WO2009086959A1 - Leitschaufel für eine variable turbinengeometrie - Google Patents
Leitschaufel für eine variable turbinengeometrie Download PDFInfo
- Publication number
- WO2009086959A1 WO2009086959A1 PCT/EP2008/064594 EP2008064594W WO2009086959A1 WO 2009086959 A1 WO2009086959 A1 WO 2009086959A1 EP 2008064594 W EP2008064594 W EP 2008064594W WO 2009086959 A1 WO2009086959 A1 WO 2009086959A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- sections
- guide vane
- section
- curvature
- region
- Prior art date
Links
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
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
Definitions
- the invention relates to a guide vane for a variable turbine geometry of a turbocharger.
- a turbocharger generally consists of an exhaust gas turbine in the exhaust stream, which is connected via a shaft with a compressor in An ⁇ aug Th.
- the turbine is set in rotation by the exhaust gas flow of the engine and thus drives the compressor.
- the pressure in the intake tract of the engine is increased via the compressor, so that a larger amount of air enters the cylinder during the intake stroke than in a naturally aspirated engine. In this way, more oxygen is available for burning a correspondingly larger amount of fuel.
- bypass or wastegate the hot exhaust gas is partly passed by the turbine and thus the performance of the turbine is reduced.
- the turbine is designed so large that it works well well below the rated operating point of the engine.
- turbochargers are known from the prior art, which are provided with a variable turbine geometry VTG, in order to better adapt the power output and the response to different operating conditions, such as load changes.
- VTG variable turbine geometry
- high peripheral components of the flow velocity and a high enthalpy gradient lead to a high turbine output and thus to a high boost pressure.
- full open position of the vanes in turn, the maximum throughput of the turbine opens up high centripetal fraction of the velocity vector of the flow.
- the advantage of this power control over a bypass control is that always the full exhaust gas mass flow is routed through the turbine and used for power conversion.
- the shape of the blade profile is the main influencing factor for the thermodynamic efficiency, the control characteristics and the required radial space.
- the profile of the adjusting blade there are a variety of shapes for the profile of the adjusting blade. In general, it is important to combine the optimum of efficiency, control characteristics and the smallest possible pitch circle (installation space).
- the shape is described by the line of curvature that extends between the center of the head radius and the center of the end radius of the pitch blade. This curvature line is created by assuming tangential circles within the profile to the top and bottom. The connecting line of the circle centers here describes the curvature line.
- curvature lines have a continuous course, i.
- the individual curve pieces merge tangentially.
- the curvature line has no kink.
- a guide vane is provided, in particular for a turbocharger, wherein the manifold ment line of the guide vane has at least one or more areas with a discontinuous course.
- the guide vane is particularly advantageous in the design of a flow profile.
- the efficiency can be improved with unchanged control behavior and space requirements.
- the line of curvature has at least one region with two sections which are connected to one another, the two sections discontinuously or not tangentially merging at their connection point.
- the sections form a kink at their junction.
- the line of curvature of the guide vane has, in addition to at least one region with a bend or with a non-tangential transition between two sections, at least one region whose two sections merge continuously or tangentially into one another at their junction.
- the line of curvature of a guide vane can be varied as desired with continuously and discontinuously extending regions, depending on which flow profile is to be achieved.
- At least one, several or all portions of the line of curvature are identical or different, for example with respect to their shape, position and / or dimension.
- the guide vane for example consists of four sections, wherein the first and second section form a first region, with a continuous course.
- a second region is formed by the second portion and a third portion, wherein the second and third portions at their junction discontinuously into each other or form a kink.
- Such a vane is an example in which the curvature line has a kink.
- the sections of the first or third area may in this case be curved, for example, both or at least one of them upwards or downwards.
- the portions of which the curvature line is composed for example, arcuate or straight.
- the sections can be curved upwards or downwards or, if the sections are straight, for example horizontally, vertically, or obliquely upwards or obliquely downwards.
