EP2009245B2 - Gebläserotor - Google Patents

Gebläserotor Download PDF

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Publication number
EP2009245B2
EP2009245B2 EP08159121.6A EP08159121A EP2009245B2 EP 2009245 B2 EP2009245 B2 EP 2009245B2 EP 08159121 A EP08159121 A EP 08159121A EP 2009245 B2 EP2009245 B2 EP 2009245B2
Authority
EP
European Patent Office
Prior art keywords
blade root
rotor according
spacer
slot
wedge
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.)
Active
Application number
EP08159121.6A
Other languages
English (en)
French (fr)
Other versions
EP2009245B1 (de
EP2009245A1 (de
Inventor
Olivier Belmonte
Jean-Luc Christina Yvon Goga
Jean-Noël Mahieu
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
Original Assignee
Safran Aircraft Engines SAS
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
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2009245A1 publication Critical patent/EP2009245A1/de
Publication of EP2009245B1 publication Critical patent/EP2009245B1/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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

Definitions

  • the invention generally relates to a turbomachine rotor, more particularly a fan rotor comprising a disc provided with cells at its periphery and blades respectively attached to said rotor, each blade comprising a blade root engaged in a corresponding cell.
  • the invention relates to an improvement to an elongated wedge which is interposed between the blade root and the bottom of the cell.
  • the invention is particularly applicable to the assembly of blades made of 3D woven composite material, which are increasingly used in blowers. It relates to a shim well suited to this type of blade (although not exclusively), the shim itself possibly being made of the same material or of a similar material.
  • One of the aims of the invention is to improve the behavior of the blades of a rotor, particularly a fan rotor, in the event of a serious incident resulting for example from the ingestion of a bird.
  • the invention proposes a new type of shim whose shape has been defined to reduce the shock during contact between the blade and the cell, absorb part of the energy generated by the impact and reduce the risk of damage. of dawn.
  • the invention relates firstly to a fan rotor comprising a disc provided with cells at its periphery and blades respectively attached to said rotor, each blade comprising a blade root engaged in a corresponding cell and each cell containing an elongated wedge interposed between the blade root and the bottom of the cell, characterized in that said wedge is made of an elastically deformable material, in that at least one longitudinal section of this wedge has a transverse profile in the form of arc to define two lateral zones in contact with corresponding lateral zones of the blade root and remote from the bottom of the cell and a central zone facing the corresponding central zone of the cell bottom, said central zone of said section being in contact with the bottom of the cell.
  • the central zone of said section is remote from the corresponding central zone of the blade root. In other words, a slight space remains between the central zone of the section of the wedge and the central zone facing the blade root.
  • the wedge consists of several aforementioned sections joined together by narrower junctions.
  • the wedge has a wavy profile in its own longitudinal direction.
  • said wedge may have a central region longitudinally in contact with the bottom of the cell and two end regions (on either side of the central region, longitudinally) in contact with the blade root.
  • the section of the shim in normal operation, is adapted to the shape of the surrounding parts (fan disc cavity and fan blade) and assembly is done with a slight stress between the blade root and the bottom. of the alveolus.
  • the blade root is pressed against its bearing surfaces, resting on the bottom of the cell (in the central part) and below the blade root on the lateral bearing surfaces thereof.
  • the corrugated profile mentioned above makes it possible to optimize the contacts between the ends and the center of the wedge on the one hand and between the blade and the disc on the other hand.
  • the wedge by its flexibility follows the combined movement of torsion-diving when a critical event occurs. It is inserted to limit the impact between the blade root and the socket of the disc. In addition, the contact zone between the wedge and the underside of the blade root is curved so as to allow relative sliding of the two parts between them, during a pivoting of the blade.
  • the wedge is divided into three sections which react separately to the combined movements of the blade root and make it possible to best accompany the movements and deformations specific to each of the parts of the blade root.
  • a coating of polyurethane film type or the like is placed on and / or under the wedge to allow part of the impact energy to be dissipated and consequently to limit the risks of the wedge breaking and the blade root cracking.
