EP2182170A1 - Turbine à gaz avec plaques d'étanchéité sur le disque de turbine - Google Patents

Turbine à gaz avec plaques d'étanchéité sur le disque de turbine Download PDF

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Publication number
EP2182170A1
EP2182170A1 EP08018988A EP08018988A EP2182170A1 EP 2182170 A1 EP2182170 A1 EP 2182170A1 EP 08018988 A EP08018988 A EP 08018988A EP 08018988 A EP08018988 A EP 08018988A EP 2182170 A1 EP2182170 A1 EP 2182170A1
Authority
EP
European Patent Office
Prior art keywords
turbine
gas turbine
sealing
sealing plate
sealing plates
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Withdrawn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
EP08018988A
Other languages
German (de)
English (en)
Inventor
Björn Bilstein
Peter Schröder
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 EP08018988A priority Critical patent/EP2182170A1/fr
Priority to PCT/EP2009/061462 priority patent/WO2010049196A1/fr
Priority to RU2011121660/06A priority patent/RU2515697C2/ru
Priority to JP2011533640A priority patent/JP5108152B2/ja
Priority to CN200980143237.2A priority patent/CN102203389B/zh
Priority to EP09782613.5A priority patent/EP2344723B1/fr
Priority to US13/126,782 priority patent/US8573943B2/en
Publication of EP2182170A1 publication Critical patent/EP2182170A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the invention relates to a gas turbine having a number of guide vanes each joined to a guide blade carrier by means of a guide vane carrier and having a number of rotor blades, each arranged on a turbine disk, the respective turbine disk having a number of Has sealing plates.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or blade rows, are arranged thereon.
  • a turbine disk is usually provided for each turbine stage, to which the blades are fastened by means of their blade root.
  • For guiding the flow of the working medium in the turbine unit also commonly associated between adjacent blade rows with the turbine housing and combined into rows of guide vanes are arranged.
  • the combustor of the gas turbine may be embodied as a so-called annular combustor having a plurality of burners circumferentially disposed about the turbine shaft in a common, surrounded by a high temperature resistant surrounding wall combustion chamber space opens.
  • the combustion chamber is designed in its entirety as an annular structure.
  • a single combustion chamber can also be provided a plurality of combustion chambers.
  • first row of guide vanes of a turbine unit which, together with the blade row immediately downstream in the flow direction of the working medium, forms a first turbine stage of the turbine unit, which is usually followed by further turbine stages.
  • sealing plates are usually provided on the turbine disks, which are mounted in a circular manner on the turbine disk on the side faces normal to the turbine axis.
  • a sealing plate is usually provided per turbine blade on each side of the turbine disk.
  • the sealing plates fulfill even more functions. On the one hand they form the axial fixation of the turbine blades by appropriate fasteners, on the other hand they not only seal the turbine disk against penetration of hot gas from the outside, but also avoid leakage of guided inside the turbine disk cooling air, which usually forwarded to the cooling of the turbine blades in selbige becomes.
  • a gas turbine in such a configuration is for example from the EP 1 944 471 A1 known.
  • the invention is therefore based on the object to provide a gas turbine, which allows a simplified construction while maintaining the greatest possible operational safety and the greatest possible efficiency.
  • the invention is based on the consideration that a simplified construction of the gas turbine, in particular in the area of the turbine disks, would be possible if the hitherto customary construction could be simplified with scale-like sealing plates.
  • the large number of sealing plates is complex, wherein a sealing plate is provided for each blade on each side surface. Therefore, the number of sealing plates should be reduced, that is, the number of sealing plates per side surface should be less than the number of blades.
  • the sealing plates are substantially circular section.
  • the sealing plates are adapted to the shape of the turbine disk and it is thus ensured a reliable seal.
  • the larger, circular segment-shaped sealing plates then cover namely the same area as the previously scaly superimposed individual sealing plates.
  • sealing plates are provided per side surface.
  • the simplest embodiment of the sealing plates is namely possible with a maximum reduction of the number of sealing plates, wherein a single sealing plate, for example in the form of a circular ring due to the tilting required during assembly is not possible. Therefore, the simplest possible construction is a design with two identically designed sealing plates. This embodiment is also particularly advantageous for stationary gas turbines, since their assembly of housing and rotor takes place radially and not axially as in aircraft gas turbines.
