EP2092174B1 - Turbocharger - Google Patents

Turbocharger Download PDF

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Publication number
EP2092174B1
EP2092174B1 EP07819254.9A EP07819254A EP2092174B1 EP 2092174 B1 EP2092174 B1 EP 2092174B1 EP 07819254 A EP07819254 A EP 07819254A EP 2092174 B1 EP2092174 B1 EP 2092174B1
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor shaft
rotor
turbine wheel
wheel
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
Application number
EP07819254.9A
Other languages
German (de)
French (fr)
Other versions
EP2092174A1 (en
Inventor
Christian Holzschuh
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Publication of EP2092174A1 publication Critical patent/EP2092174A1/en
Application granted granted Critical
Publication of EP2092174B1 publication Critical patent/EP2092174B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/16—Control of the pumps by bypassing charging air
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F01D25/186—Sealing means for sliding contact bearing
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/16—Other safety measures for, or other control of, 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbocharger according to the preamble of claim 1.
  • a generic turbocharger is from the US 5 176 497 A .
  • EP 1 394 387 A US 2000/001522 A1 or the WO 99/07982 A known.
  • the piston ring recesses or grooves were always arranged in the rotor shaft.
  • one respective groove is provided per piston ring or that two piston rings are arranged in a groove.
  • the turbinenradnahe Kolbenringnut requires a constructive minimum distance from the turbine and the connection pin is kept axially as short as possible at the Turbinenraapp, it is not yet possible to introduce two grooves in the shaft area without weakening the shaft in cross section or without axially extending the shaft, which is very negative Effects on rotor bearing stability. If the turbine wheel and the rotor shaft connected by a weld, it was not possible, the Kolbenringnuten arbitrary
  • the area of the weld is not suitable for the attachment of the grooves.
  • turbocharger for an internal combustion engine according to the preamble of claim 1, which has a turbine rotor, which allows without increasing the axial rotor length to avoid deterioration of the arrangement by the attachment of piston ring grooves.
  • Fig. 1 an inventive turbocharger 1 is illustrated in a partially broken view.
  • the turbocharger 1 has a turbine 2 which comprises an exhaust gas inlet opening 3 and an exhaust gas outlet opening 4.
  • a turbine wheel 5 is disposed in the turbine housing of the turbine 2, which is fixed to one end of a rotor shaft 6.
  • a plurality of blades is arranged in the turbine housing between the exhaust gas inlet opening 3 and the turbine wheel 5.
  • the turbocharger 1 has a compressor 8, which comprises a compressor wheel 9, which is fastened on the other end of the rotor shaft 6 and arranged in the compressor housing 8 of the compressor.
  • turbocharger 1 also includes all other conventional components of a turbocharger, such as a bearing housing with a bearing housing unit, etc., which, however, will not be described below since they are not necessary for the explanation of the principles of the present invention.
  • FIG. 2 is a part of a turbine rotor 10 shown in section, the rotor shaft 6 and the turbine wheel 5 with the inventive arrangement of Kolbenringeinsstichen 11, 11 ' on an extended, one-piece connecting pin 17 of the turbine wheel 5 shows.
  • this shaping of the turbine wheel 5 it is achieved that all structurally required piston ring punctures 11, 11 'are formed in the heat-resistant material of the turbine wheel 5 which is more heat-resistant than the material alloy of the rotor shaft 6.
  • This arrangement of Kolbenringeinsstiche 11, 11 'in identical material creates identical tribological conditions for the piston rings to be installed therein (which are not shown in this figure).
  • the turbine wheel 5 has a cylindrical cavity 15 whose depth L, measured from the axial shaft-side end face 14 of the connecting pin 17 to a wheel back 13 of the turbine wheel 5, is smaller than a length B of the connecting pin 17.
  • the rotor shaft 6 and the turbine wheel 5 can be connected to each other at the connection plane A either by friction welding or electron beam welding.
  • the rotor shaft 6 has a short stub shaft 16.
  • the inventive design of the connecting pin 17 of the turbine wheel 5 has the advantage that it can be easily pressed onto the stub shaft 16 and the risks of the occurrence of stresses during the welding process and possible resulting cracking can be minimized by the existing at the connection level A on both components material or wall thicknesses.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Description

Die Erfindung betrifft einen Turbolader gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a turbocharger according to the preamble of claim 1.

