EP0953729B1 - Guide vanes for a turbomachine - Google Patents

Guide vanes for a turbomachine Download PDF

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Publication number
EP0953729B1
EP0953729B1 EP98201416A EP98201416A EP0953729B1 EP 0953729 B1 EP0953729 B1 EP 0953729B1 EP 98201416 A EP98201416 A EP 98201416A EP 98201416 A EP98201416 A EP 98201416A EP 0953729 B1 EP0953729 B1 EP 0953729B1
Authority
EP
European Patent Office
Prior art keywords
platforms
platform
vane
outer shell
shell
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
EP98201416A
Other languages
German (de)
French (fr)
Other versions
EP0953729A1 (en
Inventor
Hung Quac Tran
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.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE69815815T priority Critical patent/DE69815815T2/en
Priority to EP98201416A priority patent/EP0953729B1/en
Priority to PCT/EP1999/003390 priority patent/WO2004074639A1/en
Priority to US09/446,131 priority patent/US6296442B1/en
Publication of EP0953729A1 publication Critical patent/EP0953729A1/en
Application granted granted Critical
Publication of EP0953729B1 publication Critical patent/EP0953729B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00Metal working
    • Y10T29/49Method of mechanical manufacture
    • Y10T29/49316Impeller making
    • Y10T29/4932Turbomachine making
    • Y10T29/49323Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to a turbomachine stator vane comprising arrangements for fixing the stationary vanes which constitute it.
  • the invention is particularly applicable to a rectifier vane of a multi-flow turbojet engine.
  • FR-A-2 321 616 thus shows a fixing of the end platforms of the blades by bolting on the outer shroud.
  • FR-A-2 671 133 a straightening vane in which the blades are fixed by means of a socket placed in abutment on the external surface of the outer shell and crimped on a rod carried by the end of the 'dawn.
  • the object of the invention is to provide an alternative solution facilitating the attachment of the blades of a straightening vane.
  • One of the aims of the invention is also to ensure an anti-rotation blocking of the vanes of the stator vane during assembly and in operation.
  • the object is achieved according to the invention by the fact that the outer shell has a housing whose bottom has a non-planar, spherical or cylindrical surface with radius of curvature R, into which the platforms of the blades are introduced, the cooperating surface of which has a corresponding non-planar, spherical or cylindrical shape, with a greater radius of curvature R + delta R before installation and which is reduced to the radius R under stress, by the action of fixing rivets, assembling the platforms of blades and the outer shell.
  • FIGS. 1 to 7 show an embodiment of a rectifier vane 1 according to the invention and constituting a fixed stage of a multiflow turbojet engine.
  • the stator vane 1 is constituted by a crown of stationary vanes 2 arranged between a radially outer stator ferrule 3 and a radially inner stator ferrule 4.
  • the radially inner end 5 of each vane 2 is introduced into a slot 6 of complementary shape formed in said inner ferrule 4.
  • the blade of the blade 2 carries at its radially outer end a platform 7 which is placed in a housing 8 formed between two shoulders 9 on the inner face of the outer ferrule 3
  • Each platform 7 has holes 10, two in number per platform according to the preferred embodiment shown in the drawings and arranged one on each side of the blade of the blade, in an opposite position along a diagonal of the platform 7.
  • the outer shell 3 has corresponding holes 11.
  • the upper face 12 of the platform 7 has a non-planar shape whose radius of curvature before mounting the blade is R + delta R, as shown diagrammatically in FIG. 2.
  • the realized shape can be spherical or cylindrical.
  • the corresponding bottom 13 of the housing 8 of the outer shell 3 also has a non-planar surface whose radius of curvature R is less than the radius of curvature of the platform before mounting.
  • the shape produced by machining is spherical or cylindrical corresponding to that of the platform.
  • washers 19 can be placed under the rivet heads 14 to avoid a matting effect on the outer shell 3, depending on the materials used.
  • the shoulders 9 formed on each side of the housing 8 on the outer shell 3 guide the mounting of the platforms 7 in the housing 8 and also ensure the anti-rotation blocking of the blades during assembly and in operation.
  • additional arrangements can be made to the stator vane 1 according to the invention.
  • the adjacent edges 15 of the platforms 7 have a chamfer in one direction over half a length and in the other direction over the other half length, as shown in FIG. 8. As a variant, as shown in FIG.
  • a hollow triangular notch 16 can be formed on an edge 15 of the platform while the adjacent edge of the adjacent platform carries the corresponding prominent element 17.
  • an additional rivet can also be added, placed astride the two adjacent edges of neighboring platforms 7, as shown at 18 in FIG. 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention concerne un aubage redresseur de turbomachine comportant des dispositions de fixation des aubes fixes qui le constituent.
L'invention s'applique particulièrement à un aubage redresseur de turboréacteur multiflux.
The present invention relates to a turbomachine stator vane comprising arrangements for fixing the stationary vanes which constitute it.
The invention is particularly applicable to a rectifier vane of a multi-flow turbojet engine.

