EP2085695A1 - Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible - Google Patents

Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible Download PDF

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Publication number
EP2085695A1
EP2085695A1 EP08001641A EP08001641A EP2085695A1 EP 2085695 A1 EP2085695 A1 EP 2085695A1 EP 08001641 A EP08001641 A EP 08001641A EP 08001641 A EP08001641 A EP 08001641A EP 2085695 A1 EP2085695 A1 EP 2085695A1
Authority
EP
European Patent Office
Prior art keywords
sleeve
pin
fuel nozzle
swirl
fuel
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.)
Withdrawn
Application number
EP08001641A
Other languages
German (de)
English (en)
Inventor
Tobias Krieger
Elmar Pfeiffer
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP08001641A priority Critical patent/EP2085695A1/fr
Priority to EP08871983A priority patent/EP2235441A2/fr
Priority to JP2010543398A priority patent/JP2011511243A/ja
Priority to US12/864,928 priority patent/US8636504B2/en
Priority to PCT/EP2008/065135 priority patent/WO2009095100A2/fr
Publication of EP2085695A1 publication Critical patent/EP2085695A1/fr
Priority to JP2012145537A priority patent/JP5312645B2/ja
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49428—Gas and water specific plumbing component making
    • Y10T29/49432—Nozzle making
    • Y10T29/49433—Sprayer

