EP1843008A1 - Stator vane with variable setting of a turbomachine - Google Patents
Stator vane with variable setting of a turbomachine Download PDFInfo
- Publication number
- EP1843008A1 EP1843008A1 EP07290419A EP07290419A EP1843008A1 EP 1843008 A1 EP1843008 A1 EP 1843008A1 EP 07290419 A EP07290419 A EP 07290419A EP 07290419 A EP07290419 A EP 07290419A EP 1843008 A1 EP1843008 A1 EP 1843008A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- zone
- pivot
- plate
- turbomachine
- 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.)
- Granted
Links
- 230000006837 decompression Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical group [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims 2
- 229910052697 platinum Inorganic materials 0.000 claims 1
- 230000006835 compression Effects 0.000 abstract description 2
- 238000007906 compression Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 9
- 210000003462 vein Anatomy 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Images
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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/304—Spool rotational speed
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
La présente invention se rapporte au domaine des turbomachines tel qu'un compresseur axial de moteur à turbine à gaz, et vise en particulier les aubes de stator à calage variable de la machine.The present invention relates to the field of turbomachines such as an axial compressor of gas turbine engine, and aims in particular stator vanes with variable pitch of the machine.
Un système articulé, comme les aubes de redresseur à calage variable d'un compresseur de moteur à turbine à gaz, comprend des pièces en mouvement relatif les unes par rapport aux autres. Sur les figures 1 et 2, on a représenté de façon schématique, une aube 1 de redresseur à calage variable montée dans le carter 3 de la machine. L'aube statorique comprend une pale 12, une platine ou plateforme 13 et une tige formant pivot 14 à une extrémité. Le pivot 14 est logé dans un alésage ou orifice radial ménagé dans la paroi du carter 3 par l'intermédiaire de différents paliers. L'aube n'est tenue que par cette extrémité. L'autre extrémité retient un élément annulaire flottant 16 dans lequel il est monté pivotant par un second pivot 17. L'anneau est pourvu de moyens d'étanchéité pour la partie du rotor 18 qui lui est adjacente. Le pivot 14 tourillonne dans l'alésage correspondant du carter par l'intermédiaire de paliers, par exemple un palier bas 4. La plateforme 13 est logée dans une cavité en forme de lamage usiné dans la paroi de ce carter. La paroi du carter est en contact radial avec la plateforme 13 soit directement soit par l'intermédiaire d'une douille ou rondelle. La partie haute du pivot 14 est retenue dans un palier haut 5. La face opposée de la plateforme 13 par rapport au palier 4 forme la base de la pale et est balayée par les gaz mis en mouvement par le compresseur. Cette face de la platine est conformée de manière à assurer la continuité de la veine formée par le carter. Un écrou maintient l'aube dans son logement et un levier actionné par des organes de commande appropriés, commande la rotation de l'aube autour de l'axe XX de la tige pour mettre celle-ci dans la position requise par rapport à la direction du flux gazeux. Les mouvements relatifs résultent du glissement des surfaces en contact entre elles.An articulated system, such as the variable pitch stator vanes of a gas turbine engine compressor, includes moving parts relative to one another. FIGS. 1 and 2 show diagrammatically a blade 1 of variable-pitch rectifier mounted in the
Dans le cas d'un compresseur axial de moteur à turbine à gaz ou bien d'un compresseur axial seul d'air ou autre gaz, tel que de haut fourneau ou gaz naturel, la pale 12 est soumise sur toute sa longueur aux efforts aérodynamiques et de pression engendrés par le flux gazeux. La composante de ces efforts orientée perpendiculairement à la corde dans le sens intrados vers extrados, en passant généralement par l'axe du pivot est la plus importante. On note cependant que dans les cas de braquages importants la composante peut s'écarter de cet axe. La pale est soumise aussi à des efforts axiaux de pression statique dirigés vers l'amont en raison de la différence de pression entre l'aval et l'amont. La force résultante est illustrée par la flèche F sur les figures. Il s'ensuit l'application d'un moment qui associé à la rotation de calage autour de l'axe XX sur une amplitude qui peut atteindre et dépasser 40 degrés, crée une zone de frottement intense. Ce frottement conduit accessoirement à une usure de la platine et/ou des douilles. Cette première zone 20 de frottement intense est localisée sur une partie de la surface de la platine. Elle est signalée par des croix sur la figure 2. Ainsi en fonctionnement normal de la machine, en raison de ces efforts de basculement appliqués sur la pale 12, la platine vient en appui par cette première zone 20 contre la surface du logement ménagé dans la paroi du carter, tandis que sur la partie diamétralement opposée par rapport au pivot, les efforts d'appui sont nuls ou très faibles.In the case of an axial compressor of gas turbine engine or of a single axial compressor of air or other gas, such as blast furnace or natural gas, the
Dans le domaine aéronautique toute surcharge pondérale est à éviter, et indépendamment de la suppression de toute surcharge, on cherche aussi à éliminer toute masse qui ne remplit aucune fonction qu'elle soit mécanique ou aérodynamique.In the aeronautical field any excess weight is to be avoided, and independently of the suppression of any overload, one also seeks to eliminate any mass which does not fulfill any function that it is mechanical or aerodynamic.
