EP2071242A1 - Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks - Google Patents
Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks Download PDFInfo
- Publication number
- EP2071242A1 EP2071242A1 EP08169015A EP08169015A EP2071242A1 EP 2071242 A1 EP2071242 A1 EP 2071242A1 EP 08169015 A EP08169015 A EP 08169015A EP 08169015 A EP08169015 A EP 08169015A EP 2071242 A1 EP2071242 A1 EP 2071242A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- air
- venturi
- injection system
- ducts
- annular
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 29
- 238000002485 combustion reaction Methods 0.000 title claims description 11
- 239000000203 mixture Substances 0.000 title claims description 11
- 239000000571 coke Substances 0.000 claims abstract description 12
- 239000004071 soot Substances 0.000 claims abstract description 9
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 8
- 230000008021 deposition Effects 0.000 claims abstract description 6
- 238000002347 injection Methods 0.000 claims description 45
- 239000007924 injection Substances 0.000 claims description 45
- 238000011144 upstream manufacturing Methods 0.000 claims description 27
- 238000005219 brazing Methods 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 239000012530 fluid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
Definitions
- the present invention relates to a system for injecting a mixture of air and fuel into a combustion chamber of a turbomachine, such as an airplane turbojet or turboprop engine.
- An injection system of this type generally comprises a fuel injector and primary and secondary tendrils which are arranged downstream of the injector, coaxially with it, and which each delimit a radial air flow downstream of the injector.
- the air flows from the two tendrils are delimited by a venturi inserted between the two tendrils and a frustoconical bowl which is mounted downstream of the tendrils and which accelerate the flow of the air / fuel mixture towards the combustion chamber.
- the venturi has an inner surface having a constriction or narrowing and delimiting a premix chamber in which are mixed a portion of the fuel ejected by the injector and the air flow delivered by the primary swirler
- the present invention is intended in particular to provide a simple, effective and economical solution to these problems of the prior art.
- a system for injecting a mixture of air and of fuel in a turbomachine combustion chamber comprising a fuel injector and a venturi disposed downstream of the injector, coaxially thereto, the venturi having an inner surface delimiting a premix chamber in which fuel is mixed and a flow of air coming from an external enclosure and passing through a primary swirler upstream of the venturi, characterized in that the venturi comprises an internal annular cavity for air circulation, this cavity being connected by inlet ducts, air to the outer enclosure and through air outlet ducts to the premix chamber, the air outlet ducts opening on the inner surface of the venturi to prevent the deposition of soot and the formation of coke on this surface .
- a flow of air coming from an external enclosure circulates in the internal cavity of the venturi and is then injected into the premixing chamber, through air outlet ducts opening onto the inner surface of the venturi, for forming a film of air near this surface opposing the deposition of soot and the formation of coke on this surface.
- the flow of air injected into the premix chamber is sufficient to prevent the air / fuel mixture coming into contact with the inner surface of the venturi, but is also small enough not to impede the flow of air and the air. injection of fuel inside the venturi and not to cause flow detachment at the outlet of the venturi.
- the air flow circulating in the internal cavity of the venturi represents approximately 0.5 to 1% of the air flow supplying the injection system.
- the venturi comprises at its upstream end an annular flange extending radially outwards and separating the primary swirler from a secondary swirl of passage of a second air flow, the cavity annular extending into the venturi rim.
- the annular cavity has a substantially L-shaped section.
- the venturi is formed of two annular pieces of substantially L-shaped section which are coaxially engaged one inside the other and which are fixed to each other by brazing or welding, the first and the second piece parts delimiting between them the annular cavity of air circulation.
- the first part extends upstream and inside the second part and has a substantially radial upstream annular wall which is connected at its inner periphery to a substantially cylindrical downstream wall in which the air outlet ducts are formed.
- the second part comprises a substantially radial upstream annular wall which is connected at its inner periphery to a substantially cylindrical downstream wall, the radial wall being fixed at its outer periphery to the outer periphery of the radial wall of the first part, and its cylindrical wall. being attached at its downstream end to the downstream end of the cylindrical wall of the first piece.
- At least a portion of the air inlet ducts may extend substantially radially relative to the axis of the injector and be formed at the outer periphery of the radial wall of one or each part.
- the air coming from the external enclosure then passes radially from outside to inside directly inside the internal cavity of the venturi.