Diverses solutions ont été mises en oeuvre pour réaliser la fixation des aubes d'un redresseur de turboréacteur. De manière courante, les aubes sont disposées entre une virole statorique radialement extérieure et une virole statorique radialement intérieure qui délimitent le profil de la veine du flux circulant dans le canal.
FR-A-2 321 616 montre ainsi une fixation des plates-formes d'extrémité des aubes par boulonnage sur la virole extérieure.
On connaít également par FR-A-2 671 133 un aubage redresseur où la fixation des aubes est réalisée au moyen d'une douille placée en appui sur la surface externe de la virole extérieure et sertie sur une tige portée par l'extrémité de l'aube.
Le but de l'invention est de fournir une solution alternative facilitant la fixation des aubes d'un aubage redresseur. Un des buts de l'invention est également d'assurer un blocage anti-rotation des aubes de l'aubage redresseur pendant le montage et en fonctionnement.
Le but est atteint selon l'invention par le fait que la virole extérieure comporte un logement dont le fond présente une surface non plane, sphérique ou cylindrique de rayon de courbure R, où sont introduites les plates-formes des aubes dont la surface coopérante présente une forme correspondante non plane, sphérique ou cylindrique, de rayon de courbure supérieur R + delta R avant mise en place et qui est ramené au rayon R sous contrainte, par l'action de rivets de fixation, assemblant les plates formes d'aubes et la virole extérieure.
Various solutions have been implemented to secure the blades of a turbojet engine rectifier. Commonly, the blades are arranged between a radially outer stator ferrule and a radially inner stator ferrule which delimit the profile of the stream from the flow flowing in the channel.
FR-A-2 321 616 thus shows a fixing of the end platforms of the blades by bolting on the outer shroud.
There is also known from FR-A-2 671 133 a straightening vane in which the blades are fixed by means of a socket placed in abutment on the external surface of the outer shell and crimped on a rod carried by the end of the 'dawn.
The object of the invention is to provide an alternative solution facilitating the attachment of the blades of a straightening vane. One of the aims of the invention is also to ensure an anti-rotation blocking of the vanes of the stator vane during assembly and in operation.
The object is achieved according to the invention by the fact that the outer shell has a housing whose bottom has a non-planar, spherical or cylindrical surface with radius of curvature R, into which the platforms of the blades are introduced, the cooperating surface of which has a corresponding non-planar, spherical or cylindrical shape, with a greater radius of curvature R + delta R before installation and which is reduced to the radius R under stress, by the action of fixing rivets, assembling the platforms of blades and the outer shell.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation de l'invention, en référence aux dessins annexés sur lesquels :