Le déposant a par ailleurs comme objectif permanent de trouver des solutions qui permettent d'alléger la machine sans nuire pour autant à ses performances et à sa fiabilité. Tout gain en masse améliore le rendement de la machine et permet de réduire les coûts d'exploitation.The applicant also has a permanent goal to find solutions that can lighten the machine without affecting its performance and reliability. Any gain in mass improves the efficiency of the machine and reduces operating costs.
Le déposant en poursuivant cet objectif est ainsi parvenu à la présente invention se rapportant à une aube de stator à calage variable.The applicant in pursuit of this object has thus come to the present invention relating to a variable-pitch stator blade.
Conformément à l'invention, l'aube de stator de turbomachine, à calage variable, comportant une pale, prolongée d'un côté par un pivot par lequel elle est montée rotative dans un alésage du carter de la turbomachine, et une platine, entre la pale et le pivot, perpendiculaire à la direction formée par la pale et le pivot , est caractérisée par le fait que la face de la platine opposée à la pale comprenant une première zone et une seconde zone, la première zone étant soumise à un frottement intense avec la paroi du carter en raison des effort transversaux appliqués sur la pale et la seconde zone étant soumise en fonctionnement normal à un frottement plus faible que la première zone, l'épaisseur de la platine sur la seconde zone est réduite par rapport à l'épaisseur de la platine sur la première zone.According to the invention, the turbomachine stator vane, variable pitch, comprising a blade, extended on one side by a pivot by which it is rotatably mounted in a bore of the casing of the turbomachine, and a plate, between the blade and the pivot, perpendicular to the direction formed by the blade and the pivot, is characterized in that the face of the plate opposite the blade comprises a first zone and a second zone, the first zone being subjected to friction with the wall of the casing due to the transverse forces applied to the blade and the second zone being subjected in normal operation to a lower friction than the first zone, the thickness of the plate on the second zone is reduced compared to the thickness of the plate on the first zone.
Les aubes à calage variable, notamment de compresseur axial, de l'art antérieur ont une platine d'épaisseur uniforme si on ne tient pas compte de la courbure et/ou non linéarité de la veine de gaz. Ainsi grâce à l'invention on permet de réduire la masse de cette partie de l'aube sans nuire à sa fonctionnalité, à savoir assurer la continuité de la veine et réduire les fuites le long du pivot.The blades with variable pitch, in particular axial compressor, of the prior art have a plate of uniform thickness if one does not take into account the curvature and / or nonlinearity of the gas stream. So thanks to the invention we can reduce the mass of this part of the blade without impairing its functionality, namely ensure continuity of the vein and reduce leakage along the pivot.
La seconde zone d'épaisseur plus faible s'étend pratiquement sur un arc de 60 à 120 degrés autour de l'axe du pivot.The second zone of lower thickness extends practically over an arc of 60 to 120 degrees around the axis of the pivot.