- the sections can be combined as desired with each other, wherein at least one area which is formed by the sections has a discontinuous course. In this way, a variety of flow profiles, depending on the desired function or desired application can be realized.
- FIG. 2 shows a second embodiment of a guide vane according to the prior art
- FIG. 3 shows a third embodiment of a guide vane according to the prior art
- Fig. 5 shows a second embodiment of a vane according to the invention.
- FIG. 1 a first embodiment of a guide vane 10 according to the prior art is shown.
- the vane 10 is shown in a diagram, wherein the diagram has an X-axis and a Y-axis. This illustration applies to all guide vanes 10 as shown in FIGS. 1 to 5.
- the shape of a vane 10 is normally described by the line of curvature 12 that extends between the midpoint 14 of the head radius and the midpoint 16 of the end radius of the vane 10.
- This curvature line 12 is formed by 20 tangential circles are assumed within the profile of the guide vane 10 to the top and bottom 18 ,.
- the connecting line of the circular center points describes the curvature line 12.
- the curvature line 12 is wavy.
- the curvature line 12 consists of four sections al to a4 together.
- the first and second sections a1, a2, which form a first area b1 are in each case arched upwards in a curved shape, wherein the two sections a1, a2 of the curve 12 merge tangentially into one another at their connection point 22.
- the area bl forms a continuous course without a kink.
- the third portion a3 is also arcuate, being curved downward, in contrast to the first and second portions al, a2.
- the second and third sections a2, a3 also merge tangentially into one another at their connection point 22, so that the second region b2, which is formed from the second and third sections a2, a3, has a continuous profile.
- the two sections a3, a4 of the curvature line 12 merge tangentially into one another, ie the region b3 has a continuous course, without a kink being formed at the transition 22 between the two sections a3, a4.
- All three areas bl to b3 extend above the X axis in the diagram in FIG. 1, furthermore, the first area bl is significantly longer and more curved than the third area b3.
- the line of curvature 12 is also composed of four sections al to a4.
- the curvature line 12 in this case runs above the X axis and in this case initially rises in an arc upwards, before it slowly drops towards the other end.
- the first section al of the line of curvature 12 is arched downward in a downward arc and the adjoining section a2 is curved upward.
- the two sections al and a2 tangentially merge into each other, so that the first area bl, by the first and second portion al, a2 has a continuous course.
- the third section a3 is also curved arcuately upwards, wherein he and the second section a2 at their junction 22 tangentially merge into each other, without causing a kink arises.
- the third region b3 of the curvature line 12 is formed from the third section a3 and a fourth section a4.
- the fourth section a4 is arched downward in an arc shape, with the third and fourth sections a3, a4 merging tangentially into one another at their connection point 22.
- Fig. 3 Further shown in Fig. 3 is a third embodiment of a prior art vane form.
- the guide vane 10 consists, as in the first and second embodiment of four sections al to a4.
- the curvature line 12 runs in a waveform initially in an arc above the X axis and then in an arc below the X axis.
- the first and second sections al, a2 of the curvature line 12 is arcuate and extends upwardly curved. At their connection point 22, the two first and second sections al, a2 merge tangentially into one another.
- the second region b2 of the curvature line 12 is formed by the second section a2 and a third section a3.
- the third section a3 is also arcuate and curved downwards.
- the two sections a2 and a3 pass tangentially into one another at their connection point 22, so that no sharp kink occurs in this area.
- the fourth region b4 is formed by the third section a3 and a fourth section a4.
- the fourth section a4 is likewise arched in an arcuate manner.
- the guide vane 10 here consists for example of four sections al to a4.
- a first region, consisting of the first and second sections al, a2, has a continuous course.
- the first and second sections al, a2 is here arc-shaped and curved upwards.
- the first section al passes tangentially into the second section a2, so that a continuous course is created without a kink.
- a second region b2 is formed by the second portion a2 and a third portion a3, wherein the second and third portions a2, a3 are each arcuate and are curved upward.
