EP2147216B1 - Exhaust gas turbocharger - Google Patents
Exhaust gas turbocharger Download PDFInfo
- Publication number
- EP2147216B1 EP2147216B1 EP08717167.4A EP08717167A EP2147216B1 EP 2147216 B1 EP2147216 B1 EP 2147216B1 EP 08717167 A EP08717167 A EP 08717167A EP 2147216 B1 EP2147216 B1 EP 2147216B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- intermediate blade
- main
- turbocharger
- blades
- 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.)
- Not-in-force
Links
Images
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
Definitions
- An exhaust gas turbocharger or turbocharger for short is a charging system for an internal combustion engine, by means of which the cylinders of the internal combustion engine are subjected to an increased charge pressure.
- a turbocharger consists of an exhaust gas turbine in the exhaust stream (outflow path), which is connected via a common shaft with a compressor in the intake (Anströmpfad).
- the turbine is set in rotation by the exhaust gas flow of the engine and thus drives the compressor.
- the compressor increases the pressure in the intake tract of the engine, so that through this compression during the intake stroke, a larger amount of air in the cylinders of the internal combustion engine succeeded than in a conventional naturally aspirated engine. This provides more oxygen for combustion.
- a disadvantage of the previous embodiments of the intermediate blades is that it comes in the blade channel to the leading main blade compared to the blade channel to trailing main blade at different speed profiles. This increases the efficiency losses within the turbine. It is the object of the present invention to reduce the aforementioned disadvantages.
- the idea on which the present invention is based is to provide a device in the inflow path or outflow path of an internal combustion engine with which an incoming gas stream is conducted as uniformly as possible through a compressor or turbine-side impeller.
- An advantage of the device according to the invention is that, by means of an angular position of the intermediate blade deviating from the main blade, the flow channels on the front side or on the rear side of the intermediate blade can be designed such that the loss of efficiency is reduced. Furthermore, the noise of the turbocharger is reduced and he increased the range of application of the turbocharger.
- the lengths of the circular arc sections from the front side and the rear side of the intermediate vane to the trailing and leading main vane are substantially the same at the rotational axis-side end of the intermediate vane.
- the impeller of the exhaust gas turbocharger is formed as a turbine wheel (108) or compressor wheel (104).
- Fig.1 shows an elevation of a turbocharger 102 with a turbine 118 and a compressor 116.
- a turbine wheel 108 according to the invention is rotatably mounted and connected to one end of a shaft 110.
- a compressor wheel 104 according to the invention is also rotatably mounted and connected to the other end of the shaft 110.
- the compressor wheel 104 has a main vane 203 and an intermediate vane 204, the vane surface of which is set back from the main vane.
- hot exhaust gas is introduced into the turbine 118 by an internal combustion engine, not shown here, whereby the turbine wheel 118 is rotated.
- the turbine wheel 108 has main blades 120 and intermediate blades 102.
- the outlet side blade edges of the intermediate blades 102 are recessed from the outlet side edge of the main blades.
- the exhaust flow leaves the turbine 118 through a turbine outlet 114.
- the turbine 118 drives the compressor 116 via the shaft 110, which couples the turbine wheel 108 to the compressor wheel 104.
- the compressor wheel 104 By means of the compressor wheel 104, the sucked air is compressed in Anströmpfad.
- Fig. 2 , 10 shows a schematic plan view of a blade arrangement according to the invention, for example a compressor wheel with a clockwise rotation, comprising a trailing main blade 202, an intermediate blade 204 and a leading main blade 203.
- the blades are arranged on a section of an axis of rotation at an angle ⁇ , the counting direction of the angle ⁇ is opposite to the direction of rotation.
- the length of the circular arc portion 206 from the intermediate blade 204 to the trailing main blade 202 is smaller than the length of the circular arc portion 207 between the intermediate blade 204 to the leading main blade 203.