Pour un compresseur axial, la première zone est située côté extrados et la seconde zone s'étend du côté de l'intrados.For an axial compressor, the first zone is located on the extrados side and the second zone extends on the intrados side.
De préférence la seconde zone d'épaisseur réduite est délimitée par une bordure plus épaisse - notamment la face supérieure de cette bordure est dans le prolongement de la surface plane supérieure de la platine - que la première zone de façon à former une chambre de décompression entre la périphérie de la platine et le pivot ce qui permet d'améliorer l'étanchéité. En outre cette bordure permet de former un contact dans le cas où les efforts viendraient à s'inverser, notamment lorsqu'il se produit des phénomènes de pompage du compresseur. En outre cette disposition est appréciable au montage de la machine en empêchant les pièces de basculer exagérément.Preferably the second zone of reduced thickness is delimited by a thicker edge - in particular the upper face of this edge is in the extension of the upper plane surface of the plate - than the first zone so as to form a decompression chamber between the periphery of the plate and the pivot which improves the seal. In addition, this edge makes it possible to form a contact in the event that the forces become reversed, in particular when compressor pumping phenomena occur. In addition, this arrangement is appreciable when mounting the machine by preventing the parts from tilting too much.
Un moyen simple et économique de réaliser des aubes avec une seconde zone ainsi aménagée est d'usiner la platine. Selon l'outil choisi la cavité est à fond plat, incurvé ou encore de toute autre forme.A simple and economical way to make blades with a second zone thus fitted is to machine the plate. Depending on the chosen tool, the cavity is flat-bottomed, curved or any other shape.
D'autres caractéristiques et avantages ressortiront de la description qui suit d'un mode de réalisation non limitatif de l'invention en regard des dessins sur lesquels
- La figure 1 montre en coupe selon l'axe de la machine un exemple d'aube de stator à calage variable conventionnelle montée dans un carter de compresseur,
- La figure 2 montre la même aube vue de dessus,
- La figure 3 est une vue en perspective d'une partie d'aube présentant les caractéristiques de l'invention.
- FIG. 1 shows in section along the axis of the machine an example of a conventional variable-pitch stator vane mounted in a compressor housing,
- Figure 2 shows the same dawn seen from above,
- Figure 3 is a perspective view of a blade portion having the features of the invention.
En se reportant à la figure 3, on voit une aube de stator représentée seule, dans sa partie proche du pivot 14. La platine 13 est vue de dessus en perspective. Conformément à un mode réalisation de l'invention, on a usiné dans la face de la platine tournée vers le carter 3 une cavité 22A dans la seconde zone 22, qui n'est pas soumise aux efforts de compression résultant de l'application de la force F sur la pale 12. Cette cavité 22A a été ici usinée par des moyens connus en soi. Le fond de la cavité est plan, il pourrait être courbe si la tête d'usinage était en forme de boule. Des formes autres que celle représentée sont possibles. En outre, au lieu d'un usinage, la cavité peut provenir de fonderie, de forge ou de métallurgie des poudres. La cavité s'étend de préférence sur un arc, de cercle par exemple, de 60 à 120 degrés, correspondant avantageusement à l'arc sous-tendant la zone de frottement intense. Cette cavité a pour fonction de réduire la masse de l'aube mais pas de réduire ses caractéristiques mécaniques. L'épaisseur résultante de la platine est donc suffisante pour assurer la tenue mécanique de la platine. On observe qu'une bordure 23 a été conservée en périphérie de la platine. Cette bordure a une double fonction. La première est de former une chambre de décompression réduisant les fuites d'air entre la veine de la turbomachine et le pivot 14 à travers l'alésage du carter dans lequel est logé le pivot 14. La seconde fonction est de former une surface d'appui en cas d'inversion des efforts résultant d'une anomalie de fonctionnement de la turbomachine, telle que le pompage du compresseur ou encore pour simplifier les opérations de montage. La largeur de cette bordure peut ne pas être constante. Par exemple, elle pourrait être plus large dans une zone à renforcer. Avantageusement son plan supérieur est dans le plan de la platine face au carter.Referring to Figure 3, we see a stator blade shown alone, in its part near the
On a décrit une solution où la réduction d'épaisseur était réalisée sur la face supérieure de la platine. Cependant il entre également dans le cadre de l'invention de réaliser cette réduction d'épaisseur en formant une cavité dans la face de la platine située du côté de la veine de gaz ou en amincissant la platine par cette face.A solution has been described in which the thickness reduction is performed on the upper face of the plate. However, it is also within the scope of the invention to achieve this reduction in thickness by forming a cavity in the face of the plate located on the side of the gas stream or by slimming the plate by this face.