Definitions

  • the present invention relates to a fuel nozzle having a swirl passage and a method of manufacturing a fuel nozzle.
  • the invention further relates to a burner and a gas turbine.
  • a first object of the present invention to provide an alternative, advantageous method for producing a fuel nozzle.
  • a second object of the present invention is to provide an alternative, advantageous fuel nozzle.
  • a third object of the present invention is the disclosure of an advantageous burner. It is a fourth object of the invention to provide an advantageous gas turbine.
  • the first object is achieved by a method for producing a fuel nozzle according to claim 1.
  • the second task is achieved by a fuel nozzle according to claim 6.
  • the third object is achieved by a burner according to claim 12.
  • the fourth object is achieved by a gas turbine according to claim 15.
  • At least one swirl duct is introduced into an outer jacket surface of a pin and / or into an inner surface of a sleeve. Subsequently, the pin is mounted in the sleeve so that the outer surface of the pin is connected to the inner surface of the sleeve, without thereby closing the channel final.
  • any swirling contours can be produced inexpensively and flexibly.
  • the swirl channel may be milled, rotated, thrust, eroded, sintered, or profile extruded into the outer surface of the pin and / or into the inner surface of the sleeve.
  • the pin and / or sleeve may also be cast, with the swirl channel defined by the mold.
  • the pin can be soldered or hammered into the sleeve.
  • the swirling contour or the swirl channel can be shaped and configured as desired.
  • the swirl duct can be introduced spirally into the outer jacket surface of the pin and / or into the inner surface of the sleeve. It is also advantageous if at least two swirl channels, in particular three swirl channels, are introduced.
  • a swirl channel can also be introduced into the outer jacket surface of the pin and another swirl channel can be introduced into the inner surface of the sleeve. These two swirl channels can in particular be arranged offset from each other.
  • Both the outer circumferential surface of the pin and the inner surface of the sleeve can be basically formed arbitrarily. They may, for example, be cylindrical, eccentric or conical. By changing these parameters and by the number of swirl channels, the exit of the fuel from the nozzle can be suitably adjusted.
  • the fuel nozzle according to the invention comprises a pin with an outer jacket surface and a sleeve with an inner surface.
  • the pin is disposed within the sleeve.
  • the outer jacket surface of the pin and / or the inner surface of the sleeve comprises at least one swirl channel.
  • the fuel nozzle according to the invention makes it possible to put the fuel within the nozzle in a swirling movement with a structurally simple design. This allows a better mixing of the fuel with the air.
  • the swirl channel can be designed, for example, spiral.
  • the outer mantle surface of the pin and / or the inner surface of the sleeve may / may in particular be cylindrical, conical or eccentric. This allows a high flexibility in the choice of the twisting geometry.
  • the fuel nozzle may further comprise at least two swirl channels, for example three swirl channels.
  • the pin may comprise a cover surface
  • the sleeve comprise an outlet opening and the pin may be arranged in the sleeve, that the cover surface is set back relative to the outlet opening to the interior of the sleeve.
  • a swirl chamber is formed within the sleeve between the top surface and the outlet opening. Within the swirl chamber, the fuel can mix well with the air due to the swirling motion of the fuel.
  • the cover surface recessed with respect to the outlet opening it is also possible to form a swirl chamber, that the top surface and the outlet opening lie in a plane and are thus aligned, in which case the fuel nozzle is set back in relation to the outer jacket surface of the attachment.
  • the fuel nozzle with lying in a plane deck surface and outlet opening is sunk so deep in the essay that the outlet opening is located closer to the center axis of the burner than the otherwise existing there lateral surface of the essay.
  • the swirl chamber is radially limited - with respect to the center axis of the fuel nozzle - by the essay. The swirl chamber is then outside, ie downstream of the sleeve.
  • both the top surface of the pin relative to the exit surface of the sleeve and the exit surface of the sleeve is set back relative to the lateral surface of the attachment. This results in a stepped swirl chamber.
  • the surface of the outlet opening is smaller than the top surface of the pin.
  • this leads to a swirl chamber in the interior of the sleeve, the flow cross-sectional area of which decreases in the direction of flow - ie from the top surface to the outlet opening - along the center axis of the fuel nozzle.
  • the manner of tapering or reducing the cross-sectional area of the swirl chamber can be curved linear, convex-concave or otherwise arbitrary.
  • the taper is symmetrical to the central axis of the fuel nozzle.
  • the fuel nozzle according to the invention can in principle be used for any fuels. It can be configured in particular as an oil nozzle.
  • the burner according to the invention comprises a fuel nozzle according to the invention with the features described above.
  • the burner according to the invention has the same advantages as the fuel nozzle according to the invention.
  • the burner according to the invention can also comprise an attachment, wherein the fuel nozzle is arranged in the attachment.
  • the essay can for example be designed pointed.
  • the attachment may comprise a central axis.
  • the fuel nozzle may also include a central axis and be arranged in the attachment so that the center axis of the fuel nozzle has an angle between 45 ° and 90 ° to the central axis of the attachment.