Ein gattungsgemäßer Turbolader ist aus der US 5 176 497 A , EP 1 394 387 A , US 2000/001522 A1 oder der WO 99/07982 A bekannt.A generic turbocharger is from the US 5 176 497 A . EP 1 394 387 A . US 2000/001522 A1 or the WO 99/07982 A known.

Bei derartigen Turboladern wurden die Kolbenringeinstiche bzw. -nuten stets in der Rotorwelle angeordnet. Hierbei ist es möglich, dass pro Kolbenring je eine Nut vorgesehen ist oder dass zwei Kolbenringe in einer Nut angeordnet sind. Da die turbinenradnahe Kolbenringnut einen konstruktiven Mindestabstand vom Turbinenrad erfordert und der Anbindungszapfen am Turbinenradrücken axial möglichst kurz gehalten wird, ist es bisher nicht möglich zwei Nuten in den Wellenbereich einzubringen ohne die Welle im Querschnitt zu schwächen oder ohne die Welle axial zu verlängern, was sehr negative Auswirkungen auf die Rotorlagerstabilität zur Folge hat. Werden das Turbinenrad und die Rotorwelle durch eine Schweißung verbunden, war es bisher nicht möglich, die Kolbenringnuten beliebigIn such turbochargers, the piston ring recesses or grooves were always arranged in the rotor shaft. In this case, it is possible that one respective groove is provided per piston ring or that two piston rings are arranged in a groove. Since the turbinenradnahe Kolbenringnut requires a constructive minimum distance from the turbine and the connection pin is kept axially as short as possible at the Turbinenradrücken, it is not yet possible to introduce two grooves in the shaft area without weakening the shaft in cross section or without axially extending the shaft, which is very negative Effects on rotor bearing stability. If the turbine wheel and the rotor shaft connected by a weld, it was not possible, the Kolbenringnuten arbitrary

zu platzieren, da der Bereich der Schweißstelle aufgrund uneinheitlicher Materialeigenschaften nicht für die Anbringung der Nuten geeignet ist.due to non-uniform material properties, the area of the weld is not suitable for the attachment of the grooves.

Es ist demgegenüber Aufgabe der vorliegenden Erfindung, einen Turbolader für einen Verbrennungsmotor gemäß dem Oberbegriff des Anspruchs 1 zu schaffen, der einen Turbinenrotor aufweist, der ohne Vergrößerung der axialen Rotorlänge die Vermeidung von Festigkeitsminderungen der Anordnung durch die Anbringung von Kolbenringnuten ermöglicht.It is accordingly an object of the present invention to provide a turbocharger for an internal combustion engine according to the preamble of claim 1, which has a turbine rotor, which allows without increasing the axial rotor length to avoid deterioration of the arrangement by the attachment of piston ring grooves.

Hinsichtlich des erfindungsgemäßen Turboladers erfolgt die Lösung dieser Aufgabe durch die Merkmale des Anspruchs 1. Hinsichtlich des Turbinenrotors, der ein selbstständig handelbares Objekt darstellt, erfolgt die Lösung dieser Aufgabe durch die Merkmale des Anspruchs 5.With regard to the turbocharger according to the invention, this object is achieved by the features of claim 1. With regard to the turbine rotor, which is an independently tradable object, the solution of this object is achieved by the features of claim 5.