  • the wedge is made of a one-piece elastic composite material and preferably of a 3D woven composite material.
  • the result is particularly advantageous when the blades are themselves made of a composite material. of the same nature.
  • the invention also relates to a wedge intended to be inserted into a fan rotor socket, characterized in that it consists of an elastically deformable material and in that it comprises at least one longitudinal section with a profile. transverse arch-shaped.
  • a wedge 11 intended to be inserted in a cell 13 of a disc 15 of the fan rotor. Such a disc is partially shown on the figures 2 to 4 .
  • the wedge 11 consists of a single block of elastically deformable material and more particularly here of a 3D woven composite material known per se.
  • the 3-dimensional weaving defining the core of the part is coated with resin.
  • the wedge comprises at least one longitudinal section with a transverse profile in the form of an arc.
  • three sections 17a, 17b, 17c of this type are provided (their number could be different) joined by narrower junctions 18, of the same material, the whole forming a single piece.
  • Such a wedge is intended to be inserted into a tangential cell 13 formed at the periphery of the rotor disc 15.
  • it is a fan rotor disc to which blades 20 are attached.
  • Each blade has a blade root 21 engaged in a corresponding cell 13.
  • a shim such as the one shown in figures 1 and 2 is housed in each cell 13 by being interposed between the blade root 21 and the bottom 13a of the cell 13.
  • the wedge 11 is preferably made of a 3D woven composite material. More generally, the wedge is made of an elastically deformable material.
  • the or each longitudinal section 17a-17c of this wedge has a transverse profile in the form of an arc to define two lateral zones 25a, 25b in contact with corresponding lateral zones 26a, 26b of the foot d blade 20 while being away from the bottom of the cell. Furthermore, a central zone 29 of the wedge section is located opposite the corresponding central zone 30 of the cell bottom.
  • the central zone of said section can be moved away from the corresponding central zone of the blade root, leaving a slight space 32 between them.
  • the wedge 11 has a wavy profile in its longitudinal direction.
  • the wedge has a longitudinal central region 11a in contact with the bottom of the cell and two end regions 11b in contact with the blade root but remote from the bottom of the cell.
  • the shim is shown mounted under stress between the blade root and the bottom of the cell, so that its longitudinal curvature between the center and the ends is less than it is in the unstressed state, before mounting.
  • a coating of polyurethane film type or the like is provided on and / or under the wedge. This makes it possible to dissipate part of the energy of the impact, in the event of an incident, and consequently to limit the risks of rupture of the wedge or of cracking of the blade root.
  • this type of wedge is well suited to maintaining a blade made of 3D woven composite material in its socket, at rest or in normal operation.
  • Elongated holes 35 are also made in the central zones of at least certain sections, to further improve the flexibility and the deformability of the various parts of the wedge.
  • the shape of the wedge combined with the classic shape of the blade root makes it possible to optimize the contacts between the ends and the center of the wedge on the one hand as well as the contact between the blade root and the walls of the on the other hand.
  • the wedge section also has two thinning lines 36 between the side parts in contact with the blade root and the middle part facing the bottom of the cell.
  • each junction 18 connecting two adjacent sections 17a-17c is located substantially in the extension and continuity of the central zones of these two sections, which it joins.
  • said junction has a transverse profile substantially identical to that of the central zone of an aforementioned section.
  • the proposed solution which consists in giving a suitable shape to the wedge and preferably in producing it in a flexible material identical to the material of the composite blade, makes it possible to eliminate the risks of cracking of the blade root.
  • the pre-stressing during assembly allows place the blade root on its seats, resting on the bottom of the disc socket.
  • the wavy shape of the wedge, in the axial direction, makes it possible to optimize the contacts between the ends and the center of the wedge on the one hand and between the vane and the disc on the other hand.
  • the wedge by its flexibility, follows the combined torsion / plunging movement of the blade root, during a critical event.
  • the wedge is inserted to limit the impact between the blade root and the socket of the disc.
  • the area in contact between the wedge and the underside of the blade root is curved, which allows relative sliding of the two parts during significant pivoting.
  • the three sections of the wedge react separately to the movement of the blade, which makes it possible to best accompany the movement of each of the parts of the root of the blade.

