EP2576991B1 - Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse - Google Patents

Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse Download PDF

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Publication number
EP2576991B1
EP2576991B1 EP11728341.6A EP11728341A EP2576991B1 EP 2576991 B1 EP2576991 B1 EP 2576991B1 EP 11728341 A EP11728341 A EP 11728341A EP 2576991 B1 EP2576991 B1 EP 2576991B1
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EP
European Patent Office
Prior art keywords
casing
rotation
turbo machine
distributor
proofing
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Application number
EP11728341.6A
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English (en)
French (fr)
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EP2576991A1 (de
Inventor
Thierry Michel Breugnot
Didier Noël DURAND
Florence Irène Noëlle Leutard
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.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP2576991A1 publication Critical patent/EP2576991A1/de
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to the field of turbomachines and aims an annular distributor of axial turbine formed of distributor segments arranged in ring sectors.
  • the invention relates more particularly to a device for wedging in rotation of these sectors inside the housing.
  • a gas turbine engine as used in aeronautics comprises an upstream inlet through which air is sucked and then compressed while being guided through the compressor stages.
  • the compressed air is introduced into a combustion chamber where the fuel with which it is mixed is also admitted and where the combustion takes place.
  • the hot combustion gases are expanded in the various turbine stages, generally a high pressure stage immediately downstream of the chamber and receiving the gases at the highest temperature compatible with the holding of the materials. After this first expansion, the gases are expanded again by being guided through the so-called low pressure turbine stages.
  • a turbine stage includes a distributor wheel upstream of a turbine impeller.
  • An axial flow distributor wheel comprises a plurality of blades arranged radially with respect to the axis of the machine connecting a radially inner annular element and a radially outer annular element; the assembly forms an annular vein opposite the moving blades of a turbine wheel.
  • the movable wheel is itself constituted by blades extending radially from the rim of a disc or a drum movable about an axis of rotation. The blades are traversed axially by the engine gases.
  • the low pressure section of an engine thus generally comprises several turbine stages.
  • the distributor wheels are segmented into a plurality of sectors distributed around the axis of the machine, each segment being formed of a plurality of vanes between two ring sectors.
  • Each segment is mounted inside the turbine housing by the radially outer ring sector.
  • the latter comprises an upstream retaining means and a downstream retaining means.
  • These means are for example annular rails formed in the inner wall of the housing on which come bearing surfaces provided on the ring sectors of the distributor segments.
  • the assembly is arranged to allow the relative expansion of the distributor relative to the housing which is a function of the variations in speed of the machine. Due to the axial symmetry of the distributor wheels and the tangential forces resulting from the gas flow passing through them, it is necessary to provide locking means for rotating sectors.
  • the patent FR 2,743,603 in the name of SNECMA describes a method of mounting such distributor segments inside a housing.
  • the distributor segments comprise a peripheral outer rib, perpendicular to the axis of the distributor, supported by faces, one radially outer, the other downstream, on corresponding faces of the inner wall of the housing. Clamps, formed by the downstream turbine ring at this level, retain the segments and hold them in place against the radial movements.
  • a protrusion on the upstream face of the rib of each segment comprises a notch in which is housed an antirotation pin.
  • This pin consists of a head housed in said notch and a rod slid into a radial bore of the housing wall. This pin thus prevents any rotational movement of the distributor segment around the axis of the latter.
  • a sheet which is interposed between the segment and the inner wall of the housing.
  • This thermal protection plate is supported upstream against a radial surface portion formed in the inner wall of the housing.
  • the upstream edge of the protective sheet is bent radially inwards to form a pin which also bears on an upstream edge of the segment and participates in maintaining it against the upstream rail of the housing.
  • Downstream the protection plate comprises a notch with a tongue in the bottom of the notch which rests against the anti-rotation pin of the segment. The tongue is actually wedged in a thin groove of the pawn.
  • This assembly gives complete satisfaction in terms of maintaining the distributor inside the housing and the thermal protection thereof.
  • the present invention aims to remedy this problem.