- An advantage of the arrangement according to the invention is that the differences in the lengths of the circular arc sections the surfaces are reduced perpendicular to the flow guide between the leading and trailing main blade. Furthermore, the differences in the velocity profiles in the blade channel at the front and rear of the intermediate blade are reduced and the efficiency is increased.
- Fig. 3 schematically shows the difference in the course of the meridian coordinate m of the intermediate blade 204 and the main blade 202nd
- the curvature of the main blade 202 in the axial direction is different at a given center distance, and preferably greater than the curvature of the intermediate blade 204.
- Fig. 4 shows a schematic plot of the axial angle ⁇ as a function of the normal to the rotational axis distance r meridian coordinate m '.
- the position of an intermediate blade according to the prior art is represented by the dashed line 210.
- An intermediate blade with a changed angle is shown by the solid line. This makes it possible to set the ratio of the flow cross sections between the preceding and following main blade.
- An advantage of the device according to the invention is that due to the special design i. the different angular arrangement of the intermediate blades in both the axial and in the radial direction relative to the main blade, the cross-sections of the flow channels along the front and back of the intermediate blades reliably align. In addition to increasing the efficiency and the smoothness of the turbocharger is improved.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Description
Bei herkömmlichen, nicht aufgeladenen Brennkraftmaschinen wird beim Ansaugen von Luft ein Unterdruck im Ansaugtrakt erzeugt, der mit wachsender Drehzahl des Motors ansteigt und die theoretisch erreichbare Leistung des Motors begrenzt. Eine Möglichkeit, dem entgegenzuwirken und damit eine Leistungssteigerung zu erzielen, ist die Verwendung eines Abgasturboladers (ATL). Ein Abgasturbolader oder kurz Turbolader ist ein Aufladesystem für eine Brennkraftmaschine, mittels dem die Zylinder der Brennkraftmaschine mit einem erhöhten Ladedruck beaufschlagt werden.In conventional, non-supercharged internal combustion engines, a negative pressure in the intake tract is generated during intake of air, which increases with increasing speed of the engine and limits the theoretically achievable performance of the engine. One way to counteract this and thus achieve an increase in performance is the use of an exhaust gas turbocharger (ATL). An exhaust gas turbocharger or turbocharger for short is a charging system for an internal combustion engine, by means of which the cylinders of the internal combustion engine are subjected to an increased charge pressure.
Der detaillierte Aufbau und die Funktionsweise ist allgemein bekannt und beispielsweise beschrieben in der Druckschrift: "
An die Abgasturbolader werden hohe Anforderungen gestellt. Dies sind vor allem die hohen Abgastemperaturen von bis über 1000°C und den je nach Drehzahlbereich völlig unterschiedlichen Gasmengen und die dadurch bedingten hohen maximalen Drehzahlen bis zu 300.000 Umdrehungen je Minute. Um den Einsatzbereich des Turboladers und das Ansprechverhalten zu verbessern werden zwischen den Hauptschaufeln eines Verdichters sogenannte Zwischenschaufeln (Splitter Blades) angeordnet. Diese weisen einen mit den Hauptschaufeln identischen Winkelverlauf auf, sind aber gegenüber diesen zurückgesetzt, d.h. die Größe der Fläche der Zwischenschaufel ist gegenüber der Größe der Fläche der Hauptschaufel verringert. Durch den Einsatz von Zwischenschaufeln lässt sich die Stromführung in den Schaufelkanälen insbesondere bei kleinen Durchmessern verbessern und der Druckgradient von Schaufelrücken zur Schaufelvorderseite verringern. Eine beispielhafte Ausführungsform eines Laufrades mit Zwischenschaufeln findet sich auf
Weitere Ausführungen von so oder ähnlich gestalteten Schaufelrädern mit Zwischenschaufeln sind beispielsweise auch aus den Dokumenten
Nachteilig an den der bisherigen Ausführungsformen der Zwischenschaufeln ist, dass es im Schaufelkanal zur voraneilenden Hauptschaufel im Vergleich zum Schaufelkanal zur nacheilenden Hauptschaufel zu unterschiedlichen Geschwindigkeitsprofilen kommt. Damit erhöhen sich die Wirkungsgradverluste innerhalb der Turbine.