- the sections a2 and a3 do not tangentially merge into one another at their connection point 22 but form a kink 24.
- the second area b2 does not form a continuous course as in the prior art but has a discontinuous course or has a sharp kink 24 at the Junction 22 of the two sections a2, a3.
- the third area b3 consists of the third section a3 and a fourth section a4 and forms a continuous course.
- the fourth section a4 is arc-shaped and arched upwards. At their connection point 22, the third and fourth sections a3, a4 merge tangentially into one another.
- the guide vane 10 has a region b2 with a discontinuous course of the curvature line 12, in which the second and third sections a2, a3 at their junction 22 form a kind of kink 24 or not tangentially into each other.
- the other areas b1 and b3 have a continuous course of the curvature line 12, without one of the areas forming a bend.
- the curvature line 12 in the present case forms two arcs, once an upwardly arched arc of the sections al and a2 and another compared to a very much shallow arched arc consisting of the sections a3 and a4. Both bends form at their junction 22 the kink 24th
- FIG. 5 a second embodiment of a guide blade 10 according to the invention is shown in FIG. 5.
- the curvature line 12 of the guide vane 10 consists of four sections al to a4.
- the first and second sections al, a2 is arc-shaped and arched upwards.
- the first and second sections al, a2 merge tangentially into one another, so that the area b1, which is formed from the two sections al, a2, has a continuous course.
- the second region b2 is formed from the second portion a2 and a third portion a3, wherein the third portion a3 is also curved upwards.
- the two sections a2, a3 do not merge tangentially into one another at their connection point 22, but form a kind of kink 24, as shown in FIG.
- the second area b2 has a discontinuous course.
- the two third and fourth sections a3, a4 are here arc-shaped and curved upwards. At their junction 22 they go tangentially into each other.
- the curvature line 12 of the guide vane 10 according to the invention has a discontinuous course at least in the region b2, while the two other regions b1 and b3 have a continuous course without buckling.
- the first area bl is formed longer, or the stretched from the sections al and a2 arch.
- the third area b3, or the arc stretched from the sections a3 and a4 is shorter in the second embodiment than in the first embodiment.
- a guide vane may comprise at least one region consisting of two sections or a plurality of sections, for example two, three, four, five, six and more sections.
- sections having an arbitrary shape, arrangement and / or dimensioning can be combined with one another.
- the areas that are formed from the sections are formed from the sections.
- the areas b 1 to b 3 are each arranged substantially above the x-axis in the diagrams.
- the regions or sections of the curvature line 12 can run as desired, for example at least partially below the X axis, as is illustrated, for example, in FIG. 3 with reference to the prior art.
- the portions of the line of curvature 12 may also extend entirely below or partially along the X-axis.
- straight and arcuate portions at the curve line 12 of a vane 10 can be varied as desired.
- the guide blade 10 can have at least one kink 24 or a plurality of kinks 24 or points at which the individual curve pieces of the curve line 12 do not merge tangentially into one another.