  • a slot is introduced into each facing surfaces of two sealing plates, wherein for sealing the gap between the surfaces of the respective opposite slots connecting plate is inserted.
  • the respective sealing plate has a substantially azimuthally and axially extending sealing wing.
  • a sealing wing which should be designed to be continuous in a correspondingly by the smaller number larger sealing plate in the azimuthal direction, a sealing of the part of the turbine disk facing the turbine shaft against the penetration of hot gas from the interior of the turbine is achieved.
  • the sealing wing should extend in the axial direction to the respective adjacent vanes, in order to achieve a particularly good seal.
  • the respective sealing plate advantageously on the turbine axis side facing an azimuthally extending, spaced from the inner edge of the respective sealing plate edge, wherein azimuthally displaceable between the edge and a likewise azimuthally extending turbine disk groove on the turbine disk for sealing a plurality of abutment pieces is arranged.
  • closure pieces for example in the form of beams, can be introduced into the remaining space between the sealing plate and the turbine disk.
  • These are fixed in radial and axial direction by edge, sealing plate and turbine disk groove. In the azimuthal direction, however, they remain displaceable and can thus be arranged adjacent to one another in order to achieve a complete seal by forming a ring of closure pieces.
  • the respective sealing plate advantageously comprises at least one recess extending substantially azimuthally on the side facing the turbine axis.
  • This recess is geometrically designed so that a closure piece can be inserted into the turbine disk groove, i. she is just so big that a closure piece can be lowered in the turbine disk groove already mounted sealing plate.
  • this closure piece can then be moved azimuthally into its end position, where it is fixed axially and radially.
  • Other fasteners can then be inserted over the same recess and also moved until all fasteners are mounted.
  • the respective closure piece has a bore and / or the respective sealing plate has a number of notches for receiving a securing bolt.
  • the respective sealing plate is made by turning.
  • the smaller number of sealing plates makes it possible to manufacture the sealing plates as a circular ring in the turning process and then to divide. As a result, a simplified and more cost-effective production of the sealing plates is possible.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages associated with the invention are in particular that by reducing the number of sealing plates per side surface of the turbine disk of a gas turbine a significantly simplified and cheaper construction of Gas turbine is possible.
  • the design of the entire blade row is thereby significantly simplified and is less expensive to manufacture, since the sealing plates can be manufactured in the turning process.
  • the sealing plates have comparatively few leakage surfaces. This can be sealed much denser to reduce the loss of cooling air.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine unit 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each blade 12 is fixed in a similar manner via a platform 19 on the turbine shaft 8.
  • a guide ring 21 is arranged on a guide blade carrier 16 of the turbine unit 6.
  • the outer surface of each guide ring 21 is also exposed to the hot, the turbine unit 6 flowing through the working medium M and spaced in the radial direction from the outer end of the opposite blades 12 through a gap.
  • the guide rings 21 arranged between adjacent rows of guide blades serve in particular as cover elements which protect the inner housing 16 in the guide blade carrier or other housing installation parts from thermal overstress by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • FIG. 2 1 shows in each case a section through a sealing plate 30, a securing bolt 32, a closure piece 34, a securing plate 36 and through the outer circumference of a turbine disk 38, attached to the turbine shaft 8, of a rotor blade stage of the turbine unit 6.
  • the turbine disk 38 includes a blade retention groove 40 in which the blade 12 (not shown) is disposed. Through the cooling air hole 42 1 cooling air is supplied during operation of the gas turbine, which cools the turbine disk 36 and is also forwarded to the blade 12, not shown.
  • the sealing plate 30 is set on the side surface of the turbine disk 38.
  • circulating cams 44, 46 circulating in the turbine disk 38 serve as spacers.