- At least a portion of the air inlet ducts extend substantially parallel to the axis of the injector and are formed through blades of the secondary swirler and the radial wall of the second room.
- air from the outer enclosure flows axially downstream upstream in the ducts formed in the vanes of the secondary auger and in the radial wall of the second part into the internal cavity of the venturi.
- the air outlet ducts are inclined axially and circumferentially with respect to the axis of the injector, in the same direction as the vanes of the primary swirler, so that that the air leaving these ducts does not disturb the flow of air delivered by the primary swirler and does not impact the head of the injector.
- the invention thus makes it possible to prevent the formation of coke on the venturi without modifying the flow of air and fuel injection inside the venturi.
- each outlet duct formed between the axis of this duct and the axis of the injector is for example between 10 and 40 °, this angle being measured in a plane passing through the axis of the injector.
- each outlet duct formed between the axis of this duct and a plane passing through the axis of the injector is, for example, between approximately 50 and 75 °, this angle being measured in a plane perpendicular to the axis of the injector.
- the outlets of the air outlet ducts are regularly arranged around the axis of the injector and are distributed in one, two, three or four annular rows spaced axially from each other.
- the inclinations in the axial and circumferential direction of the air ducts may vary from row to row.
- the injection system comprises for example between 10 and 30 air inlet ducts and between 10 and 30 air outlet ducts.
- the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising an injection system as described above.
- the invention also relates to a venturi for an injection system as described above, comprising an inner surface having a neck, characterized in that it is formed of two annular pieces of substantially L-shaped section which are coaxially attached to one another. inside the other and which delimit between them an internal cavity of air circulation, the inner annular part having a cylindrical wall having air outlet ducts connected at one of their ends to the internal cavity and opening at the other of their ends on the inner surface, and the outer annular wall having a radial annular wall having at its outer periphery air inlet ducts connected at one of their ends to the internal cavity.
- the figure 1 represents an annular combustion chamber 10 of a turbomachine such as a turbojet engine or an airplane turboprop, this chamber being arranged at the outlet of a diffuser 12, itself located at the outlet of a compressor (not shown).
- the chamber 10 comprises a wall of internal revolution 14 and a wall of external revolution 16, connected upstream to an annular wall 18 of the chamber bottom and attached downstream by internal and external 20 frustoconical ferrules 22 respectively on an internal frustoconical web 24 of the diffuser, and on an outer casing 26 of the chamber, the upstream end of this housing 26 being connected to an outer frustoconical web 28 of the diffuser.
- An annular fairing 29 is attached to the upstream ends of the walls 14, 16 and 18 of the chamber and includes air passage holes aligned with openings 30 of the wall 18 of the chamber floor in which are mounted systems 32 for injecting a mixture of air and fuel into the chamber, the air coming from the diffuser 12 and the fuel being supplied by injectors (not shown) fixed on the outer casing 26 and regularly distributed around the axis of the room.
- Each injector comprises a fuel injection head 36 aligned with the axis 38 of the corresponding opening 30.
- the other part of the air flow enters the annular enclosure 46 defined by the shroud 29, passes into the injection system 32 (arrows 48 and 50), and is then mixed with the fuel supplied by the injector and sprayed in the combustion chamber.
- the injection system 32 comprises two coaxial upstream turbulence swirlers 52 and downstream 54 which are separated from each other by a venturi 56 and which are connected upstream to means 58 for centering and guiding the injector head 36 and downstream to a mixing bowl 60 which is mounted axially in the opening 30 of the wall 18 of the chamber bottom.
- the swirlers 52, 54 each comprise a plurality of vanes extending radially around the axis of the swirler and regularly distributed around this axis to deliver a flow of air 48, 50 swirling downstream of the injection head 36.
- the means 58 for guiding the injection head 36 of the injector comprise a ring 62 traversed axially by the injection head 36 and mounted radially sliding in a socket 64 fixed on the vanes of the primary swirler 52.
- the mixing bowl 60 has a substantially frustoconical wall flared downstream and connected at its downstream end to a cylindrical flange 66, extending upstream and axially mounted in the opening 30 of the wall 18 of the chamber bottom with a deflector ring 68.
- the upstream end of the wall frustoconical 60 of the bowl is connected to an intermediate annular piece 70 fixed on the vanes of the secondary swirler 54.