  • la figure 1 représente une vue schématique partielle en perspective d'un aubage redresseur de turbomachine conforme à l'invention, en cours de montage ;
  • la figure 2 représente une vue schématique en coupe des surfaces d'assemblage entre plate-forme d'aube et logement ;
  • la figure 3 représente une vue schématique partielle en perspective de l'aubage redresseur représenté sur la figure 1, à l'état assemblé ;
  • la figure 4 représente une vue en coupe par un plan longitudinal d'une aube montée de l'aubage redresseur représenté sur la figure 3 ;
  • la figure 5 représente une vue partielle en coupe transversale de l'aubage redresseur représenté sur la figure 3 ;
  • la figure 6 représente un détail agrandi de la figure 5 ;
  • la figure 7 représente une vue partielle de dessus de l'aubage redresseur représenté sur la figure 3 ;
  • la figure 8 représente selon une vue analogue à celle de la figure 1 un aubage redresseur conforme à l'invention comportant un exemple de disposition de blocage anti-chute des aubes ;
  • la figure 9 représente selon une vue analogue à celle de la figure 8 un autre exemple de blocage anti-chute des aubes d'un redresseur conforme à l'invention ;
  • la figure 10 représente selon une vue analogue à celle de la figure 9 un autre exemple de blocage anti-chute des aubes d'un redresseur conforme à l'invention.
Other characteristics and advantages of the invention will be better understood on reading the description which follows of an embodiment of the invention, with reference to the appended drawings in which:
  • Figure 1 shows a partial schematic perspective view of a turbomachine stator vane according to the invention, during assembly;
  • 2 shows a schematic sectional view of the assembly surfaces between the blade platform and the housing;
  • 3 shows a partial schematic perspective view of the rectifier vane shown in Figure 1, in the assembled state;
  • 4 shows a sectional view through a longitudinal plane of a blade mounted on the straightening vane shown in Figure 3;
  • Figure 5 shows a partial cross-sectional view of the stator vane shown in Figure 3;
  • Figure 6 shows an enlarged detail of Figure 5;
  • Figure 7 shows a partial top view of the stator vane shown in Figure 3;
  • FIG. 8 represents, in a view similar to that of FIG. 1, a straightening vane according to the invention comprising an example of an anti-fall blocking arrangement of the blades;
  • FIG. 9 shows, in a view similar to that of FIG. 8, another example of anti-fall blocking of the blades of a rectifier according to the invention;
  • FIG. 10 shows, in a view similar to that of FIG. 9, another example of blocking the blades of a stator according to the invention against falling.

Les figures 1 à 7 montrent un exemple de réalisation d'un aubage redresseur 1 conforme à l'invention et constituant un étage fixe de turboréacteur multiflux. De manière classique, l'aubage redresseur 1 est constitué par une couronne d'aubes fixes 2 disposées entre une virole statorique radialement extérieure 3 et une virole statorique radialement intérieure 4. L'extrémité radialement intérieure 5 de chaque aube 2 est introduite dans une fente 6 de forme complémentaire ménagée dans ladite virole intérieure 4. La pale de l'aube 2 porte à son extrémité radialement extérieure une plate-forme 7 qui se place dans un logement 8 ménagé entre deux épaulements 9 sur la face intérieure de la virole extérieure 3. Chaque plate-forme 7 comporte des perçages 10, au nombre de deux par plate-forme selon le mode préférentiel de réalisation représenté sur les dessins et disposés un de chaque côté de la pale d'aube, en position opposée selon une diagonale de la plate-forme 7. La virole extérieure 3 comporte des perçages correspondants 11.
De manière remarquable et conforme à l'invention, la face supérieure 12 de la plate-forme 7 présente une forme non plane dont le rayon de courbure avant montage de l'aube est R + delta R, comme schématisé sur la figure 2. La forme réalisée peut être sphérique ou cylindrique. Le fond 13 correspondant du logement 8 de la virole extérieure 3 présente également une surface non plane dont le rayon de courbure R est inférieure au rayon de courbure de la plate-forme avant montage. La forme réalisée par usinage est sphérique ou cylindrique correspondant à celle de la plate-forme.
Après mise en place, les plates-formes 7 des aubes 2 sont fixées sur la virole extérieure 3 au moyen de rivets 14 introduits dans les perçages correspondants 10 et 11. Après la fixation des rivets 14, la face supérieure 12 de la plate-forme 7 et le fond 13 du logement 8 viennent en contact, par déformation des plates-formes dont le rayon R + delta R est rendu égal au rayon R du logement, réalisant ainsi le contact sphérique ou cylindrique suivant la forme adoptée, entre la plate-forme 7 et le logement 8.
Comme représenté sur les figures 5 et 6, des rondelles 19 peuvent être placées sous les têtes de rivets 14 pour éviter un effet de matage sur la virole extérieure 3, suivant les matériaux utilisés.
Les épaulements 9 ménagés de chaque côté du logement 8 sur la virole extérieure 3 permettent de guider le montage des plates-formes 7 dans le logement 8 et assurent également le blocage anti-rotation des aubes pendant le montage et en fonctionnement.
Afin d'éviter la chute de l'aube 2 de redresseur lors du montage ou en cas de perte des rivets 14, des dispositions complémentaires peuvent être apportées à l'aubage redresseur 1 conforme à l'invention. Les bords adjacents 15 des plates-formes 7 ont un chanfrein dans un sens sur une demi-longueur et dans l'autre sens sur l'autre demi-longueur, comme représenté sur la figure 8.
En variante, comme représenté sur la figure 9, une encoche 16 triangulaire en creux peut être ménagée sur un bord 15 de plate-forme tandis que le bord adjacent de plate-forme voisine porte l'élément proéminent correspondant 17.
En variante, un rivet supplémentaire peut également être ajouté, placé à cheval sur les deux bords adjacents de plates-formes voisines 7, comme représente en 18 sur la figure 10.
FIGS. 1 to 7 show an embodiment of a rectifier vane 1 according to the invention and constituting a fixed stage of a multiflow turbojet engine. Conventionally, the stator vane 1 is constituted by a crown of stationary vanes 2 arranged between a radially outer stator ferrule 3 and a radially inner stator ferrule 4. The radially inner end 5 of each vane 2 is introduced into a slot 6 of complementary shape formed in said inner ferrule 4. The blade of the blade 2 carries at its radially outer end a platform 7 which is placed in a housing 8 formed between two shoulders 9 on the inner face of the outer ferrule 3 Each platform 7 has holes 10, two in number per platform according to the preferred embodiment shown in the drawings and arranged one on each side of the blade of the blade, in an opposite position along a diagonal of the platform 7. The outer shell 3 has corresponding holes 11.
Remarkably and in accordance with the invention, the upper face 12 of the platform 7 has a non-planar shape whose radius of curvature before mounting the blade is R + delta R, as shown diagrammatically in FIG. 2. The realized shape can be spherical or cylindrical. The corresponding bottom 13 of the housing 8 of the outer shell 3 also has a non-planar surface whose radius of curvature R is less than the radius of curvature of the platform before mounting. The shape produced by machining is spherical or cylindrical corresponding to that of the platform.
After installation, the platforms 7 of the vanes 2 are fixed to the outer shell 3 by means of rivets 14 introduced into the corresponding holes 10 and 11. After the rivets 14 have been fixed, the upper face 12 of the platform 7 and the bottom 13 of the housing 8 come into contact, by deformation of the platforms whose radius R + delta R is made equal to the radius R of the housing, thus achieving spherical or cylindrical contact according to the adopted form, between the platform form 7 and housing 8.
As shown in Figures 5 and 6, washers 19 can be placed under the rivet heads 14 to avoid a matting effect on the outer shell 3, depending on the materials used.
The shoulders 9 formed on each side of the housing 8 on the outer shell 3 guide the mounting of the platforms 7 in the housing 8 and also ensure the anti-rotation blocking of the blades during assembly and in operation.
In order to avoid the fall of the stator vane 2 during assembly or in the event of loss of the rivets 14, additional arrangements can be made to the stator vane 1 according to the invention. The adjacent edges 15 of the platforms 7 have a chamfer in one direction over half a length and in the other direction over the other half length, as shown in FIG. 8.
As a variant, as shown in FIG. 9, a hollow triangular notch 16 can be formed on an edge 15 of the platform while the adjacent edge of the adjacent platform carries the corresponding prominent element 17.
As a variant, an additional rivet can also be added, placed astride the two adjacent edges of neighboring platforms 7, as shown at 18 in FIG. 10.