  • the pin comprising a head housed in the notch of the segment and a rod coming into the housing formed on the housing, said surface portion is integral with the head of the antirotation pin.
  • This embodiment has the advantage of only involving the antirotation pin, the rest of the parts: distributor segment, thermal protection plate and housing remaining unchanged. This results in a significant economic advantage, the existing pawn being able to be replaced by the modified pawn without modifying the surrounding pieces.
  • This replacement can be carried out in nine as a preventive measure or during a repair.
  • said surface portion is constituted by a shoulder machined in the head of the anti-rotation pin; more particularly said portion of surface is formed by a lug extending parallel to the axis of the distributor and bearing against the inner wall of the housing.
  • the device of the invention finds an interesting application in the configuration described in the patent FR 2,743,603 , the distributor segment comprising a rib, perpendicular to the axis of the distributor, bearing against the inner wall of the housing and said notch is formed in a projection provided on one side of the rib.
  • the thermal protection plate is preferably in the form of a ring sector with a notch corresponding to said projection, the tongue being formed in the bottom of the notch. More particularly, the protective plate is disposed upstream with respect to the rib of the distributor segment and the antirotation pin.
  • the invention also relates to an antirotation pin suitable for use in the above device, the pin comprising a straight rod and a head with a first parallel face. to the axis of the rod and a surface portion perpendicular to said first face, on the opposite side to the rod.
  • the pin comprises a tab perpendicular to the axis of the right rod, said surface portion being formed on the tab.
  • the invention also relates to a gas turbine engine comprising a turbine stage with a device as described above.
  • a gas turbine engine 1 of the turbofan type comprises from upstream to downstream, here from left to right, a fan 2 with a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6 and a low turbine pressure 7.
  • the low-pressure turbine 7 comprising several stages moving on the same rotor drives via a central shaft, the assembly formed by the fan 2 and the low-pressure compressor 3.
  • the high-pressure turbine 6 to a single stage independently drives the high pressure compressor 4.
  • FIG. 2 there is shown a partial view of the low pressure turbine section 7 at its outer circumference.
  • a distributor 8 or stator is upstream of a wheel with moving blades 9 inside the casing 10 of the turbine.
  • the moving wheel rotates about the axis of the machine inside a turbine ring 9 '.
  • the distributor 8 is formed of vanes arranged in a wheel divided into a plurality of segments 80 distributed circumferentially around the axis of the machine. Each segment 80 comprises several adjacent stationary vanes integral with a ring sector element 81.
  • the distributor segment 80 is held upstream by a rail-shaped rib 101 extending axially from the inner wall of the housing 10. ; an upstream hook 82 integral with the ring sector element 81 bears against the radially outer face of the rail 101.
  • the element 81 Downstream the element 81 comprises a peripheral radial rib 83, perpendicular to the axis of the distributor, which is supported by a radially outer face 83a and a downstream face 83b on corresponding faces of an annular rail 102 which extends axially from the inner wall of the housing 10 with a downstream edge turned towards the axis.
  • an antirotation pin 20 is housed in a radial bore of the housing 10.
  • the pin 20 is projecting inside the housing and is housed in a notch 83c machined in the rib 83 of the segment 80.
  • the rib forms at this level an overthickness 83 'in which the notch is machined.
  • the rib 83 forms a barrier to upstream gases; there is no communication between the area upstream of the rib 83 and the downstream zone.
  • the pin is fit tight in the housing bore but also in the notch 83c.
  • the notch is open upstream and is located at the center of the segment. In this way the segment 80 is held fixed in rotation relative to the housing while being able to expand circumferentially on either side of the pin and move axially to a certain extent.
  • a thermal protection plate 30 is disposed between the ring sector 81 of the segment 80 and the inner wall of the housing.
  • the sheet has a generally ring-shaped shape which upstream bears against a stop surface formed in the casing which may be at the level of the upstream rail 101. Downstream the protective plate 30 is cut into a notch along the contour of the projection 83 'of the rib. A tongue 30a in the bottom of the notch bears against the anti-rotation pin 20.
  • the sheet being slightly deformable a spring effect may be provided to ensure the maintenance of the sheet during operation of the turbomachine.
  • the figure 4 shows the anti-rotation counter of the prior art alone. It comprises a cylindrical rod 21 whose diameter allows a tight fit in the bore of the housing.
  • the pin comprises a head 22 forming the bar of a T with the rod 21. This head is of parallelepiped shape with two flanks 22a and 22b parallel to the axis of the rod 21 and between them.