  • the sealing plate 30 is tilted by an applied thereto, extending in the azimuthal direction edge 47 by means of the closure piece 34 on the turbine disk 38 and fixed radially and azimuthally with the locking pin 32 in a bore 48 of the turbine disk 38.
  • the locking plate 36 prevents axial pushing out of the locking bolt 32nd
  • the seal plate 30 includes an attached, substantially in the axial and azimuthal direction extending sealing vanes 50, which seals the gap between the turbine disk 38 and adjacent vanes 14 against ingress of hot working fluid M from the turbine. Furthermore, the sealing plate 30 also provides for axial fixation of the blade 12 in the Schaufelfußnut 40 and secures them against displacement.
  • FIG. 3 shows the sealing plate 30 in the top view. Notches 52 are introduced into the sealing plate 30 at a uniform spacing on the side facing the turbine shaft, which serve to receive the securing bolts 32. As a result, the sealing plate 30, which is larger due to the overall smaller number of sealing plates, is fixed along the entire circumference. Furthermore, the edge 47 can be seen for fixing the closure pieces 34.
  • the sealing plate 30 is in FIG. 4 shown in the inclined profile.
  • a slot 54 is introduced, in which a not shown corrugated sheet is introduced, so that the parting line lying between the sealing plates 30 is closed and thus sealed.
  • FIG. 5 again shows the sealing plate 30 in the plan.
  • the notch 52 respectively introduced recess 56 is shown here, which interrupts the edge 47. It is adapted in its geometry to the size of the closure pieces 34, so that it is suitable for insertion of the closure piece 34 shown in more detail in the following figures.
  • closure pieces 34 can be lowered through the recess 56 and subsequently pushed along the edge 47 into its end position. This is a fixation of the already mounted sealing plate 30 on the turbine disk 38 and a good seal of the remaining gap achieved.
  • FIG. 6 shows the closure piece 34 in section.
  • a bore 58 is introduced, in which the securing bolt 32 is introduced.
  • a recess 60 is shown, which serves to receive the locking plate 36, which prevents axial displacement of the securing bolt 32.
  • the FIG. 8 shows the closure piece again in the supervision.
  • the adaptation to the shape of the in the FIG. 5 Recognize recess 56 shown.
  • FIG. 9 to FIG. 14 show the assembly process of the sealing plate 30 on the turbine disk 36.
  • the sealing plate 30 is first lowered radially into the turbine disk groove 62 ( FIG. 10 . FIG. 11 ), then moved axially towards the blade 12 ( FIG. 12 ) and finally lifted radially ( FIG. 13 ).
  • the shoulder 64 at the inner radius of the sealing plate 30 thus abuts against the cam 46 of the turbine disk 38.
  • the closure piece 34 is inserted radially over the recess 56 on the sealing plate 30 in the groove 62 and circumferentially along the edge 47 shifted so far that its bore 58 is aligned with a bore 48 in the turbine disk 38 and a notch 52 in the sealing plate 52. There, the closure piece 34 is fixed with a locking bolt 32.
  • the other closure pieces 34 are used in the same way.
  • the sealing plate 30 is secured radially and axially.
  • the closure pieces 47 are in the assembled state to each other, so that a complete seal of the gap between the sealing plate 30 and turbine disk groove 62 is ensured.
  • the locking plate 36 is inserted radially, which also has a bore in the center. In this and the holes 48, 58 of the Locking bolt 32 introduced. This secures radially the locking plate 36 and in the circumferential direction, the closure piece 34 and the sealing plate 30. against axial pushing out of the locking bolt 32, the end of the locking plate 36 is bent radially downwards. The final assembly is in FIG. 14 shown.
  • the illustrated sealing plate 30 is substantially semicircular.
  • the sealing plate 30 can be made in the turning process as a circular ring and then shared.
  • a particularly simple construction of the gas turbine 1 is possible.
  • a much better seal against cooling air loss is possible due to the smaller number of leakage surfaces compared to the previous scale-like arrangement.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP08018988A 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine Withdrawn EP2182170A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP08018988A EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
PCT/EP2009/061462 WO2010049196A1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
RU2011121660/06A RU2515697C2 (ru) 2008-10-30 2009-09-04 Газовая турбина с уплотнительными пластинами на турбинном диске
JP2011533640A JP5108152B2 (ja) 2008-10-30 2009-09-04 タービンディスク上にシールプレートを備えたガスタービン
CN200980143237.2A CN102203389B (zh) 2008-10-30 2009-09-04 具有设置在涡轮叶轮盘上的密封板的燃气涡轮机
EP09782613.5A EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
US13/126,782 US8573943B2 (en) 2008-10-30 2009-09-04 Gas turbine having sealing plates on the turbine disc