So ist es bei der erfindungsgemäßen Ausbildung des Turbinenrads möglich, eine Mehrzahl von erforderlichen Kolbenringeinstichen komplett in das Material des Turbinenrades zu integrieren. Dadurch werden die Nachteile des Standes der Technik vermieden. Der Vorteil der erfin-dungsgemäßen Ausbildung besteht darin, dass alle Kolbenringeinstiche einerseits in dem gegenüber dem Material der Rotorwelle hitzebeständigeren Material liegen und andererseits entsprechend entfernt von der Verbindungsebene zwischen Rotorwelle und Turbinenrad platziert sind, woraus eine Erhöhung der Festigkeit des gesamten Turbinenrotors resultiert.Thus, in the case of the turbine wheel design according to the invention, it is possible to completely integrate a plurality of required piston ring punctures into the material of the turbine wheel. This avoids the disadvantages of the prior art. The advantage of the embodiment according to the invention is that all piston ring punctures lie, on the one hand, in the material which is more heat-resistant with respect to the material of the rotor shaft and, on the other hand, correspondingly placed away from the connection plane between rotor shaft and turbine wheel, resulting in an increase in the strength of the entire turbine rotor.

Weitere Einzelheiten, Vorteile und Merkmale der Erfindung ergeben sich aus nachfolgender Beschreibung eines Ausführungsbeispiels und der Zeichnung.Further details, advantages and features of the invention will become apparent from the following description of an embodiment and the drawing.

Es zeigt:

  • Fig. 1 eine teilweise aufgebrochene perspektivische Darstellung des erfindungsgemäßen Turboladers, und
  • Fig. 2 eine Querschnittsansicht des Turbinenrotors mit zwei Kolbenringeinsstichen
It shows:
  • Fig. 1 a partially broken perspective view of the turbocharger according to the invention, and
  • Fig. 2 a cross-sectional view of the turbine rotor with two Kolbenringeinsstichen

In Fig. 1 ist ein erfindungsgemäßer Turbolader 1 in teilweise aufgebrochener Darstellung veranschaulicht.In Fig. 1 an inventive turbocharger 1 is illustrated in a partially broken view.

Der Turbolader 1 weist eine Turbine 2 auf, die eine Abgaseintrittsöffnung 3 und eine Abgasaustrittöffnung 4 umfasst.The turbocharger 1 has a turbine 2 which comprises an exhaust gas inlet opening 3 and an exhaust gas outlet opening 4.

Ferner ist im Turbinengehäuse der Turbine 2 ein Turbinenrad 5 angeordnet, das auf einem Ende einer Rotorwelle 6 befestigt ist.Further, a turbine wheel 5 is disposed in the turbine housing of the turbine 2, which is fixed to one end of a rotor shaft 6.

Eine Mehrzahl von Schaufeln, von denen in Fig. 1 nur die Schaufel 7 zu sehen ist, ist im Turbinengehäuse zwischen der Abgaseintrittsöffnung 3 und dem Turbinenrad 5 angeordnet.A plurality of blades, of which in Fig. 1 only the blade 7 can be seen, is arranged in the turbine housing between the exhaust gas inlet opening 3 and the turbine wheel 5.

Ferner weist der Turbolader 1 einen Verdichter 8 auf, der ein Verdichterrad 9 umfasst, das auf dem anderen Ende der Rotorwelle 6 befestigt und im Verdichtergehäuse des Verdichters 8 angeordnet ist.Furthermore, the turbocharger 1 has a compressor 8, which comprises a compressor wheel 9, which is fastened on the other end of the rotor shaft 6 and arranged in the compressor housing 8 of the compressor.

Natürlich weist der erfindungsgemäße Turbolader 1 auch alle anderen üblichen Bauteile eines Turboladers, wie ein Lagergehäuse mit einer Lagergehäuseeinheit usw., auf, die jedoch nachfolgend nicht beschrieben werden, da sie für die Erläuterung der Prinzipien vorliegender Erfindung nicht erforderlich sind.Of course, the turbocharger 1 according to the invention also includes all other conventional components of a turbocharger, such as a bearing housing with a bearing housing unit, etc., which, however, will not be described below since they are not necessary for the explanation of the principles of the present invention.