Claims (5)

  1. Turbomachine stator vane set consisting of a ring of vanes (2) located between a radially outer stator shell (3) and a radially inner stator shell (4), the inner end (5) of each vane (2) being placed in a slot (6) of complementary shape formed in said inner shell (4), and the outer end of each vane (2) bearing a platform (7) which is fixed to the interior face of the outer shell (3), characterized in that the outer shell (3) has a housing (8), the bottom (13) of which has a non-planar surface, which is spherical or cylindrical with a radius of curvature R, into which are inserted the platforms (7) of the vanes (2), the cooperating surface (12) of which has a corresponding non-planar surface which is spherical or cylindrical with a larger radius of curvature R + delta R prior to fitting and which is reduced to the radius R under stress, by the action of fastening rivets (14) used to assemble the vane platforms (7) with the outer shell (3).
  2. Turbomachine stator vane set according to Claim 1, characterized in that the housing (8) is delimited on the interior face of the outer shell (3) by two shoulders (9) which provide guidance for mounting the platforms (7) and immobilize the vanes (2) to prevent them from rotating during mounting and in operation, and the fastening rivets (14) number two per platform (7), each arranged on each side of the vane (2) in opposed positions along a diagonal of the platform (7).
  3. Turbomachine stator vane set according to either of Claims 1 and 2, characterized in that the edges (15) of the platforms (7) are chamfered in one direction along half of their length and in the other direction along the other half of their length and such that the chamfered platforms complement each other along adjacent edges (15) of two platforms (7) which are next to each other.
  4. Turbomachine stator vane set according to either of Claims 1 and 2, characterized in that a recessed triangular notch (16) is formed on one edge (15) of each platform (7), and the adjacent edge of the platform (7) next to it bears a corresponding protruding element (17).
  5. Turbomachine stator vane set according to either of Claims 1 and 2, characterized in that an additional rivet is placed astride the two adjacent edges (15) of two platforms (7) which are next to each other.
EP98201416A 1998-05-01 1998-05-01 Guide vanes for a turbomachine Expired - Lifetime EP0953729B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE69815815T DE69815815T2 (en) 1998-05-01 1998-05-01 Guide blades for a turbomachine
EP98201416A EP0953729B1 (en) 1998-05-01 1998-05-01 Guide vanes for a turbomachine
PCT/EP1999/003390 WO2004074639A1 (en) 1998-05-01 1999-04-27 Turbomachine guide bucket
US09/446,131 US6296442B1 (en) 1998-05-01 1999-04-27 Turbomachine stator vane set

