EP1843008A1 - Stator vane with variable setting of a turbomachine - Google Patents

Stator vane with variable setting of a turbomachine Download PDF

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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
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EP
European Patent Office
Prior art keywords
blade
zone
pivot
plate
turbomachine
Prior art date
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Granted
Application number
EP07290419A
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German (de)
French (fr)
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EP1843008B1 (en
Inventor
Yvon Cloarec
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

The vane has a plate (13) perpendicular to direction formed by a blade (12) and a pivot (14). A surface of the plate opposed to the blade includes two zones (20, 22), where one zone (20) is subjected to high friction with a wall of a bore housing due to the stress transversely applied on the blade. A cavity (22A) in the zone (22) is fabricated in the surface turned towards the housing, where the cavity is not subjected to compression stress resulting from application of force on the blade. The cavity extends on an arc i.e. circle, from sixty to one hundred and twenty degrees around the pivot.

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 casing 3 of the machine. The stator blade comprises a blade 12, a plate or platform 13 and a pivot rod 14 at one end. The pivot 14 is housed in a bore or radial orifice formed in the wall of the casing 3 by means of different bearings. Dawn is held only by this extremity. The other end retains a floating annular element 16 in which it is pivotally mounted by a second pivot 17. The ring is provided with sealing means for the portion of the rotor 18 which is adjacent thereto. The pivot 14 is journalled in the corresponding bore of the casing via bearings, for example a low bearing 4. The platform 13 is housed in a recess shaped machined in the wall of this housing. The housing wall is in radial contact with the platform 13 either directly or via a bushing or washer. The upper part of the pivot 14 is retained in a high bearing 5. The opposite face of the platform 13 with respect to the bearing 4 forms the base of the blade and is swept by the gases set in motion by the compressor. This face of the plate is shaped to ensure the continuity of the vein formed by the housing. A nut keeps the blade in its housing and a lever actuated by appropriate control members, controls the rotation of the blade around the axis XX of the rod to put it in the required position relative to the direction gas flow. The relative movements result from the sliding of the surfaces in contact with each other.

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 blade 12 is subjected over its entire length to the aerodynamic forces and pressure generated by the gas flow. The component of these forces oriented perpendicular to the chord in the direction intrados towards extrados, passing generally by the axis of the pivot is the most important. Note, however, that in cases of major robberies the component may deviate from this axis. The blade is also subjected to axial forces of static pressure directed upstream due to the pressure difference between the downstream and the upstream. The resulting force is illustrated by the arrow F in the figures. It follows the application of a moment that associated with the pitch rotation about the axis XX on an amplitude that can reach and exceed 40 degrees, creates a zone of intense friction. This friction leads incidentally to a wear of the plate and / or sockets. This first zone 20 of intense friction is located on a part of the surface of the plate. It is indicated by crosses in FIG. 2. Thus, during normal operation of the machine, because of these tilting forces applied to the blade 12, the plate comes to bear by this first zone 20 against the surface of the housing formed in the crankcase wall, while on the diametrically opposite portion relative to the pivot, the support forces are zero or very low.

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.
Other features and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the drawings in which
  • 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 pivot 14. The plate 13 is viewed from above in perspective. According to one embodiment of the invention, a cavity 22A has been machined in the face of the plate facing towards the casing 3 in the second zone 22, which is not subjected to compression forces resulting from the application of the force F on the blade 12. This cavity 22A has been machined here by means known per se. The bottom of the cavity is flat, it could be curved if the machining head was ball-shaped. Shapes other than the one shown are possible. In addition, instead of machining, the cavity can come from foundry, forging or metallurgy powders. The cavity preferably extends over an arc, of a circle for example, of 60 to 120 degrees, advantageously corresponding to the arc underlying the zone of intense friction. This cavity has the function of reducing the mass of the blade but not reducing its mechanical characteristics. The resulting thickness of the plate is therefore sufficient to ensure the mechanical strength of the plate. It is observed that a border 23 has been preserved on the periphery of the plate. This border has a dual function. The first is to form a decompression chamber reducing air leakage between the vein of the turbomachine and the pivot 14 through the bore of the housing in which is housed the pivot 14. The second function is to form a surface of support in the event of inversion of the forces resulting from a malfunction of the turbomachine, such as the pumping of the compressor or to simplify assembly operations. The width of this border may not be constant. For example, it could be wider in an area to be strengthened. Advantageously, its upper plane is in the plane of the plate facing the housing.