In Fig. 2 ist ein Teil eines Turbinenrotors 10 im Schnitt dargestellt, der die Rotorwelle 6 und das Turbinenrad 5 mit der erfindungsgemäßen Anordnung von Kolbenringeinsstichen 11, 11' auf einem verlängerten, einstückigen Anbindungszapfen 17 des Turbinenrads 5 zeigt. Durch diese Formgebung des Turbinenrads 5 wird erreicht, dass alle konstruktiv benötigten Kolbenringeinsstiche 11, 11' im gegenüber der Materiallegierung der Rotorwelle 6 hitzebeständigeren Material des Turbinenrads 5 ausgebildet sind. Diese Anordnung der Kolbenringeinsstiche 11, 11' in identischem Material schafft identische tribologische Verhältnisse für die darin einzubauenden Kolbenringe (die in dieser Figur nicht dargestellt sind). Die Lage der Kolbenringeinsstiche 11, 11' sowie der deutliche, in Fig. 2 ersichtliche Abstand von der Verbindungsebene A zwischen der Rotorwelle 6 und dem ersten Kolbenringeinstich 11 erhöhen die Festigkeit der Gesamtanordnung des Turbinenrotors 10 in hohem Maße. Nachteilige Einflüsse durch das Fügeverfahren zur Verbindung der Rotorwelle 6 und des Turbinenrads 5, wie z. B. eine geringere Härte oder Härtespitzen an den Kolbenringeinsstichen 11, 11' können somit gegenüber dem Stand der Technik weitestgehend eliminiert werden.In Fig. 2 is a part of a turbine rotor 10 shown in section, the rotor shaft 6 and the turbine wheel 5 with the inventive arrangement of Kolbenringeinsstichen 11, 11 ' on an extended, one-piece connecting pin 17 of the turbine wheel 5 shows. As a result of this shaping of the turbine wheel 5, it is achieved that all structurally required piston ring punctures 11, 11 'are formed in the heat-resistant material of the turbine wheel 5 which is more heat-resistant than the material alloy of the rotor shaft 6. This arrangement of Kolbenringeinsstiche 11, 11 'in identical material creates identical tribological conditions for the piston rings to be installed therein (which are not shown in this figure). The location of the Kolbenringeinsstiche 11, 11 'and the clear, in Fig. 2 apparent distance from the joint plane A between the rotor shaft 6 and the first piston ring recess 11 increase the strength of the overall arrangement of the turbine rotor 10 to a great extent. Adverse influences by the joining method for connecting the rotor shaft 6 and the turbine wheel 5, such. As a lower hardness or hardness peaks on the Kolbenringeinsstichen 11, 11 'can thus be largely eliminated over the prior art.

Wie ferner aus der Schnittzeichnung in Fig. 2 ersichtlich, weist das Turbinenrad 5 einen zylindrischen Hohlraum 15 auf, dessen Tiefe L, gemessen von der axialen wellenseitigen Endfläche 14 des Anbindungszapfens 17 bis zu einem Radrücken 13 des Turbinenrads 5, kleiner als eine Länge B des Anbindungszapfens 17 ist.As further from the sectional drawing in Fig. 2 As can be seen, the turbine wheel 5 has a cylindrical cavity 15 whose depth L, measured from the axial shaft-side end face 14 of the connecting pin 17 to a wheel back 13 of the turbine wheel 5, is smaller than a length B of the connecting pin 17.

Die Rotorwelle 6 und das Turbinenrad 5 können an der Verbindungsebene A entweder durch Reibschweißung oder Elektronenstrahlschweissung miteinander verbunden werden. Wie aus der Zeichnung von Fig. 2 ersichtlich ist, weist die Rotorwelle 6 einen kurzen Wellenstumpf 16 auf. Für den Fügevorgang durch Elektronenstrahlschweißung hat die erfindungsgemäße Ausbildung des Anbindungszapfens 17 des Turbinenrads 5 den Vorteil, dass dieser einfach auf den Wellenstumpf 16 aufgepresst werden kann und die Risiken des Auftretens von Spannungen beim Schweißvorgang und mögliche daraus folgende Rissbildungen durch die an der Verbindungsebene A an beiden Bauteilen vorhandenen Material- bzw. Wandstärken minimiert werden können.The rotor shaft 6 and the turbine wheel 5 can be connected to each other at the connection plane A either by friction welding or electron beam welding. As from the drawing of Fig. 2 it can be seen, the rotor shaft 6 has a short stub shaft 16. For the joining process by electron beam welding, the inventive design of the connecting pin 17 of the turbine wheel 5 has the advantage that it can be easily pressed onto the stub shaft 16 and the risks of the occurrence of stresses during the welding process and possible resulting cracking can be minimized by the existing at the connection level A on both components material or wall thicknesses.