Claims (8)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0651243A FR2899637B1 (en) | 2006-04-06 | 2006-04-06 | STATOR VANE WITH VARIABLE SETTING OF TURBOMACHINE |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1843008A1 true EP1843008A1 (en) | 2007-10-10 |
EP1843008B1 EP1843008B1 (en) | 2009-06-17 |
Family
ID=37491722
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07290419A Active EP1843008B1 (en) | 2006-04-06 | 2007-04-05 | Stator vane with variable setting of a turbomachine |
Country Status (10)
Country | Link |
---|---|
US (1) | US7980815B2 (en) |
EP (1) | EP1843008B1 (en) |
JP (1) | JP5143465B2 (en) |
CN (1) | CN101054908B (en) |
AT (1) | ATE434116T1 (en) |
CA (1) | CA2583850C (en) |
DE (1) | DE602007001294D1 (en) |
ES (1) | ES2328530T3 (en) |
FR (1) | FR2899637B1 (en) |
RU (1) | RU2436967C2 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009004933A1 (en) * | 2009-01-16 | 2010-07-29 | Mtu Aero Engines Gmbh | Guide vane for a stator of a turbocompressor |
EP3388638A1 (en) * | 2017-04-11 | 2018-10-17 | United Technologies Corporation | Guide vane arrangement for gas turbine engine |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
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CA2823224C (en) | 2010-12-30 | 2016-11-22 | Rolls-Royce North American Technologies, Inc. | Variable vane for gas turbine engine |
US9062560B2 (en) | 2012-03-13 | 2015-06-23 | United Technologies Corporation | Gas turbine engine variable stator vane assembly |
US9334751B2 (en) * | 2012-04-03 | 2016-05-10 | United Technologies Corporation | Variable vane inner platform damping |
CN103397912B (en) * | 2013-08-19 | 2015-07-15 | 中国航空动力机械研究所 | Turbine engine rotor blade, turbine and turbine engine |
CN104153822B (en) * | 2014-07-22 | 2015-09-30 | 哈尔滨工程大学 | A kind ofly comprise the variable geometry turbine of end of blade with the variable stator vane angle of the little wing structure of groove-like |
US9784285B2 (en) | 2014-09-12 | 2017-10-10 | Honeywell International Inc. | Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith |
US9995166B2 (en) * | 2014-11-21 | 2018-06-12 | General Electric Company | Turbomachine including a vane and method of assembling such turbomachine |
CN104533544B (en) * | 2015-01-26 | 2016-01-06 | 成都成发科能动力工程有限公司 | For the stator blade controlling device of TRT |
DE102015110249A1 (en) * | 2015-06-25 | 2017-01-12 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a turbomachine with a housing device and a plurality of guide vanes |
DE102015110250A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a turbomachine with a housing device and a plurality of guide vanes |
EP3421754B1 (en) * | 2016-03-30 | 2021-12-01 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Variable geometry turbocharger |
US11572798B2 (en) * | 2020-11-27 | 2023-02-07 | Pratt & Whitney Canada Corp. | Variable guide vane for gas turbine engine |
CN113623021B (en) * | 2021-07-30 | 2023-01-17 | 中国航发沈阳发动机研究所 | Variable-geometry low-pressure turbine guide vane |
CN114321019A (en) * | 2021-12-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Adjustable stator structure of gas compressor |
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US2671634A (en) * | 1949-07-01 | 1954-03-09 | Rolls Royce | Adjustable stator blade and shroud ring arrangement for axial flow turbines and compressors |
US3542484A (en) * | 1968-08-19 | 1970-11-24 | Gen Motors Corp | Variable vanes |