Es ist die Aufgabe der vorliegenden Erfindung, die vorgenannten Nachteile zu verringern.A disadvantage of the previous embodiments of the intermediate blades is that it comes in the blade channel to the leading main blade compared to the blade channel to trailing main blade at different speed profiles. This increases the efficiency losses within the turbine.
It is the object of the present invention to reduce the aforementioned disadvantages.
Erfindungsgemäß wird diese Aufgabe durch einen Turbolader mit den Merkmalen des Patentanspruch 1 gelöst.According to the invention this object is achieved by a turbocharger with the features of claim 1.
Demgemäß ist vorgesehen:
- Einen Turbolader für ein oder in einem Kraftfahrzeug, aufweisend ein Laufrad mit jeweils einer zwischen zwei Hauptschaufeln liegender Zwischenschaufel, bereitzustellen, bei dem die Zwischenschaufel wenigstens teilweise einen gegenüber den Hauptschaufeln unterschiedlichen Winkelverlauf aufweist. Dabei ist der Winkelverlauf der Zwischenschaufel derart ausgebildet, dass der Querschnitt des Strömungskanals an der Rückseite der Zwischenschaufel dem Querschnitt des Strömungskanals an der Vorderseite der Zwischenschaufel im Wesentlichen gleich ist und dass bei einem vorgegeben Abstand von der Drehachse die Länge des Kreisbogenabschnitts von der Zwischenschaufel zur nacheilenden Hauptschaufel geringer ist, als die Länge des Kreisbogenabschnitts zur vorauseilenden Hauptschaufel.
- To provide a turbocharger for or in a motor vehicle, comprising an impeller, each with an intermediate blade lying between two main blades, wherein the intermediate blade at least partially has a different angle with respect to the main blades angle. In this case, the angle profile of the intermediate blade is formed such that the cross section of the flow channel at the back of the intermediate blade is substantially equal to the cross section of the flow channel at the front of the intermediate blade and that at a predetermined distance from the axis of rotation, the length of the circular arc portion of the intermediate blade for trailing Main blade is less than the length of the circular arc section to the leading main bucket.
Die der vorliegenden Erfindung zu Grunde liegende Idee besteht darin, im Anströmpfad oder Abströmpfad einer Brennkraftmaschine, eine Vorrichtung bereitzustellen, mit der ein ankommender Gasstrom möglichst gleichmäßig durch ein verdichter- bzw. turbinenseitiges Laufrad geleitet wird. Ein Vorteil der erfindungsgemäßen Vorrichtung ist es, mittels einer von der Hauptschaufel abweichenden Winkelstellung der Zwischenschaufel die Strömungskanäle an der Vorderseite bzw. an der Rückseite der Zwischenschaufel so ausgestaltet werden können, dass der Wirkungsgradverlust verringert wird. Ferner wird die Geräuschentwicklung des Turboladers vermindert und er Einsatzbereich des Turboladers erhöht.The idea on which the present invention is based is to provide a device in the inflow path or outflow path of an internal combustion engine with which an incoming gas stream is conducted as uniformly as possible through a compressor or turbine-side impeller. An advantage of the device according to the invention is that, by means of an angular position of the intermediate blade deviating from the main blade, the flow channels on the front side or on the rear side of the intermediate blade can be designed such that the loss of efficiency is reduced. Furthermore, the noise of the turbocharger is reduced and he increased the range of application of the turbocharger.
Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen sowie aus der Beschreibung in Zusammenschau mit den Zeichnungen.Advantageous embodiments and modifications of the invention will become apparent from the dependent claims and from the description in conjunction with the drawings.