Zur Ergänzung der Offenbarung wird explizit auf die zeichnerische Darstellung der Erfindung in den Figuren 1 und 2 verwiesen.To supplement the disclosure is explicitly to the drawings of the invention in the Figures 1 and 2 directed.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Turbolader/AbgasturboladerTurbocharger / turbocharger
22
Turbineturbine
33
AbgaseintrittsöffnungExhaust gas inlet opening
44
AbgasaustrittsöffnungExhaust gas outlet opening
55
Turbinenradturbine
66
Rotorwellerotor shaft
77
Schaufelnshovel
88th
Kompressorcompressor
99
Kompressorradcompressor
1010
Turbinenrotorturbine rotor
11, 11'11, 11 '
KolbenringeinstichPiston ring groove
1212
Anschlußteilconnector
1313
Radrückenwheel rear side
1414
wellenseitige Endflächewave-side end face
1515
Hohlraumcavity
1616
Wellenstumpfstub shaft
1717
Anbindungszapfenconnection pins
AA
Verbindungsebeneconnecting plane
LL
Tiefe des Hohlraums (der Kalotte)Depth of the cavity (the dome)
BB
Länge des AnbindungszapfensLength of the connecting pin

Claims (3)

  1. Turbocharger (1)
    - with a compressor (8), which has a compressor wheel (9) which is fixed on one end of a rotor shaft (6);
    - with a turbine (2), which has a turbine rotor (10), which comprises a turbine wheel (5) which has a connecting journal (17) which can be connected to a connecting section (12) of the rotor shaft (6), and
    - with at least one piston ring groove (11, 11'), which is provided on the turbine rotor (10); characterized in that
    - two piston ring grooves (11, 11') are arranged on the connecting journal (17), and in that
    - the connecting journal (17) of the turbine wheel (5) has a cylindrical cavity (15), the depth (L) of which is smaller than a length (B) of the connecting journal (17), measured from an axial shaft-side end face (14) of the rotor shaft (6) to a wheel back (13) of the turbine wheel (5).
  2. Turbocharger according to Claim 1, characterized in that
    a connecting plane (A) is arranged between the rotor shaft (6) and the turbine wheel (5) at a distance to the nearest piston ring groove (11, 11').
  3. Turbocharger according to Claim 1, characterized in that
    the turbine wheel (5) and the rotor shaft (6) are connected by means of a friction weld or by means of an electron beam weld.
EP07819254.9A 2006-12-11 2007-10-23 Turbocharger Not-in-force EP2092174B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006058339 2006-12-11
PCT/EP2007/009193 WO2008071253A1 (en) 2006-12-11 2007-10-23 Turbocharger

Publications (2)

Publication Number Publication Date
EP2092174A1 EP2092174A1 (en) 2009-08-26
EP2092174B1 true EP2092174B1 (en) 2015-09-09

Family

ID=39015735

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07819254.9A Not-in-force EP2092174B1 (en) 2006-12-11 2007-10-23 Turbocharger

Country Status (6)

Country Link
US (1) US8465261B2 (en)
EP (1) EP2092174B1 (en)
JP (1) JP2010512481A (en)
KR (1) KR20090087885A (en)
CN (1) CN101542088A (en)
WO (1) WO2008071253A1 (en)

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WO2008071253A1 (en) 2008-06-19
US20100003132A1 (en) 2010-01-07
KR20090087885A (en) 2009-08-18
US8465261B2 (en) 2013-06-18
CN101542088A (en) 2009-09-23
JP2010512481A (en) 2010-04-22
EP2092174A1 (en) 2009-08-26

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