Landscapes

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

Claims (11)

  1. Gebläserotor, umfassend eine Scheibe, die mit Vertiefungen an ihrer Peripherie versehen ist, und Schaufeln, die jeweils am Rotor befestigt sind, wobei jede Schaufel (20) einen Schaufelfuß (21), umfasst, der in einer entsprechenden Vertiefung (13) in Eingriff ist, und wobei jede Vertiefung einen länglichen Keil (11) einschließt, der zwischen dem Schaufelfuß und dem Boden der Vertiefung zwischengefügt ist, wobei der Keil aus einem elastisch verformbaren Material ist, dadurch gekennzeichnet, dass mindestens ein Längsabschnitt (17a-17c) dieses Keils ein Querprofil in Bogenform hat, um zwei seitliche Kontaktzonen mit entsprechenden seitlichen Zonen des Schaufelfußes, die vom Boden der Vertiefung entfernt sind, und eine zentrale Zone (29) gegenüber der entsprechenden zentralen Zone des Bodens der Vertiefung zu definieren, wobei die zentrale Zone (29) der Abschnitt mit dem Boden der Vertiefung (13) in Kontakt ist.
  2. Rotor gemäß Anspruch 1, dadurch gekennzeichnet, dass die zentrale Zone (29) des Abschnitts von der entsprechenden zentralen Zone des Schaufelfußes entfernt ist.
  3. Rotor gemäß Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Keil von mehreren vorgenannten Abschnitten (17a-17c) gebildet ist, die durch schmalere Verbindungen (18) verbunden sind.
  4. Rotor gemäß Anspruch 3, dadurch gekennzeichnet, dass jede Verbindung (18) im Wesentlichen in der Verlängerung und der Kontinuität der zentralen Zonen der zwei Abschnitte, die sie verbindet, angeordnet ist.
  5. Rotor gemäß Anspruch 4, dadurch gekennzeichnet, dass die Verbindung (18) ein Querprofil im Wesentlichen identisch mit jenem der zentralen Zone eines vorgenannten Abschnitts hat.
  6. Rotor gemäß einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Keil (11) entlang seiner Längsrichtung ein welliges Profil hat (Fig. 2).
  7. Rotor gemäß Anspruch 6, dadurch gekennzeichnet, dass der Keil längs einen zentralen Bereich (11a) in Kontakt mit dem Boden der Vertiefung und zwei äußerste Bereiche (11b) in Kontakt mit dem Schaufelfuß aufweist.
  8. Rotor gemäß einem der Ansprüche 6 oder 7, dadurch gekennzeichnet, dass der Keil (11) unter Spannung zwischen dem Schaufelfuß (21) und dem Boden (13a) der Vertiefung montiert ist.
  9. Rotor gemäß einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Keil aus einem 3D-gewebten Verbundstoff ist.
  10. Rotor gemäß einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Schaufeln (20) aus einem 3D-gewebten Verbundstoff sind.
  11. Turbomaschine, dadurch gekennzeichnet, dass sie einen Rotor gemäß einem der Ansprüche 1 bis 10 umfasst.
EP08159121.6A 2007-06-26 2008-06-26 Gebläserotor Active EP2009245B2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0756015A FR2918129B1 (fr) 2007-06-26 2007-06-26 Perfectionnement a une cale intercalee entre un pied d'aube et le fond de l'alveole du disque dans laquelle il est monte

Publications (3)

Publication Number Publication Date
EP2009245A1 EP2009245A1 (de) 2008-12-31
EP2009245B1 EP2009245B1 (de) 2017-10-04
EP2009245B2 true EP2009245B2 (de) 2020-12-16

Family

ID=39154378

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08159121.6A Active EP2009245B2 (de) 2007-06-26 2008-06-26 Gebläserotor

Country Status (6)