In einer Ausgestaltung sind am drehachsenseitigen Ende der Zwischenschaufel die Längen der Kreisbogenabschnitte von der Vorderseite und der Rückseite der Zwischenschaufel zur nacheilenden und vorauseilenden Hauptschaufel im Wesentlichen gleich.In one embodiment, the lengths of the circular arc sections from the front side and the rear side of the intermediate vane to the trailing and leading main vane are substantially the same at the rotational axis-side end of the intermediate vane.
In einer weiteren Ausgestaltung ist das Laufrad des Abgasturboladers als Turbinenrad (108) oder Verdichterrad (104) ausgebildet.In a further embodiment, the impeller of the exhaust gas turbocharger is formed as a turbine wheel (108) or compressor wheel (104).
Die Erfindung wird nachfolgend an Hand der in den Figuren der Zeichnungen angegebenen Ausführungsbeispiele näher erläutert. Es zeigen dabei:
- Fig. 1
- einen Aufriss eines Turboladers mit einem erfindungsgemäßen Laufrad;
- Fig. 2
- eine schematische Draufsicht auf eine verdichterseitigen Schaufelanordnung;
- Fig. 3
- eine schematische Draufsicht auf den Verlauf der Meridiankoordinate;
- Fig. 4
- eine schematische Darstellung des axialen Winkels der Schaufeln als Funktion einer normierten Meridiankoordinate.
- Fig. 1
- an elevation of a turbocharger with an impeller according to the invention;
- Fig. 2
- a schematic plan view of a compressor-side blade assembly;
- Fig. 3
- a schematic plan view of the course of the meridian coordinate;
- Fig. 4
- a schematic representation of the axial angle of the blades as a function of a normalized meridian coordinate.
In den Figuren sind gleiche und funktionsgleiche Elemente, Merkmale und Größen - sofern nichts Abweichendes angegeben ist - mit denselben Bezugszeichen versehen.In the figures, the same and functionally identical elements, features and sizes - unless otherwise indicated - provided with the same reference numerals.
Das Turbinenrad 108 weist Hauptschaufeln 120 und Zwischenschaufeln 102 auf. Die auslassseitigen Schaufelkanten der Zwischenschaufeln 102 sind gegenüber der auslassseitigen Kante der Hauptschaufeln zurückgesetzt. Der Abgasstrom verlässt die Turbine 118 durch einen Turbinenauslass 114. Über die Welle 110, die das Turbinerad 108 an das Verdichterrad 104 koppelt, treibt die Turbine 118 den Verdichter 116 an. Mittels des Verdichterrades 104 wird im Anströmpfad die angesaugte Luft verdichtet.The
Demgemäß ist die Krümmung der Hauptschaufel 202 in axialer Richtung bei einem gegebenen Achsabstand unterschiedlich und vorzugsweise größer als die Krümmung der Zwischenschaufel 204. Ein Vorteil der unterschiedlichen Krümmung ist es, dass es möglich wird, in Zusammenschau mit den unterschiedlichen Längen in den Kreisbogenabschnitten, die Unterschiede in den Querschnittesflächen der Schaufelkanäle an der Vorder- und Rückseite einer Zwischenschaufel wirkungsvoll zu minimieren.Accordingly, the curvature of the
Eine Zwischenschaufel mit geändertem Winkelverlauf ist mit der durchgezogenen Linie dargestellt. Damit lässt sich das Verhältnis der Strömungsquerschnitte zwischen vorhergehender und nachfolgend Hauptschaufel einstellen.
An intermediate blade with a changed angle is shown by the solid line. This makes it possible to set the ratio of the flow cross sections between the preceding and following main blade.