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)

Aube de stator de turbomachine, à calage variable, comportant une pale (12), prolongée d'un côté par un pivot (14) par lequel elle est montée rotative dans un alésage du carter (3) de la turbomachine, et une platine (13), entre la pale et le pivot, perpendiculaire à la direction formée par la pale et le pivot, caractérisée par le fait que la face de la platine opposée à la pale comprenant une première zone (20) et une seconde zone (22), la première zone (20) étant soumise à un frottement intense avec la paroi du carter (3) en raison des efforts transversaux appliqués sur la pale (12), l'épaisseur de la platine sur la seconde zone (22) est réduite par rapport à l'épaisseur de platine de la première zone (20).Turbomachine stator blade, variable pitch, comprising a blade (12), extended on one side by a pivot (14) by which it is rotatably mounted in a bore of the casing (3) of the turbomachine, and a plate ( 13), between the blade and the pivot, perpendicular to the direction formed by the blade and the pivot, characterized in that the face of the plate opposite the blade comprising a first zone (20) and a second zone (22). the first zone (20) being subjected to intense friction with the wall of the housing (3) due to the transverse forces applied to the blade (12), the thickness of the plate on the second zone (22) is reduced by relative to the platinum thickness of the first zone (20). Aube selon la revendication 1 dont la partie d'épaisseur plus faible de la seconde zone (22) s'étend sur un arc de 60 à 120 degrés autour du pivot (14).A blade according to claim 1, wherein the lower thickness portion of the second zone (22) extends over a 60 to 120 degree arc around the pivot (14). Aube selon la revendication 1 dont la première zone est située du côté extrados et la seconde zone s'étend du côté de l'intrados de la pale.A blade according to claim 1, the first zone of which is located on the extrados side and the second zone extending on the underside side of the blade. Aube selon la revendication 1, 2 ou 3 dont la seconde zone d'épaisseur plus faible est délimitée par une bordure (23) de façon à former une chambre de décompression entre la périphérie de la platine (13) et le pivot (14).Blade according to claim 1, 2 or 3, the second zone of smaller thickness is delimited by a border (23) so as to form a decompression chamber between the periphery of the plate (13) and the pivot (14). Aube selon l'une des revendications précédentes dont la seconde zone (22) d'épaisseur plus faible forme une cavité obtenue par usinage de la platine (13).Blade according to one of the preceding claims, the second zone (22) of smaller thickness forms a cavity obtained by machining the plate (13). Aube selon la revendication précédente dont la cavité est à fond plat ou fond incurvé.Dawn according to the preceding claim whose cavity is flat bottom or curved bottom. Aube selon l'une des revendications 5 ou 6 dont la cavité est allongée en arc de cercle.Dawn according to one of claims 5 or 6, the recess is elongated in an arc. Turbomachine comprenant au moins une aube de stator selon l'une des revendications 1 à 7.Turbomachine comprising at least one stator blade according to one of Claims 1 to 7.
EP07290419A 2006-04-06 2007-04-05 Stator vane with variable setting of a turbomachine Active EP1843008B1 (en)

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

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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)

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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

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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
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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
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
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
EP3954882B1 (en) * 2016-03-30 2023-05-03 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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CA2583850A1 (en) 2007-10-06
FR2899637A1 (en) 2007-10-12
CN101054908A (en) 2007-10-17
DE602007001294D1 (en) 2009-07-30
US7980815B2 (en) 2011-07-19
JP5143465B2 (en) 2013-02-13
FR2899637B1 (en) 2010-10-08
ATE434116T1 (en) 2009-07-15
EP1843008B1 (en) 2009-06-17
RU2436967C2 (en) 2011-12-20
JP2007278291A (en) 2007-10-25
CN101054908B (en) 2010-09-08
US20100266389A1 (en) 2010-10-21
ES2328530T3 (en) 2009-11-13
CA2583850C (en) 2014-02-18
RU2007112880A (en) 2008-10-20

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