. Hier erfolgt ein analoger
Schleifprozess, wobei allerdings im zweiten Schleifmedium 29
ein Poliervorgang erfolgt, durch den eine besonders hohe
Glättung erreichbar ist.After sufficient smoothing in the grinding
An der Schleppvorrichtung 33 können natürlich auch eine Vielzahl
von Gasturbinenschaufeln 1 angeordnet werden, so dass
ein hoher Durchsatz an Gasturbinenschaufeln 1 erreichbar ist.A large number can of course also be attached to the towing
Claims (10)
Priority Applications (9)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00128574A EP1219389A1 (en) | 2000-12-27 | 2000-12-27 | Method for smoothing the external surface of a gas turbine blade |
EP01989541A EP1345732B1 (en) | 2000-12-27 | 2001-11-29 | Method for smoothing the surface of a gas turbine blade |
DE50106828T DE50106828D1 (en) | 2000-12-27 | 2001-11-29 | METHOD FOR SMOOTING THE SURFACE OF A GAS TURBINE BLADE |
JP2002552713A JP2004516159A (en) | 2000-12-27 | 2001-11-29 | Gas turbine blade surface smoothing method |
CNA01820743XA CN1481293A (en) | 2000-12-27 | 2001-11-29 | Method for smoothing surface of gas turbine blade |
US10/451,911 US7014533B2 (en) | 2000-12-27 | 2001-11-29 | Method for smoothing the surface of a gas turbine blade |
PCT/EP2001/013982 WO2002051586A1 (en) | 2000-12-27 | 2001-11-29 | Method for smoothing the surface of a gas turbine blade |
US11/185,821 US7144302B2 (en) | 2000-12-27 | 2005-07-21 | Method for smoothing the surface of a gas turbine blade |
US11/238,059 US7118464B2 (en) | 2000-12-27 | 2005-09-29 | Apparatus for smoothing the surface of a gas turbine blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00128574A EP1219389A1 (en) | 2000-12-27 | 2000-12-27 | Method for smoothing the external surface of a gas turbine blade |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1219389A1 true EP1219389A1 (en) | 2002-07-03 |
Family
ID=8170838
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00128574A Withdrawn EP1219389A1 (en) | 2000-12-27 | 2000-12-27 | Method for smoothing the external surface of a gas turbine blade |
EP01989541A Expired - Lifetime EP1345732B1 (en) | 2000-12-27 | 2001-11-29 | Method for smoothing the surface of a gas turbine blade |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01989541A Expired - Lifetime EP1345732B1 (en) | 2000-12-27 | 2001-11-29 | Method for smoothing the surface of a gas turbine blade |
Country Status (6)
Country | Link |
---|---|
US (2) | US7014533B2 (en) |
EP (2) | EP1219389A1 (en) |
JP (1) | JP2004516159A (en) |
CN (1) | CN1481293A (en) |
DE (1) | DE50106828D1 (en) |
WO (1) | WO2002051586A1 (en) |
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Also Published As
Publication number | Publication date |
---|---|
US7118464B2 (en) | 2006-10-10 |
JP2004516159A (en) | 2004-06-03 |
US20040097170A1 (en) | 2004-05-20 |
CN1481293A (en) | 2004-03-10 |
EP1345732B1 (en) | 2005-07-20 |
US7014533B2 (en) | 2006-03-21 |
US20060194526A1 (en) | 2006-08-31 |
WO2002051586A1 (en) | 2002-07-04 |
DE50106828D1 (en) | 2005-08-25 |
EP1345732A1 (en) | 2003-09-24 |
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