Ein Vorteil der erfindungsgemäßen Vorrichtung ist es, dass sich durch die besondere Ausbildung d.h. der unterschiedlichen Winkelanordnung der Zwischenschaufeln sowohl in axialer als auch in radialer Richtung im Vergleich zu den Hauptschaufel die Querschnitte der Strömungskanäle entlang der Vorder-und Rückseite der Zwischenschaufeln zuverlässig angleichen lassen. Neben der Erhöhung des Wirkungsgrades wird auch die Laufruhe des Turboladers verbessert.An advantage of the device according to the invention is that due to the special design i. the different angular arrangement of the intermediate blades in both the axial and in the radial direction relative to the main blade, the cross-sections of the flow channels along the front and back of the intermediate blades reliably align. In addition to increasing the efficiency and the smoothness of the turbocharger is improved.
Claims (3)
- Turbocharger for a or in a motor vehicle, having an impeller with in each case one intermediate blade (204) situated between two main blades (202), wherein the intermediate blade (204) at least partially has a different angle profile in relation to the main blades (202), characterized in that the angle profile of the intermediate blade (204) is designed such that the cross section of the flow duct at the rear side of the intermediate blade (204) is substantially equal to the cross section of the flow duct at the front side of the intermediate blade (204), and in that,
at a predefined distance from the axis of rotation, the length of the circular arc segment (206) from the intermediate blade (204) to the trailing main blade (202) is smaller than the length of the circular arc segment (207) to the leading main blade (202). - Turbocharger according to Claim 1,
characterized in that,
at the axis-of-rotation end of the intermediate blade (204), the lengths of the circular arc segments (206, 207) from the front side and the rear side of the intermediate blade (204) to the trailing and leading main blades (202) are substantially equal. - Turbocharger according to either of Claims 1 and 2,
characterized in that
the impeller is designed as a turbine wheel (108) or compressor wheel (104).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007017822A DE102007017822A1 (en) | 2007-04-16 | 2007-04-16 | turbocharger |
PCT/EP2008/052360 WO2008125384A1 (en) | 2007-04-16 | 2008-02-27 | Exhaust gas turbocharger |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2147216A1 EP2147216A1 (en) | 2010-01-27 |
EP2147216B1 true EP2147216B1 (en) | 2017-11-22 |
Family
ID=39526264
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08717167.4A Not-in-force EP2147216B1 (en) | 2007-04-16 | 2008-02-27 | Exhaust gas turbocharger |
Country Status (4)
Country | Link |
---|---|
US (1) | US8512000B2 (en) |
EP (1) | EP2147216B1 (en) |
DE (1) | DE102007017822A1 (en) |
WO (1) | WO2008125384A1 (en) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007017822A1 (en) * | 2007-04-16 | 2008-10-23 | Continental Automotive Gmbh | turbocharger |
FR2946399B1 (en) * | 2009-06-05 | 2016-05-13 | Turbomeca | CENTRIFUGAL COMPRESSOR WHEEL. |
DE102009024568A1 (en) * | 2009-06-08 | 2010-12-09 | Man Diesel & Turbo Se | compressor impeller |
JP5574951B2 (en) * | 2010-12-27 | 2014-08-20 | 三菱重工業株式会社 | Centrifugal compressor impeller |
JP5665535B2 (en) * | 2010-12-28 | 2015-02-04 | 三菱重工業株式会社 | Centrifugal compressor |
IL212729A (en) * | 2011-05-05 | 2015-03-31 | Rafael Advanced Defense Sys | Combined fan-compressor impeller |
US20160281732A1 (en) * | 2015-03-27 | 2016-09-29 | Dresser-Rand Company | Impeller with offset splitter blades |