EP0546935A1 (en) * | 1991-12-11 | 1993-06-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Stator guiding the inlet of air into a turbomachine and procedure for mounting a blade of this stator |
EP1528226A2 (en) * | 2003-10-29 | 2005-05-04 | United Technologies Corporation | Variable vane electro-graphitic thrust washer |
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CA2082709A1 (en) * | 1991-12-02 | 1993-06-03 | Srinivasan Venkatasubbu | Variable stator vane assembly for an axial flow compressor of a gas turbine engine |
FR2723614B1 (en) * | 1994-08-10 | 1996-09-13 | Snecma | DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES. |
US5593275A (en) * | 1995-08-01 | 1997-01-14 | General Electric Company | Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine |
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US6283705B1 (en) * | 1999-02-26 | 2001-09-04 | Allison Advanced Development Company | Variable vane with winglet |
US6682299B2 (en) * | 2001-11-15 | 2004-01-27 | General Electric Company | Variable stator vane support arrangement |
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-
2006
- 2006-04-06 FR FR0651243A patent/FR2899637B1/en not_active Expired - Fee Related
-
2007
- 2007-04-05 AT AT07290419T patent/ATE434116T1/en not_active IP Right Cessation
- 2007-04-05 CA CA2583850A patent/CA2583850C/en active Active
- 2007-04-05 DE DE602007001294T patent/DE602007001294D1/en active Active
- 2007-04-05 EP EP07290419A patent/EP1843008B1/en active Active
- 2007-04-05 ES ES07290419T patent/ES2328530T3/en active Active
- 2007-04-06 RU RU2007112880/06A patent/RU2436967C2/en active
- 2007-04-06 US US11/697,455 patent/US7980815B2/en active Active
- 2007-04-06 CN CN2007101016223A patent/CN101054908B/en active Active
- 2007-04-06 JP JP2007100147A patent/JP5143465B2/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2671634A (en) * | 1949-07-01 | 1954-03-09 | Rolls Royce | Adjustable stator blade and shroud ring arrangement for axial flow turbines and compressors |
US3542484A (en) * | 1968-08-19 | 1970-11-24 | Gen Motors Corp | Variable vanes |
EP0546935A1 (en) * | 1991-12-11 | 1993-06-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Stator guiding the inlet of air into a turbomachine and procedure for mounting a blade of this stator |
EP1528226A2 (en) * | 2003-10-29 | 2005-05-04 | United Technologies Corporation | Variable vane electro-graphitic thrust washer |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009004933A1 (en) * | 2009-01-16 | 2010-07-29 | Mtu Aero Engines Gmbh | Guide vane for a stator of a turbocompressor |
EP3388638A1 (en) * | 2017-04-11 | 2018-10-17 | United Technologies Corporation | Guide vane arrangement for gas turbine engine |
US10436050B2 (en) | 2017-04-11 | 2019-10-08 | United Technologies Corporation | Guide vane arrangement for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
RU2436967C2 (en) | 2011-12-20 |
JP5143465B2 (en) | 2013-02-13 |
US20100266389A1 (en) | 2010-10-21 |
CN101054908B (en) | 2010-09-08 |
RU2007112880A (en) | 2008-10-20 |
JP2007278291A (en) | 2007-10-25 |
US7980815B2 (en) | 2011-07-19 |
ATE434116T1 (en) | 2009-07-15 |
FR2899637A1 (en) | 2007-10-12 |
ES2328530T3 (en) | 2009-11-13 |
CN101054908A (en) | 2007-10-17 |
FR2899637B1 (en) | 2010-10-08 |
DE602007001294D1 (en) | 2009-07-30 |
CA2583850A1 (en) | 2007-10-06 |
EP1843008B1 (en) | 2009-06-17 |
CA2583850C (en) | 2014-02-18 |
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