Country Link
US (2) US8529209B2 (de)
EP (1) EP2009245B2 (de)
JP (1) JP5496476B2 (de)
CA (1) CA2634942C (de)
FR (1) FR2918129B1 (de)
RU (1) RU2479724C2 (de)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2945074B1 (fr) * 2009-04-29 2011-06-03 Snecma Cale d'aube de soufflante renforcee
US8616850B2 (en) * 2010-06-11 2013-12-31 United Technologies Corporation Gas turbine engine blade mounting arrangement
EP2455588B1 (de) * 2010-11-15 2017-03-01 MTU Aero Engines GmbH Sicherungsmittel zur axialen Sicherung eines Schaufelfußes einer Turbomaschinenschaufel
IT1403416B1 (it) * 2010-12-21 2013-10-17 Avio Spa Rotore palettato di una turbina a gas per motori aeronautici e metodo per il raffreddamento di detto rotore palettato
GB201106278D0 (en) * 2011-04-14 2011-05-25 Rolls Royce Plc Annulus filler system
FR2975428B1 (fr) * 2011-05-17 2015-11-20 Snecma Roue a aubes de turbomachine
EP2562356A1 (de) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Schaufelanordnung
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
US8851854B2 (en) 2011-12-16 2014-10-07 United Technologies Corporation Energy absorbent fan blade spacer
US9359906B2 (en) * 2012-12-18 2016-06-07 United Technologies Corporation Rotor blade root spacer with a fracture feature
US9422819B2 (en) * 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
US20150322805A1 (en) * 2012-12-27 2015-11-12 United Technologies Corporation Blade underroot spacer with hook removal
US10508556B2 (en) 2013-01-17 2019-12-17 United Technologies Corporation Rotor blade root spacer with grip element
US9840922B2 (en) 2014-03-07 2017-12-12 United Technologies Corporation Fan blade spacer
US20160024946A1 (en) * 2014-07-22 2016-01-28 United Technologies Corporation Rotor blade dovetail with round bearing surfaces
GB201417417D0 (en) * 2014-10-02 2014-11-19 Rolls Royce Plc Slider
US10099323B2 (en) 2015-10-19 2018-10-16 Rolls-Royce Corporation Rotating structure and a method of producing the rotating structure
FR3102206B1 (fr) * 2019-10-18 2023-02-17 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l’alvéole en même temps qu’un pied de l’aube
RU198476U1 (ru) * 2020-02-03 2020-07-13 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Диск ротора газотурбинного двигателя из никелевого жаропрочного сплава
US11242761B2 (en) 2020-02-18 2022-02-08 Raytheon Technologies Corporation Tangential rotor blade slot spacer for a gas turbine engine
FR3107724B1 (fr) 2020-02-27 2022-06-24 Safran Aircraft Engines Rotor de soufflante à aubes à calage variable et turbomachine équipée d’un tel rotor
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신
US12140046B2 (en) 2020-10-16 2024-11-12 Safran Aircraft Engines Fastening assembly for a turbomachine blade
FR3120389B1 (fr) 2021-03-04 2023-06-02 Safran Aircraft Engines Ensemble pour un rotor pour une turbomachine
FR3121171B1 (fr) 2021-03-25 2023-04-14 Safran Aircraft Engines Rotor de soufflante pour une turbomachine
FR3124546B1 (fr) 2021-06-28 2024-05-10 Safran Aircraft Engines Aube de rotor a maintien ameliore, procede de fabrication d’une telle aube et rotor comportant une telle aube
KR20230091604A (ko) * 2021-12-16 2023-06-23 한화에어로스페이스 주식회사 보호심을 구비하는 로터 어셈블리 및 이를 포함하는 가스 터빈 엔진
FR3132126B1 (fr) * 2022-01-24 2025-02-21 Safran Aircraft Engines Moteur d'aéronef comprenant des aubes fixées au carter
FR3139159B1 (fr) * 2022-08-31 2024-07-19 Safran Aircraft Engines Roue de turbine comprenant un dispositif de maintien radial de pieds d’aube dans les alveoles d’un disque de rotor
US12146421B2 (en) * 2022-10-28 2024-11-19 Rtx Corporation Deformable root spacer for a gas turbine engine rotor blade
FR3159192A1 (fr) * 2024-02-08 2025-08-15 Safran Aircraft Engines Cale pour aube mobile de turbomachine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040076523A1 (en) † 2002-10-18 2004-04-22 Sinha Sunil Kumar Method and apparatus for facilitating preventing failure of gas turbine engine blades
US20050207892A1 (en) † 2004-02-25 2005-09-22 Mitsubishi Heavy Industries, Ltd. Rotating blade body and rotary machine using rotating blade body

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU443192A1 (ru) * 1972-11-14 1974-09-15 Моторостроительное конструкторское бюро Устройство дл уплотнени рабочих лопаток турбины
JP2500245Y2 (ja) * 1991-04-12 1996-06-05 川崎重工業株式会社 動翼固定装置
US5519677A (en) * 1993-03-22 1996-05-21 Sony Corporation Biaxial actuator for driving an objective lens in both focusing and tracking directions
DE4430636C2 (de) * 1994-08-29 1997-01-23 Mtu Muenchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorunwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
FR2807096B1 (fr) * 2000-03-30 2002-05-31 Abb Alstom Power Nv Disque rotorique de turbine equipe d'ailettes a pied de sapin et procede de montage d'une ailette sur un disque
FR2841609B1 (fr) * 2002-06-27 2004-09-10 Snecma Moteurs Cale de retenue du pied des aubes de soufflante
RU2227150C1 (ru) * 2002-12-10 2004-04-20 Открытое акционерное общество "Термостойкие изделия и инженерные разработки" Слоистый уплотнительный материал для прокладки
GB0424481D0 (en) * 2004-11-05 2004-12-08 Rolls Royce Plc Composite aerofoil
FR2881174B1 (fr) * 2005-01-27 2010-08-20 Snecma Moteurs Dispositif de positionnement d'une aube et disque aubage comportant un tel dispositif

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040076523A1 (en) † 2002-10-18 2004-04-22 Sinha Sunil Kumar Method and apparatus for facilitating preventing failure of gas turbine engine blades
US20050207892A1 (en) † 2004-02-25 2005-09-22 Mitsubishi Heavy Industries, Ltd. Rotating blade body and rotary machine using rotating blade body

Also Published As

Publication number Publication date
CA2634942A1 (fr) 2008-12-26
US20090004017A1 (en) 2009-01-01
US20130259695A1 (en) 2013-10-03
FR2918129A1 (fr) 2009-01-02
RU2008125805A (ru) 2009-12-27
EP2009245B1 (de) 2017-10-04
FR2918129B1 (fr) 2009-10-30
CA2634942C (fr) 2015-12-01
US8529209B2 (en) 2013-09-10
EP2009245A1 (de) 2008-12-31
JP2009008079A (ja) 2009-01-15
US8845294B2 (en) 2014-09-30
RU2479724C2 (ru) 2013-04-20
JP5496476B2 (ja) 2014-05-21

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