  • the tongue 30a of the protective plate bears against the face perpendicular to the first two 22a and 22b, disposed upstream when the pin is in the notch 83c of the rib 83.
  • the antirotation counter has been modified.
  • the antirotation peg according to the invention bears the same references as the prior art pin to which 100 has been added.
  • This pawn 120 is visible on Figures 5 and 6 . It is similar to the pin 20 with a rod 121 a head 122 and flanks 122a and 122b. The dimensions are the same than that of the pin 20. It further comprises a tab 122c which extends perpendicular to the axis of the rod 121 and the width of the head 120. It is disposed between the rod and the head. Its thickness is calibrated.
  • the figure 5 shows the new pin 120 in position. As the pin 20 it ensures the rotation of the distributor relative to the housing 10. It should be noted that compared to the prior art only the pin has been modified. The other elements: distributor, sheet and housing are the same. The tongue is in abutment against the upstream side of the head 122 of the antirotation pin. The tab 122c resting against the housing forms a surface against which the downstream edge of the sheet is likely to abut. If a friction occurs during the operation of the turbomachine, the area impaired by wear will be the surface of the tab 122c turned inward; in repair, it will suffice if necessary to replace the pin 120 without having to reload the inner wall of the housing. The cost of repair will be greatly reduced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Turbomaschine, die Folgendes umfasst:
    - ein ringförmiges Gehäuse (10), das eine Innenwand aufweist,
    - mindestens ein Verteilersegment (80), das einen Ringsektor bildet, der in dem ringförmigen Gehäuse (10) aufgenommen ist und eine Außenwand aufweist, wobei jedes Segment (80) mehrere nebeneinander liegende stationäre Schaufeln, die fest mit dem Ringsektor verbunden sind, umfasst,
    - ein Wärmeschutzblech (30), das zwischen die Innenwand des Gehäuses und die Außenwand des Verteilersegments (80) eingefügt ist,
    - eine Vorrichtung zum Verkeilen in Drehung des Verteilersegments (80), wobei die Vorrichtung einen Rotationsschutzklotz (120) umfasst, der sowohl über ein radiales inneres Ende in einer Raste (83c), die auf dem Verteilersegment (80) eingerichtet ist, montiert ist, als auch über ein radiales äußeres Ende in einer Aufnahme, die auf dem Gehäuse eingerichtet ist, in das der Rotationsschutzklotz (120) vorsteht,
    - wobei das Wärmeschutzblech (30) an einem stromabwärtigen Ende eine Lasche (30a) umfasst, die gegen den Rotationsschutzklotz (120) aufliegt, dadurch gekennzeichnet, dass der Rotationsschutzklotz einen Oberflächenabschnitt (122c) umfasst, der radial zwischen der Lasche (30a) und der Innenwand des Gehäuses eingerichtet ist, der einen radialen Anschlag bei einer eventuellen radialen Bewegung des Wärmeschutzblechs (30) während des Betriebs der Turbomaschine bildet, wobei der Oberflächenabschnitt eine obere Oberfläche in Auflage gegen die Innenwand des Gehäuses und ein stromaufwärtiges Ende frei von jeder Berührung mit dem Gehäuse aufweist.
  2. Turbomaschine nach dem vorhergehenden Anspruch, deren Rotationsschutzklotz (120) einen Kopf (122) umfasst, der in der Raste (83c) des Verteilersegments (80) aufgenommen ist, und einen Schaft (121), der in die Aufnahme kommt, die auf dem Gehäuse eingerichtet ist, wobei der Oberflächenabschnitt (122c) fest mit dem Kopf (122) des Rotationsschutzklotzes verbunden ist.
  3. Turbomaschine nach dem vorhergehenden Anspruch, deren Oberflächenabschnitt (122c) aus einem Ansatz besteht, der in den Kopf des Rotationsschutzklotzes gearbeitet ist.
  4. Turbomaschine nach einem der vorhergehenden Ansprüche, deren Oberflächenabschnitt (122c) durch eine Pratze gebildet ist, die zu der Achse des Verteilers parallel ist und gegen die Innenwand des Gehäuses aufliegt.
  5. Turbomaschine nach einem der vorhergehenden Ansprüche, wobei das Verteilersegment (80) eine Rille (83) senkrecht zu der Achse des Verteilers umfasst und gegen die Innenwand des Gehäuses aufliegt, von dem eine Raste (83c) in einem Vorsprung (83') gebildet ist, der auf der Seite der Rille (83) vorgesehen ist.
  6. Turbomaschine nach dem vorhergehenden Anspruch, deren Wärmeschutzblech (30) die Form eines Ringsektors mit einem Ausschnitt, der dem Vorsprung (83') entspricht, hat, wobei die Lasche (30a) in dem Grund des Ausschnitts eingerichtet ist.
  7. Turbomaschine nach einem der Ansprüche 5 und 6, deren Wärmeschutzblech (30) stromaufwärts in Bezug zu der Rille (83) des Verteilersegments (80) und des Rotationsschutzklotzes (120) angeordnet ist.
  8. Turbomaschine nach einem der vorhergehenden Ansprüche, deren Rotationsschutzklotz abnehmbar ist.
EP11728341.6A 2010-06-01 2011-05-31 Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse Active EP2576991B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1054263A FR2960591B1 (fr) 2010-06-01 2010-06-01 Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation
PCT/FR2011/051251 WO2011151596A1 (fr) 2010-06-01 2011-05-31 Turbomachine avec un dispositif pour caler en rotation un segment de distributeur dans un carter; pion antirotation