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08018988A EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Publications (1)

Publication Number Publication Date
EP2182170A1 true EP2182170A1 (fr) 2010-05-05

Family

ID=40506496

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08018988A Withdrawn EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
EP09782613.5A Not-in-force EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09782613.5A Not-in-force EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Country Status (6)

Country Link
US (1) US8573943B2 (fr)
EP (2) EP2182170A1 (fr)
JP (1) JP5108152B2 (fr)
CN (1) CN102203389B (fr)
RU (1) RU2515697C2 (fr)
WO (1) WO2010049196A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3002411A1 (fr) * 2014-09-26 2016-04-06 Rolls-Royce plc Agencement de rotor à aubes avec plaques de verrouillage avec pieds déformables
EP3536907A4 (fr) * 2016-12-13 2020-01-08 Mitsubishi Hitachi Power Systems, Ltd. Procédé de désassemblage/assemblage de turbine à gaz, rotor de turbine à gaz et turbine à gaz
US11111799B2 (en) 2016-12-13 2021-09-07 Mitsubishi Power, Ltd. Method for disassembling/assembling gas turbine, seal plate assembly, and gas turbine rotor

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2973829B1 (fr) * 2011-04-05 2013-05-24 Snecma Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant
CN104285040B (zh) * 2012-05-08 2016-09-07 西门子公司 用于燃气轮机的轴向的转子部段和涡轮机转子叶片
EP3521561A1 (fr) * 2018-02-02 2019-08-07 Siemens Aktiengesellschaft Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP3564489A1 (fr) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges
CN110578557A (zh) * 2019-10-29 2019-12-17 北京动力机械研究所 一种涡轮叶片锁紧装置及其装配方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
EP1284339A1 (fr) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz
US20070237645A1 (en) * 2006-04-10 2007-10-11 Snecma Retaining device for axially retaining a rotor disk flange in a turbomachine
EP1944471A1 (fr) 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
US20080181767A1 (en) * 2007-01-30 2008-07-31 Siemens Power Generation, Inc. Turbine seal plate locking system

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB928349A (en) 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
RU1077380C (ru) * 1982-03-22 1995-06-19 Запорожское машиностроительное конструкторское бюро "Прогресс" Рабочее колесо турбомашины
FR2857691B1 (fr) * 2003-07-17 2006-02-03 Snecma Moteurs Retention de flasque de rotor
GB0423363D0 (en) 2004-10-21 2004-11-24 Rolls Royce Plc Rotor assembly retaining apparatus

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
EP1284339A1 (fr) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz
US20070237645A1 (en) * 2006-04-10 2007-10-11 Snecma Retaining device for axially retaining a rotor disk flange in a turbomachine
EP1944471A1 (fr) 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
US20080181767A1 (en) * 2007-01-30 2008-07-31 Siemens Power Generation, Inc. Turbine seal plate locking system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3002411A1 (fr) * 2014-09-26 2016-04-06 Rolls-Royce plc Agencement de rotor à aubes avec plaques de verrouillage avec pieds déformables
US10125621B2 (en) 2014-09-26 2018-11-13 Rolls-Royce Plc Bladed rotor arrangement and a lock plate for a bladed rotor arrangement
EP3536907A4 (fr) * 2016-12-13 2020-01-08 Mitsubishi Hitachi Power Systems, Ltd. Procédé de désassemblage/assemblage de turbine à gaz, rotor de turbine à gaz et turbine à gaz
US11111799B2 (en) 2016-12-13 2021-09-07 Mitsubishi Power, Ltd. Method for disassembling/assembling gas turbine, seal plate assembly, and gas turbine rotor
US11339672B2 (en) 2016-12-13 2022-05-24 Mitsubishi Power, Ltd. Method for disassembling/assembling gas turbine, gas turbine rotor, and gas turbine

Also Published As

Publication number Publication date
RU2515697C2 (ru) 2014-05-20
WO2010049196A1 (fr) 2010-05-06
EP2344723A1 (fr) 2011-07-20
US20110206524A1 (en) 2011-08-25
CN102203389A (zh) 2011-09-28
US8573943B2 (en) 2013-11-05
JP5108152B2 (ja) 2012-12-26
CN102203389B (zh) 2014-03-05
RU2011121660A (ru) 2012-12-10
JP2012506968A (ja) 2012-03-22
EP2344723B1 (fr) 2014-05-07

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