  • the gas turbine according to the invention comprises a burner according to the invention and has the same advantages as the burner according to the invention described above.
  • a gas turbine typically includes a compressor, one or more burners, a combustor, and a turbine. During operation of the gas turbine air is compressed by the compressor. The compressed air provided at the turbine end of the compressor is fed to the burners where it is mixed with a fuel. The mixture is then burned to form a working medium in the combustion chamber. From there, the working medium flows to the turbine and drives it.
  • the fuel nozzle according to the invention can be produced quickly and inexpensively, for example by means of the method according to the invention. It is characterized by a high degree of flexibility in the choice of the twisting geometry and can be used flexibly.
  • FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • FIG. 2 schematically shows a section through a burner 107 according to the invention in a partially perspective view.
  • the burner 107 can be used on the one hand in conjunction with the annular combustion chamber 106.
  • the burner 107 is used in conjunction with a so-called tube combustion chamber.
  • the gas turbine 100 instead of the annular combustion chamber 106, the gas turbine 100 has a plurality of annularly arranged tube combustion chambers whose downstream openings open into the annular hot gas channel 111 on the turbine inlet side.
  • a plurality, for example six or eight, burner 107 is arranged at the opposite end of the downstream opening of the tube combustion chamber usually annularly around a pilot burner.
  • the burner 107 comprises a cylindrical housing 12.
  • a lance with a fuel channel 16 is arranged along the central axis 27 of the burner 107.
  • the latter On the side of the lance leading to the combustion chamber 110, the latter comprises a pointed attachment 13, which is arranged concentrically to the central axis 27.
  • Fuel nozzles 1 are arranged, which communicate with the fuel channel 16.
  • swirl blades 17 are arranged around the lance.
  • the swirl blades 17 are arranged along the circumference of the lance in the housing 12.
  • a compressor air flow 15 is passed into the combustion chamber 110 leading to the part of the burner 107.
  • the air is displaced by the swirl blades 17 in a swirling motion.
  • Fuel for example oil, is injected through the fuel nozzles 1 into the resulting air stream.
  • the resulting fuel-air mixture is then passed on to the combustion chamber 110.
  • the FIG. 3 schematically shows a section through the attachment 13 in a perspective view.
  • the central axis of the attachment 13 is indicated by the reference numeral 18.
  • the attachment 13 is conical to the combustion chamber 110, tapered designed. It comprises a plurality, in the present embodiment four, fuel nozzles 1.
  • the fuel nozzles 1 are arranged on the outer circumference of the attachment 13 in corresponding recesses.
  • the center axes of the fuel nozzles 1 are indicated by the reference numeral 19.
  • the central axes 19 of the fuel nozzles 1 have to the central axis 18 of the attachment 13 at an angle 20 between 45 ° and 90 °.
  • the fuel enters the attachment 13 along the direction of flow indicated by the reference numeral 26 through the fuel channel 16.
  • the fuel is then injected through the fuel nozzles 1 in the direction 25 in the coming of the swirl blades 17 air flow.
  • the fuel nozzle 1 comprises a sleeve 2 and a pin 3 arranged in the sleeve 2
  • FIG. 4 schematically shows a section through the sleeve 2 in a perspective view.
  • the sleeve 2 has the shape of a hollow cylinder in the present embodiment.
  • the inner surface the sleeve 2 is indicated by the reference numeral 6.
  • the FIG. 5 shows a pin 3 in a perspective view.
  • the pin 3 has the shape of a cylinder in the present embodiment.
  • the outer shell surface of the cylinder is identified by the reference numeral 5.
  • the top surface of the pin 3 is identified by the reference numeral 7.
  • a swirl duct 4 extends in the form of a depression. The swirl duct 4 spirals around the central axis 28 of the pin 3 on the outer jacket surface 5.
  • FIG. 6 schematically shows a section through a fuel nozzle 1 according to the invention in a perspective view.
  • the fuel nozzle 1 according to the invention comprises in the FIG. 4 shown sleeve 2 and in the FIG. 5
  • the pin 3 is arranged in the sleeve 2, that the inner surface 6 of the sleeve 2 is connected to the outer circumferential surface 5 of the pin 3 conclusive.
  • the connection can basically be positive or non-positive.
  • the pin 3 can be soldered or hammered, for example, in the sleeve 2.
  • the swirl channel 4 is covered or bounded by the inner surface 6 of the sleeve 2 radially with respect to the central axis 28 of the pin.
  • the sleeve 2 has an outlet opening 8 in the flow direction 25 of the fuel nozzle 1 leaving fuel.
  • the pin 3 is arranged in the sleeve 2, that the top surface 7 of the pin 3 is set back against the outlet opening 8 of the sleeve 2.
  • a swirl chamber 9 is formed.
  • a mixing of the fuel, in the present embodiment of the oil, takes place with air. It is also possible that the top surface 7 is aligned with the outlet opening 8.
  • FIG. 7 schematically shows a pin 29 in a perspective view.
  • pin 3 includes three spirally around the central axis 28 of the pin 29 along the outer surface 5 arranged swirl channels 4.
  • the swirl channels 4 are arranged offset from each other in the circumferential direction.
  • the respectively adjacent swirl channels 4 can be arranged offset to one another, for example, along the circumference of the pin 29 at an angle of 120 °.
  • the pin 3, 29 may also comprise any other number of swirl channels 4.