- the venturi 56 has a substantially L-shaped cross section and comprises at its upstream end a substantially radial annular flange 71 which is interposed axially between the two tendrils 52, 54 and which axially delimits with the bushing 64 located upstream the annular passing channel.
- the venturi 56 extends axially downstream to the interior of the secondary swirler 54 and separates the air flows coming from upstream tendrils 52 and downstream 54.
- the venturi 56 comprises an inner cylindrical surface 72 having a neck and delimiting a premix chamber 74 in which a portion of the ejected fuel mixes with the air flow 48 delivered by the primary swirler 52. This air / fuel premix then mixes with downstream of the venturi to the air stream 50 from the secondary swirler 54 to form a sprayed fuel cone within the chamber.
- the air / fuel premix formed in the chamber 74 can come into contact with the inner surface 72 of the venturi and cause the deposition of soot and the formation of coke on this surface, which can reduce the life of the venturi 56.
- the invention overcomes this problem through the formation of an air film on the inner surface 72 of the venturi which opposes the deposit of coke and soot on this surface.
- This result is obtained by means of a hollow venturi comprising an internal annular cavity for circulating air, this cavity being supplied with air coming from the outer enclosure 46 and being connected to air outlet ducts opening on the inner surface 72 of the venturi.
- the venturi 56 is formed of two annular pieces 80, 82 with section substantially L-shaped which are fixed coaxially one inside the other and which delimit between them the annular cavity 84 of air flow.
- This cavity 84 also has a substantially L-shaped section and comprises a cylindrical portion which extends axially inside the venturi, over substantially its entire axial dimension, and which is connected at its upstream end to a radial portion which is extends inside the flange of the venturi, over substantially its entire radial dimension.
- Each piece 80, 82 comprises a substantially radial upstream annular wall 86 which is connected at its inner periphery to a substantially cylindrical downstream wall 88.
- the radial walls 86 of the parts 80, 82 form the annular flange 71 of the venturi.
- the downstream and outboard part 82 further comprises a cylindrical flange 90 which extends upstream from the outer periphery of the radial wall 86 and which is attached by brazing or welding to the outer periphery of the wall. radial 86 of the other room 80.
- This cylindrical flange 88 comprises orifices or ducts 92 of substantially radial air inlet which provide fluid communication between the enclosure 46 and the internal cavity 84 of the venturi.
- the injection system 32 comprises for example between 10 and 30 conduits 92 which are regularly distributed around the axis of the venturi.
- the downstream end of the cylindrical wall 88 of the part 82 is fixed by brazing or welding at the downstream end of the cylindrical wall of the other part.
- the cylindrical wall 88 of the piece 80 located upstream and inside comprises orifices or air outlet ducts 94 which open at one of their ends on the inner surface 72 of the venturi and at the other of their ends. in the internal cavity 84, to ensure fluid communication between this cavity 84 and the premix chamber 74.
- the injection system 32 comprises for example between 10 and 30 ducts 94 which are distributed in annular rows, for example three in number in the example shown, which are spaced axially each other.
- the air ducts 94 of each row are regularly spaced from each other about the axis of the injection head.
- the angle formed between the axis of each outlet duct 94 and the axis of the injection head 36 is between approximately 10 and 40 °, this angle being measured in a plane passing through the axis of the injection head.
- the angle formed between the axis of each outlet duct 94 and a plane passing through the axis of the injection head is between approximately 50 and 75 °, this angle being measured in a plane perpendicular to the axis of the injection head.
- the ducts 94 of the same annular row of ducts have identical inclinations in axial and circumferential directions but which may be different from the inclinations of the ducts of the or each other row.
- the inclination in the axial direction of the ducts 94 of the first row located upstream may for example be lower than that of the pipes of the third row located downstream ( figure 4 ).
- FIGS 5 to 7 represent an alternative embodiment of the invention which comprises, in addition to the characteristics described with reference to the Figures 3 and 4 , additional ducts 96 of air inlet into the internal cavity 84 of the venturi. These ducts 96 extend substantially parallel to the axis of the venturi and also connect the internal cavity 84 of the venturi to the outer enclosure 46.
- these ducts 96 extend through the radial wall of the piece 82 located downstream and outward, through at least a portion of the vanes of the secondary swirler 54, and through the element.
- the ducts 96 open at their upstream ends into the internal cavity 84 and at their downstream ends into an annular space delimited by the element 70 and the bowl 60, this annular space communicating with the external enclosure 46.