- the curvature line 12 can have one, two, three, four or more of these so-called kinks 24 or non-tangential transitions, wherein the kinks 24 can be provided at arbitrary positions of the curvature line 12, depending on the function or intended use.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/812,499 US20100296924A1 (en) | 2008-01-11 | 2008-10-28 | Guide Vane for a Variable Turbine Geometry |
EP08869779.2A EP2245275B1 (de) | 2008-01-11 | 2008-10-28 | Leitschaufel einer variablen turbinengeometrie eines turboladers |
CN200880124892.9A CN101910565B (zh) | 2008-01-11 | 2008-10-28 | 用于可变涡轮几何形状的导向叶片 |
JP2010541722A JP2011509371A (ja) | 2008-01-11 | 2008-10-28 | 可変のタービンジオメトリのためのガイドベーン |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008004014A DE102008004014A1 (de) | 2008-01-11 | 2008-01-11 | Leitschaufel für eine variable Turbinengeometrie |
DE102008004014.2 | 2008-01-11 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009086959A1 true WO2009086959A1 (de) | 2009-07-16 |
Family
ID=40193669
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2008/064594 WO2009086959A1 (de) | 2008-01-11 | 2008-10-28 | Leitschaufel für eine variable turbinengeometrie |
Country Status (7)
Country | Link |
---|---|
US (1) | US20100296924A1 (de) |
EP (1) | EP2245275B1 (de) |
JP (2) | JP2011509371A (de) |
KR (1) | KR20100110867A (de) |
CN (1) | CN101910565B (de) |
DE (1) | DE102008004014A1 (de) |
WO (1) | WO2009086959A1 (de) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009057987A1 (de) * | 2009-12-11 | 2011-06-16 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Ladeeinrichtung |
CN102296995A (zh) * | 2010-06-25 | 2011-12-28 | 霍尼韦尔国际公司 | 用于向涡轮引导废气的叶片 |
WO2016062531A1 (de) * | 2014-10-21 | 2016-04-28 | Siemens Aktiengesellschaft | Profilierung von leitschaufeln von leitapparaten bei turbomaschinen, insbesondere verdichtern |
EP3412892A4 (de) * | 2016-03-31 | 2019-01-23 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotierende maschinenschaufel, superlader und verfahren zur bildung eines strömungsfeldes davon |
EP3470627A1 (de) * | 2017-10-12 | 2019-04-17 | United Technologies Corporation | Gasturbinenmotorschaufel |
EP3073063B1 (de) * | 2015-03-23 | 2020-12-09 | BMTS Technology GmbH & Co. KG | Ladeeinrichtung und zugehörige leitschaufel |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2787181B1 (de) | 2011-11-30 | 2019-01-09 | Mitsubishi Heavy Industries, Ltd. | Radialturbine |
JP5964081B2 (ja) * | 2012-02-29 | 2016-08-03 | 三菱重工業株式会社 | 可変容量ターボチャージャ |
FR2991373B1 (fr) * | 2012-05-31 | 2014-06-20 | Snecma | Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied |
US9790796B2 (en) * | 2013-09-19 | 2017-10-17 | General Electric Company | Systems and methods for modifying a pressure side on an airfoil about a trailing edge |
DE102013224572A1 (de) * | 2013-11-29 | 2015-06-03 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Abgasturbolader, insbesondere für ein Kraftfahrzeug |
DE102013225642B4 (de) * | 2013-12-11 | 2020-09-17 | Vitesco Technologies GmbH | Abgasturbolader mit einem verstellbaren Leitgitter |
WO2015134351A1 (en) * | 2014-03-04 | 2015-09-11 | Borgwarner Inc. | A cast turbocharger turbine housing having guide vanes |
US10935041B2 (en) | 2016-06-29 | 2021-03-02 | Rolls-Royce Corporation | Pressure recovery axial-compressor blading |
CN112154260B (zh) * | 2018-12-19 | 2022-10-14 | 三菱重工发动机和增压器株式会社 | 喷嘴叶片 |
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DE522531C (de) * | 1929-01-12 | 1931-04-10 | Bbc Brown Boveri & Cie | Verfahren zur Anpassung des freien Durchgangsquerschnittes verstellbar eingesetzter Leitschaufeln von Turbinen, insbesondere Abgasturbinen |