  • FIGS. 8 to 10 explained in more detail.
  • Elements corresponding to elements of the first embodiment are given the same reference numerals and will not be described again in detail.
  • FIG. 8 schematically shows a section through a sleeve 22 in a perspective view.
  • the sleeve 22 is distinguished in contrast to that in the FIG. 4 shown sleeve 2 characterized in that along its inner surface 6 a swirl channel 24 is arranged.
  • the swirl channel 24 spirals with respect to the central axis of the sleeve 21 along its inner surface 6.
  • FIG. 9 schematically shows a pin 23 in a perspective view.
  • the pin 23 used in the present embodiment has the shape of a cylinder and has, in contrast to that in the FIG. 5 shown pin 3 no swirl channel.
  • the pin 23 comprises an outer jacket surface 5 and a top surface 7.
  • FIG. 10 schematically shows a section through a fuel nozzle 21 according to the invention in a perspective view.
  • the fuel nozzle 21 includes those in the FIG. 8 shown Sleeve 22 and in the FIG. 9
  • the pin 23 is arranged in the sleeve 22 so that the outer jacket surface 5 of the pin 23 with the inner surface 6 of the sleeve 22 is in a positive connection.
  • the connection can basically be positive or non-positive. Due to the arrangement of the pin 23 in the sleeve 22 of the swirl passage 24 is radially covered or limited to the central axis 19 out.
  • the sleeve 22 used may also comprise a plurality of mutually offset swirl channels 24.
  • the adjacent swirl channels 4 may, for example, be arranged offset from each other along the circumference of the pin 23 by an angle of 120 °.
  • the pin 23 is further arranged in the sleeve 22, that the top surface 7 of the pin 23 is set back against the outlet opening 8 of the sleeve 22. It thus arises between the top surface 7 of the pin 23 and the outlet opening 8 a swirl chamber 9, is mixed in the fuel with air.
  • FIG. 11 shows a fuel nozzle 31 according to the invention, which is a combination of the sleeve 22 of the second embodiment with the pin 3, 29 of the first embodiment.
  • the fuel nozzle 31 includes a sleeve 32 having a swirl passage along its inner surface 6.
  • the swirl channel 24 has the same characteristics as those associated with the FIGS. 8 and 10 described swirl channel 24th
  • a pin 33 is arranged in the sleeve 32.
  • the pin 33 has the same characteristics as that associated with the FIG. 5 described pin 3 or as related to the FIG. 7
  • the pin 33 comprises a swirl channel 4.
  • the pin 33 is arranged in the sleeve 32, that the swirl channel 4 is covered by the inner surface 6 of the sleeve 32 and that the swirl channel 24 through the outer jacket surface 5 of the pin 33rd is covered. This creates two swirl channels in the fuel nozzle 31.
  • a swirl chamber Inside the sleeve 32 is located between the top surface 7 of the pin 33 and the outlet opening 8 of the sleeve 32, a swirl chamber. 9
  • FIG. 12 schematically shows a section through a fuel nozzle according to the invention 41.
  • the fuel nozzle 41 includes a sleeve 42 and a pin 43.
  • the pin 43 is disposed inside the sleeve 42.
  • the outer jacket surface 45 of the pin 43 and the inner surface 46 of the sleeve 42 have the shape of the lateral surface of a truncated cone. This means that the radius of the pin 43 increases conically with respect to the central axis 28 in the direction of flow of the fuel.
  • the inner diameter of the sleeve 42 increases conically in the direction of flow 25 of the fuel.
  • the pin 43 has at least one spiral channel 4 extending spirally along its outer jacket surface 45.
  • the top surface 7 of the pin 43 is arranged in the interior of the sleeve 42 with respect to the outlet opening 8 set back.
  • a swirl chamber 9 is formed in the sleeve 42, in which the fuel is mixed with air.
  • Alternatively to the one in the FIG. 12 shown embodiment can also only the sleeve 42 or both the sleeve 42 and the pin 43 include at least one swirl duct.
  • the outlet of the fuel can be controlled by changing, for example, the diameter, the eccentricity, the conical shape or by a multi-stage ejection through a plurality of swirl channels.
  • the fuel may in particular be oil.
  • the pin can be soldered or hammered into the sleeve, for example.
  • the respective swirl channels can be produced by means of various manufacturing methods. They can be introduced, for example, by milling, turning, pushing, eroding, sintering or extruded profile into the respective surface of the pin and / or the nozzle. Furthermore, the respective surface of the pin and / or the nozzle can be produced by casting.
  • top surface 7 is located with the outlet opening 8 in a plane.
  • To form a swirl chamber is then only necessary that the fuel nozzle 1, 21, 31, 41 is set back relative to the lateral surface of the attachment 13.
EP08001641A 2008-01-29 2008-01-29 Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible Withdrawn EP2085695A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP08001641A EP2085695A1 (fr) 2008-01-29 2008-01-29 Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible
EP08871983A EP2235441A2 (fr) 2008-01-29 2008-11-07 Buse d'injection de carburant munie d'un canal à flux tourbillonnaire et procédé de fabrication d'une buse d'injection de carburant
JP2010543398A JP2011511243A (ja) 2008-01-29 2008-11-07 旋回流路を有する燃料ノズル及び燃料ノズルの製造方法
US12/864,928 US8636504B2 (en) 2008-01-29 2008-11-07 Fuel nozzle having swirl duct and method for producing a fuel nozzle
PCT/EP2008/065135 WO2009095100A2 (fr) 2008-01-29 2008-11-07 Buse d'injection de carburant munie d'un canal à flux tourbillonnaire et procédé de fabrication d'une buse d'injection de carburant
JP2012145537A JP5312645B2 (ja) 2008-01-29 2012-06-28 旋回流路を有する燃料ノズルを備えたバーナ及び燃料ノズルの製造方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08001641A EP2085695A1 (fr) 2008-01-29 2008-01-29 Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible

Publications (1)

Publication Number Publication Date
EP2085695A1 true EP2085695A1 (fr) 2009-08-05

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EP08001641A Withdrawn EP2085695A1 (fr) 2008-01-29 2008-01-29 Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible
EP08871983A Withdrawn EP2235441A2 (fr) 2008-01-29 2008-11-07 Buse d'injection de carburant munie d'un canal à flux tourbillonnaire et procédé de fabrication d'une buse d'injection de carburant

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08871983A Withdrawn EP2235441A2 (fr) 2008-01-29 2008-11-07 Buse d'injection de carburant munie d'un canal à flux tourbillonnaire et procédé de fabrication d'une buse d'injection de carburant

Country Status (4)

Country Link
US (1) US8636504B2 (fr)
EP (2) EP2085695A1 (fr)
JP (2) JP2011511243A (fr)
WO (1) WO2009095100A2 (fr)

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JP2013529771A (ja) * 2010-07-01 2013-07-22 シーメンス アクチエンゲゼルシヤフト バーナー装置
EP2754964A1 (fr) * 2013-01-15 2014-07-16 Siemens Aktiengesellschaft Buse à combustible et procédé de fabrication d'une buse à combustible
EP2927598A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Procédé destiné à remplacer une coupelle à aubes rotatives
EP2619507B1 (fr) * 2010-09-21 2019-11-06 Micro Turbine Technology BV Chambre de combustion dotée d'un unique brûleur à mélange air/carburant limité et micro-turbine à gaz récupéré

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US9366439B2 (en) * 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
EP2905539A1 (fr) * 2014-02-07 2015-08-12 Siemens Aktiengesellschaft Veilleuse avec aubes axiales pour turbine à gaz
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WO2016085494A1 (fr) * 2014-11-26 2016-06-02 Siemens Aktiengesellschaft Lance à carburant ayant un moyen pour interagir avec un flux d'air et améliorer la rupture d'un jet de carburant liquide éjecté
KR101657535B1 (ko) * 2015-05-21 2016-09-19 두산중공업 주식회사 버닝 저감 연료공급노즐.
KR102091043B1 (ko) * 2018-05-30 2020-03-20 두산중공업 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
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EP2169313A2 (fr) * 2008-09-30 2010-03-31 Alstom Technology Ltd Lance à combustible de turbine à gaz
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EP2588805B1 (fr) * 2010-07-01 2016-04-20 Siemens Aktiengesellschaft Brûleur
EP2619507B1 (fr) * 2010-09-21 2019-11-06 Micro Turbine Technology BV Chambre de combustion dotée d'un unique brûleur à mélange air/carburant limité et micro-turbine à gaz récupéré
EP2754964A1 (fr) * 2013-01-15 2014-07-16 Siemens Aktiengesellschaft Buse à combustible et procédé de fabrication d'une buse à combustible
EP2927598A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Procédé destiné à remplacer une coupelle à aubes rotatives
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WO2009095100A3 (fr) 2010-05-27
JP2011511243A (ja) 2011-04-07
JP2012189318A (ja) 2012-10-04
EP2235441A2 (fr) 2010-10-06
JP5312645B2 (ja) 2013-10-09
WO2009095100A2 (fr) 2009-08-06
US20100330521A1 (en) 2010-12-30
US8636504B2 (en) 2014-01-28

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