Publications (2)

Publication Number Publication Date
EP2576991A1 EP2576991A1 (de) 2013-04-10
EP2576991B1 true EP2576991B1 (de) 2017-01-25

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EP11728341.6A Active EP2576991B1 (de) 2010-06-01 2011-05-31 Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse

Country Status (9)

Country Link
US (1) US9562441B2 (de)
EP (1) EP2576991B1 (de)
JP (1) JP5796066B2 (de)
CN (1) CN102918230B (de)
BR (1) BR112012029475A2 (de)
CA (1) CA2800262A1 (de)
FR (1) FR2960591B1 (de)
RU (1) RU2558174C2 (de)
WO (1) WO2011151596A1 (de)

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Publication number Priority date Publication date Assignee Title
FR2985792B1 (fr) 2012-01-18 2014-02-07 Snecma Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine
US9051849B2 (en) * 2012-02-13 2015-06-09 United Technologies Corporation Anti-rotation stator segments
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
US10240467B2 (en) 2012-08-03 2019-03-26 United Technologies Corporation Anti-rotation lug for a gas turbine engine stator assembly
FR2995340A1 (fr) * 2012-09-12 2014-03-14 Snecma Tole de protection thermique avec butee radiale, notamment pour distributeur de turbomachine
FR3002272A1 (fr) * 2013-02-19 2014-08-22 Snecma Secteur de distributeur a anti-rotation pour secteur adjacent
FR3003894B1 (fr) * 2013-03-29 2017-10-27 Snecma Organe de verrouillage en rotation pour un distributeur et un anneau d'une turbomachine
FR3039201B1 (fr) * 2015-07-22 2017-07-21 Snecma Partie de turbomachine a tole de protection thermique pourvue d'epingles
US10280773B2 (en) 2016-04-06 2019-05-07 General Electric Company Turbomachine alignment key and related turbomachine
FR3069014B1 (fr) * 2017-07-11 2021-02-26 Safran Aircraft Engines Partie de turbomachine a tole ressort
FR3085412B1 (fr) * 2018-08-31 2020-12-04 Safran Aircraft Engines Secteur de distributeur d'une turbomachine comprenant une encoche anti-rotation a insert d'usure
FR3096397B1 (fr) 2019-05-21 2021-04-16 Safran Aircraft Engines Pion amovible sur distributeur de turbomachine
GB2588929B (en) * 2019-11-14 2023-09-27 Cummins Ltd Pin member for turbine
CN117569923B (zh) * 2024-01-12 2024-04-05 成都中科翼能科技有限公司 一种燃气轮机涡轮支点结构

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US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield

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FR2743603B1 (fr) * 1996-01-11 1998-02-13 Snecma Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine
DE19959665A1 (de) * 1999-12-10 2001-06-13 Rolls Royce Deutschland Befestigungsanordnung für die den Strömungskanal einer Strömungsmaschine begrenzenden Wandsegmente
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FR2829525B1 (fr) * 2001-09-13 2004-03-12 Snecma Moteurs Assemblage de secteurs d'un distributeur de turbine a un carter
DE10312956B4 (de) * 2003-03-22 2011-08-11 MTU Aero Engines GmbH, 80995 Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes
FR2899274B1 (fr) * 2006-03-30 2012-08-17 Snecma Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
FR2899275A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
FR2941488B1 (fr) * 2009-01-28 2011-09-16 Snecma Anneau de turbine a encoche anti-rotation

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US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield

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Publication number Publication date
BR112012029475A2 (pt) 2017-01-24
EP2576991A1 (de) 2013-04-10
FR2960591B1 (fr) 2012-08-24
CA2800262A1 (fr) 2011-12-08
RU2012152657A (ru) 2014-07-20
JP5796066B2 (ja) 2015-10-21
US9562441B2 (en) 2017-02-07
CN102918230B (zh) 2015-08-26
WO2011151596A1 (fr) 2011-12-08
RU2558174C2 (ru) 2015-07-27
FR2960591A1 (fr) 2011-12-02
US20130078086A1 (en) 2013-03-28
CN102918230A (zh) 2013-02-06
JP2013531165A (ja) 2013-08-01

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