- injection comprises for example between 10 and 30 ducts 96.
- the ducts 96 may have a section of circular or oblong shape.
- the ducts 92 and 94 described above may also have in section a circular or oblong shape.
- the dimensions of these ducts 92, 94, 96 are in particular determined as a function of the flow rate of air inside the cavity. They typically have a diameter of about 1 to 2 mm.
- the flow rate of air circulating inside the cavity 84 represents approximately 0.5 to 1% of the flow rate of air supplying the injection system 32.
- the inner cavity 84 is connected to the outer enclosure 46 only by the axial ducts 96 of air inlet.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
- Fuel-Injection Apparatus (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0708703A FR2925146B1 (fr) | 2007-12-14 | 2007-12-14 | Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2071242A1 true EP2071242A1 (de) | 2009-06-17 |
EP2071242B1 EP2071242B1 (de) | 2017-08-02 |
Family
ID=39493567
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08169015.8A Active EP2071242B1 (de) | 2007-12-14 | 2008-11-13 | Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks |
Country Status (6)
Country | Link |
---|---|
US (1) | US8312723B2 (de) |
EP (1) | EP2071242B1 (de) |
JP (1) | JP5260245B2 (de) |
CA (1) | CA2646959C (de) |
FR (1) | FR2925146B1 (de) |
RU (1) | RU2478878C2 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3033030A1 (fr) * | 2015-02-20 | 2016-08-26 | Snecma | Systeme d'injection d'un melange air-carburant dans une chambre de combustion de turbomachine d'aeronef, comprenant un venturi perfore de trous d'injection d'air |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2903169B1 (fr) * | 2006-06-29 | 2011-11-11 | Snecma | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
FR2941288B1 (fr) | 2009-01-16 | 2011-02-18 | Snecma | Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
FR2952166B1 (fr) * | 2009-11-05 | 2012-01-06 | Snecma | Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air |
US9951955B2 (en) | 2011-05-17 | 2018-04-24 | Snecma | Annular combustion chamber for a turbine engine |
FR2980554B1 (fr) * | 2011-09-27 | 2013-09-27 | Snecma | Chambre annulaire de combustion d'une turbomachine |
FR2986856B1 (fr) | 2012-02-15 | 2018-05-04 | Safran Aircraft Engines | Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine |
US9441543B2 (en) * | 2012-11-20 | 2016-09-13 | Niigata Power Systems Co., Ltd. | Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion |
FR3080437B1 (fr) | 2018-04-24 | 2020-04-17 | Safran Aircraft Engines | Systeme d'injection pour une chambre annulaire de combustion de turbomachine |
CN111006243B (zh) * | 2019-12-03 | 2021-03-30 | 哈尔滨工程大学 | 一种防回火燃油闪蒸旋流一体化喷嘴 |
US11378275B2 (en) * | 2019-12-06 | 2022-07-05 | Raytheon Technologies Corporation | High shear swirler with recessed fuel filmer for a gas turbine engine |
FR3106374B1 (fr) | 2020-01-21 | 2022-01-21 | Safran Aircraft Engines | Circuit d’alimentation en carburant pour une chambre de combustion d’une turbomachine |
FR3108162B1 (fr) | 2020-03-10 | 2023-01-13 | Safran Aircraft Engines | Système d’injection pour une chambre annulaire de combustion de turbomachine |
CN112983652B (zh) * | 2021-03-12 | 2022-09-02 | 广州大学城华电新能源有限公司 | 一种燃气轮机进气控制系统 |
US11802693B2 (en) | 2021-04-16 | 2023-10-31 | General Electric Company | Combustor swirl vane apparatus |
US11846423B2 (en) | 2021-04-16 | 2023-12-19 | General Electric Company | Mixer assembly for gas turbine engine combustor |
US11598526B2 (en) | 2021-04-16 | 2023-03-07 | General Electric Company | Combustor swirl vane apparatus |