CH351065A (de) * | 1957-02-21 | 1960-12-31 | Ingenieurbureau W Hausammann & | Laufrad für Turbomaschinen, speziell Axialkompressoren |
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EP1731716A2 (de) * | 2005-06-06 | 2006-12-13 | The General Electric Company | Forwärts geneigte Statorschaufel |
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EP3150805B1 (de) * | 2005-11-25 | 2020-09-23 | BorgWarner, Inc. | Schaufel eines turboladers mit verstellbarer turbinengeometrie sowie turbolader |
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2008
- 2008-01-11 DE DE102008004014A patent/DE102008004014A1/de not_active Withdrawn
- 2008-10-28 JP JP2010541722A patent/JP2011509371A/ja active Pending
- 2008-10-28 WO PCT/EP2008/064594 patent/WO2009086959A1/de active Application Filing
- 2008-10-28 EP EP08869779.2A patent/EP2245275B1/de active Active
- 2008-10-28 US US12/812,499 patent/US20100296924A1/en not_active Abandoned
- 2008-10-28 CN CN200880124892.9A patent/CN101910565B/zh active Active
- 2008-10-28 KR KR1020107017638A patent/KR20100110867A/ko not_active Application Discontinuation
-
2013
- 2013-09-05 JP JP2013184103A patent/JP5701352B2/ja not_active Expired - Fee Related
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Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8662836B2 (en) | 2009-12-11 | 2014-03-04 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device |
DE102009057987B4 (de) * | 2009-12-11 | 2020-08-20 | BMTS Technology GmbH & Co. KG | Ladeeinrichtung und Leitschaufel für eine derartige Ladeeinrichtung |
DE102009057987A1 (de) * | 2009-12-11 | 2011-06-16 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Ladeeinrichtung |
US8834104B2 (en) | 2010-06-25 | 2014-09-16 | Honeywell International Inc. | Vanes for directing exhaust to a turbine wheel |
EP2402558A1 (de) * | 2010-06-25 | 2012-01-04 | Honeywell International, Inc. | Schaufeln zum Leiten von Abgas zu einem Turbinenrad |
CN102296995B (zh) * | 2010-06-25 | 2016-04-13 | 霍尼韦尔国际公司 | 用于向涡轮引导废气的叶片 |
EP3048253A1 (de) * | 2010-06-25 | 2016-07-27 | Honeywell International Inc. | Schaufeln zum leiten von abgas zu einem turbinenrad |
CN102296995A (zh) * | 2010-06-25 | 2011-12-28 | 霍尼韦尔国际公司 | 用于向涡轮引导废气的叶片 |
WO2016062531A1 (de) * | 2014-10-21 | 2016-04-28 | Siemens Aktiengesellschaft | Profilierung von leitschaufeln von leitapparaten bei turbomaschinen, insbesondere verdichtern |
CN107109960A (zh) * | 2014-10-21 | 2017-08-29 | 西门子公司 | 在涡轮机械中、尤其压缩机中的导向器的导向叶片的轮廓部 |
US10634156B2 (en) | 2014-10-21 | 2020-04-28 | Siemens Aktiengesellschaft | Centrifugal compressor |
EP3073063B1 (de) * | 2015-03-23 | 2020-12-09 | BMTS Technology GmbH & Co. KG | Ladeeinrichtung und zugehörige leitschaufel |
EP3412892A4 (de) * | 2016-03-31 | 2019-01-23 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotierende maschinenschaufel, superlader und verfahren zur bildung eines strömungsfeldes davon |
US11041505B2 (en) | 2016-03-31 | 2021-06-22 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotary machine blade, supercharger, and method for forming flow field of same |
EP3470627A1 (de) * | 2017-10-12 | 2019-04-17 | United Technologies Corporation | Gasturbinenmotorschaufel |
US10774650B2 (en) | 2017-10-12 | 2020-09-15 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
Also Published As
Publication number | Publication date |
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US20100296924A1 (en) | 2010-11-25 |
CN101910565B (zh) | 2014-06-11 |
JP2013238249A (ja) | 2013-11-28 |
KR20100110867A (ko) | 2010-10-13 |
EP2245275A1 (de) | 2010-11-03 |
JP2011509371A (ja) | 2011-03-24 |
DE102008004014A1 (de) | 2009-07-23 |
JP5701352B2 (ja) | 2015-04-15 |
CN101910565A (zh) | 2010-12-08 |
EP2245275B1 (de) | 2015-04-08 |
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