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98201416A EP0953729B1 (en) 1998-05-01 1998-05-01 Guide vanes for a turbomachine

Publications (2)

Publication Number Publication Date
EP0953729A1 EP0953729A1 (en) 1999-11-03
EP0953729B1 true EP0953729B1 (en) 2003-06-25

Family

ID=8233667

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98201416A Expired - Lifetime EP0953729B1 (en) 1998-05-01 1998-05-01 Guide vanes for a turbomachine

Country Status (4)

Country Link
US (1) US6296442B1 (en)
EP (1) EP0953729B1 (en)
DE (1) DE69815815T2 (en)
WO (1) WO2004074639A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199544A1 (en) 2008-12-22 2010-06-23 Techspace Aero S.A. Assembly of guide vanes

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US7195453B2 (en) * 2004-08-30 2007-03-27 General Electric Company Compressor stator floating tip shroud and related method
ATE486195T1 (en) 2005-12-22 2010-11-15 Techspace Aero BLADE GUIDE RING OF A FLOW MACHINE, FLOW MACHINE WITH SUCH A GUIDE RING AND GUIDE VANE
FR2906296A1 (en) 2006-09-26 2008-03-28 Snecma Sa DEVICE FOR FASTENING A FIXED BLADE IN AN ANNULAR CASE FOR TURBOMACHINE, TURBOREACTOR INCORPORATING THE DEVICE AND METHOD FOR MOUNTING THE BLADE.
EP1936121B1 (en) * 2006-12-22 2012-05-02 Techspace Aero Angular setting of turbomachine stator vanes.
EP2075412B1 (en) * 2007-12-26 2012-02-29 Techspace Aero Device for attachment vanes by bolting to a shroud of a turbomachine stator stage and associated method for attachment by bolting
US8092165B2 (en) * 2008-01-21 2012-01-10 Pratt & Whitney Canada Corp. HP segment vanes
US8157507B1 (en) * 2010-01-19 2012-04-17 Florida Turbine Technologies, Inc. Damped stator assembly
US20130052004A1 (en) 2011-08-25 2013-02-28 Nicholas D. Stilin Structural composite fan exit guide vane for a turbomachine
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
EP2738356B1 (en) * 2012-11-29 2019-05-01 Safran Aero Boosters SA Vane of a turbomachine, vane assembly of a turbomachine, and corresponding assembly method
CN106050322A (en) * 2016-08-08 2016-10-26 中国船舶重工集团公司第七�三研究所 Tilting axis type variable-geometry power turbine guide vane
US10900364B2 (en) * 2017-07-12 2021-01-26 Raytheon Technologies Corporation Gas turbine engine stator vane support
US11286797B2 (en) 2018-06-06 2022-03-29 Raytheon Technologies Corporation Gas turbine engine stator vane base shape
CN109986489B (en) * 2019-03-12 2021-03-02 上海应达风机股份有限公司 Automatic fan impeller assembling equipment and fan impeller assembling process

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199544A1 (en) 2008-12-22 2010-06-23 Techspace Aero S.A. Assembly of guide vanes

Also Published As

Publication number Publication date
US6296442B1 (en) 2001-10-02
EP0953729A1 (en) 1999-11-03
DE69815815D1 (en) 2003-07-31
DE69815815T2 (en) 2004-05-13
WO2004074639A1 (en) 2004-09-02

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