US11428411B1 (en) * | 2021-05-18 | 2022-08-30 | General Electric Company | Swirler with rifled venturi for dynamics mitigation |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1586819A2 (de) * | 2004-04-16 | 2005-10-19 | General Electric Company | Verwirbelungsanordnung für Gasturbinenbrennkammer |
EP1790908A2 (de) * | 2005-11-28 | 2007-05-30 | General Electric Company | Reparaturverfahren für Brennkammerdom einer Gasturbine |
EP1857741A1 (de) * | 2006-05-19 | 2007-11-21 | Snecma | Brennkammer einer Gasturbine |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3121996A (en) * | 1961-10-02 | 1964-02-25 | Lucas Industries Ltd | Liquid fuel combustion apparatus |
US3570242A (en) | 1970-04-20 | 1971-03-16 | United Aircraft Corp | Fuel premixing for smokeless jet engine main burner |
US3811278A (en) | 1973-02-01 | 1974-05-21 | Gen Electric | Fuel injection apparatus |
FR2572463B1 (fr) * | 1984-10-30 | 1989-01-20 | Snecma | Systeme d'injection a geometrie variable. |
FR2585770B1 (fr) * | 1985-08-02 | 1989-07-13 | Snecma | Dispositif d'injection a bol elargi pour chambre de combustion de turbomachine |
FR2596102B1 (fr) * | 1986-03-20 | 1988-05-27 | Snecma | Dispositif d'injection a vrille axialo-centripete |
FR2602271B1 (fr) | 1986-07-30 | 1990-07-27 | Snecma | Dispositif d'injection, pour turbomachines, a vrille de turbulence a calage variable |
DE69421766T2 (de) | 1993-07-30 | 2000-06-21 | United Technologies Corp., Hartford | Wirbelmischvorrichtung für eine Brennkammer |
FR2717250B1 (fr) * | 1994-03-10 | 1996-04-12 | Snecma | Système d'injection à prémélange. |
RU2157954C2 (ru) * | 1995-09-05 | 2000-10-20 | Открытое акционерное общество "Самарский научно-технический комплекс им. Н.Д.Кузнецова" | Топливовоздушная горелка |
FR2752917B1 (fr) * | 1996-09-05 | 1998-10-02 | Snecma | Systeme d'injection a degre d'homogeneisation avancee |
US6412272B1 (en) * | 1998-12-29 | 2002-07-02 | United Technologies Corporation | Fuel nozzle guide for gas turbine engine and method of assembly/disassembly |
US6474071B1 (en) * | 2000-09-29 | 2002-11-05 | General Electric Company | Multiple injector combustor |
US7389643B2 (en) * | 2005-01-31 | 2008-06-24 | General Electric Company | Inboard radial dump venturi for combustion chamber of a gas turbine |
-
2007
- 2007-12-14 FR FR0708703A patent/FR2925146B1/fr active Active
-
2008
- 2008-11-13 EP EP08169015.8A patent/EP2071242B1/de active Active
- 2008-11-27 JP JP2008301971A patent/JP5260245B2/ja active Active
- 2008-12-10 CA CA2646959A patent/CA2646959C/fr active Active
- 2008-12-12 US US12/333,732 patent/US8312723B2/en active Active
- 2008-12-12 RU RU2008149163/06A patent/RU2478878C2/ru active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1586819A2 (de) * | 2004-04-16 | 2005-10-19 | General Electric Company | Verwirbelungsanordnung für Gasturbinenbrennkammer |
EP1790908A2 (de) * | 2005-11-28 | 2007-05-30 | General Electric Company | Reparaturverfahren für Brennkammerdom einer Gasturbine |
EP1857741A1 (de) * | 2006-05-19 | 2007-11-21 | Snecma | Brennkammer einer Gasturbine |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3033030A1 (fr) * | 2015-02-20 | 2016-08-26 | Snecma | Systeme d'injection d'un melange air-carburant dans une chambre de combustion de turbomachine d'aeronef, comprenant un venturi perfore de trous d'injection d'air |
Also Published As
Publication number | Publication date |
---|---|
FR2925146B1 (fr) | 2009-12-25 |
US20090151357A1 (en) | 2009-06-18 |
JP2009145039A (ja) | 2009-07-02 |
RU2478878C2 (ru) | 2013-04-10 |
CA2646959C (fr) | 2016-10-18 |
US8312723B2 (en) | 2012-11-20 |
EP2071242B1 (de) | 2017-08-02 |
FR2925146A1 (fr) | 2009-06-19 |
RU2008149163A (ru) | 2010-06-20 |
CA2646959A1 (fr) | 2009-06-14 |
JP5260245B2 (ja) | 2013-08-14 |
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