US10167875B2 (en) | 2016-01-04 | 2019-01-01 | Caterpillar Inc. | Turbocharger compressor and method |
US10087947B2 (en) | 2016-01-04 | 2018-10-02 | Caterpillar Inc. | Turbocharger compressor and method |
US10167876B2 (en) | 2016-01-04 | 2019-01-01 | Caterpillar Inc. | Turbocharger compressor and method |
US10082153B2 (en) | 2016-01-04 | 2018-09-25 | Caterpillar Inc. | Turbocharger compressor and method |
JP2017193985A (en) * | 2016-04-19 | 2017-10-26 | 本田技研工業株式会社 | Turbine impeller |
US10669854B2 (en) | 2017-08-18 | 2020-06-02 | Pratt & Whitney Canada Corp. | Impeller |
RU2667251C1 (en) * | 2017-10-05 | 2018-09-18 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Box of drive units |
SE1950700A1 (en) | 2019-06-13 | 2020-12-01 | Scania Cv Ab | Centrifugal Compressor Impeller for a Charging Device of an Internal Combustion Engine |
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DE174855C (en) | 1905-08-19 | 1906-10-01 | Wittig Emil | IMPELLER FOR FANS |
US2484554A (en) * | 1945-12-20 | 1949-10-11 | Gen Electric | Centrifugal impeller |
US3006603A (en) * | 1954-08-25 | 1961-10-31 | Gen Electric | Turbo-machine blade spacing with modulated pitch |
GB941343A (en) * | 1961-08-29 | 1963-11-13 | Rudolph Birmann | Improvements in or relating to impeller blading for centrifugal compressors |
US4093401A (en) * | 1976-04-12 | 1978-06-06 | Sundstrand Corporation | Compressor impeller and method of manufacture |
JPS6017296A (en) * | 1983-07-08 | 1985-01-29 | Matsushita Electric Ind Co Ltd | Vane wheel of crossing current blower |
FR2550585B1 (en) * | 1983-08-09 | 1987-01-16 | Foueillassar Jean Marie | MEANS OF UNIFORMING THE SPEED OF A FLUID AT THE OUTPUT OF A CENTRIFUGAL WHEEL |
US4693669A (en) * | 1985-03-29 | 1987-09-15 | Rogers Sr Leroy K | Supercharger for automobile engines |
US4904158A (en) * | 1988-08-18 | 1990-02-27 | Union Carbide Corporation | Method and apparatus for cryogenic liquid expansion |
US5002461A (en) * | 1990-01-26 | 1991-03-26 | Schwitzer U.S. Inc. | Compressor impeller with displaced splitter blades |
US5639217A (en) * | 1996-02-12 | 1997-06-17 | Kawasaki Jukogyo Kabushiki Kaisha | Splitter-type impeller |
GB2337795A (en) * | 1998-05-27 | 1999-12-01 | Ebara Corp | An impeller with splitter blades |
US6663347B2 (en) * | 2001-06-06 | 2003-12-16 | Borgwarner, Inc. | Cast titanium compressor wheel |
JP3876195B2 (en) * | 2002-07-05 | 2007-01-31 | 本田技研工業株式会社 | Centrifugal compressor impeller |
US7147433B2 (en) * | 2003-11-19 | 2006-12-12 | Honeywell International, Inc. | Profiled blades for turbocharger turbines, compressors, and the like |
US7841506B2 (en) * | 2004-08-11 | 2010-11-30 | Honeywell International Inc. | Method of manufacture of dual titanium alloy impeller |
TW200722627A (en) * | 2005-12-15 | 2007-06-16 | Ind Tech Res Inst | Centrifugal type pressure-increasing impeller structure |
DE102007017822A1 (en) * | 2007-04-16 | 2008-10-23 | Continental Automotive Gmbh | turbocharger |
-
2007
- 2007-04-16 DE DE102007017822A patent/DE102007017822A1/en not_active Withdrawn
-
2008
- 2008-02-27 WO PCT/EP2008/052360 patent/WO2008125384A1/en active Application Filing
- 2008-02-27 US US12/596,157 patent/US8512000B2/en not_active Expired - Fee Related
- 2008-02-27 EP EP08717167.4A patent/EP2147216B1/en not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
DE102007017822A1 (en) | 2008-10-23 |
WO2008125384A1 (en) | 2008-10-23 |
US8512000B2 (en) | 2013-08-20 |
EP2147216A1 (en) | 2010-01-27 |
US20100254816A1 (en) | 2010-10-07 |
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