EP2722486A1 - Support d'étanchéité pour ensemble statorique - Google Patents

Support d'étanchéité pour ensemble statorique Download PDF

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Publication number
EP2722486A1
EP2722486A1 EP12188822.6A EP12188822A EP2722486A1 EP 2722486 A1 EP2722486 A1 EP 2722486A1 EP 12188822 A EP12188822 A EP 12188822A EP 2722486 A1 EP2722486 A1 EP 2722486A1
Authority
EP
European Patent Office
Prior art keywords
axial
seal carrier
shell element
flange
radial
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12188822.6A
Other languages
German (de)
English (en)
Other versions
EP2722486B1 (fr
Inventor
Frank Stiehler
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12188822.6A priority Critical patent/EP2722486B1/fr
Priority to US14/056,876 priority patent/US9856736B2/en
Publication of EP2722486A1 publication Critical patent/EP2722486A1/fr
Application granted granted Critical
Publication of EP2722486B1 publication Critical patent/EP2722486B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to a fish-mouth seal carrier for a guide vane assembly of a gas turbine, a vane assembly or gas turbine with such a fish-mouth seal carrier and a method for its production.
  • the fishmouth seal carrier is composed of a total of five sheet metal parts: an S-shaped sheet metal part to form a fishmouth gasket, an L-shaped sheet metal part to form an opposite fishmouth gasket, a U-shaped sheet metal part, a radial flange of the platform and a head between its radial legs a screw is arranged, a C-shaped sheet metal part in which a washer is received, which passes through the screw, and finally a G-shaped sheet metal part which carries the S-shaped sheet metal part, wherein the honeycomb seal on the L and the G is attached shaped sheet metal part.
  • An object of an embodiment of the present invention is to improve the manufacture and / or operation of a gas turbine.
  • a fishmouth seal carrier for a guide vane assembly of a gas turbine on a first half-shell member and a materially connected thereto, in particular welded, second half-shell element, which together a box section with two axial legs and form two radial legs.
  • a sealing element which in one embodiment has a honeycomb seal, in particular can be, is arranged on an outer side of a, in installation position radially inner, this axial leg of the box profile.
  • a box profile is understood in particular to mean a profile which has two, in particular at least substantially parallel, axial legs and two, in particular at least substantially parallel, radial legs, in particular thereof, which in a further embodiment is preferably at least substantially rectangular , Corners merge into each other.
  • the first and / or second half-shell element has in each case an axial flange for forming a fish mouth seal, which is formed integrally or integrally with the half-shell element, in particular, ur- or reshaped.
  • the Axialflansch acts in one embodiment as a so-called deflector of Fischmauldichtung. Opposite it radially in one embodiment is a radially inner platform of a vane assembly having one or more vanes to which the fishmouth seal carrier in one embodiment is suspended by means of a spoke centering. Radial between the platform and the axial flange, an axial flange of an adjacent blade assembly is arranged with one or more blades.
  • a Fischmauldichtung upstream and / or downstream of the vane assembly may be formed or have the first and / or second half-shell element of the fish-mouth seal carrier having a corresponding, designed as a deflector Axialflansch.
  • the axial flange of the first and / or second half-shell element extends in one embodiment, at least substantially, in the axial direction. He may have radial paragraphs or steps.
  • the first half-shell element has a U-profile for forming the box profile and a radial flange formed integrally therewith.
  • the radial flange can be followed by the axial flange on the side opposite the U-profile to form a fish gauge.
  • the second half-shell element can have a radial flange, to which the axial flange can connect in one embodiment to form a fish-measuring direction.
  • the radial flange together with the U-profile of the first half-shell element, can form the box profile, i. Completing the U-shaped profile lid-like and essentially form a radial leg of the U-profile.
  • a U-profile for forming the box profile also connects to the radial flange on the second half-shell element on the axial flange, so that both half-shell elements each form a radial leg and in each case a part of the two axial legs of the box profile.
  • a slider for suspending the fishmouth seal carrier on the vane assembly between the radial flange of the first half-shell member and the radial flange of the second half-shell member is mounted on both sides.
  • the fish-mouth seal carrier may for this purpose have a bolt which passes through passage openings in the radial flanges and the sliding body arranged between them and thus defines them.
  • the bolt can in particular be detachably or non-detachably fastened to the radial flanges, in particular screwed or riveted.
  • the sliding body can be accommodated in a passage opening, in particular a slot, of the guide blade arrangement, so that the fish-mouth seal carrier is suspended by means of spoke centering on the guide blade arrangement.
  • the sliding body can space and / or support the two radial flanges and thus improve the rigidity of the box profile.
  • an additional sheet may be fixed to the radial flange of the first or second half-shell element. It can be axially supported on the vane assembly and thus secure the fishmouth seal carrier axially.
  • the additional sheet may be arranged in an embodiment between the radial flange of the first half-shell element and the radial flange of the second half-shell element, in particular between the sliding body and a radial flange.
  • the additional sheet may be frictionally secured to the radial flange, in particular clamped between this and the slider, in particular by a bolt which connects the two radial flanges and / or superimposed on the slider.
  • a joint friction is impressed by the frictionally fixed additional sheet, which can advantageously damp vibrations.
  • the additional sheet can be firmly bonded to the radial flange, in particular welded to this.
  • the sealing element extends, at least substantially, axially from one to the other radial leg of the box section. In this way, a wide support surface can be provided and the box profile can be optimally used.
  • the sealing element has a honeycomb seal and a carrier, in particular a carrier plate, which is arranged on the outside of the axial leg, in particular cohesively, connected thereto, in particular soldered, welded or glued, and on whose axialschenkelabgewandten side the Honigwabendichtung, in particular cohesively, attached, in particular soldered, welded or glued.
  • the honeycomb seal can extend at least substantially axially from one to the other radial leg of the box profile and, in contrast, the carrier can project axially beyond one or both radial legs. This can protect the Honigwabendichtung especially with an axial rubbing.
  • At least one reinforcing element in particular a reinforcing plate, attached to one or both radial limbs of the box section, in particular cohesively, preferably by welding, soldering or gluing.
  • one or both radial legs may have an integral wall thickness thickening.
  • one or both half-shell elements are formed into a urine.
  • one or both half-shell elements in particular forging technology, can be reshaped.
  • one or both half shell elements are designed as sheet metal construction. In particular, they can have a wall thickness which is a maximum of 5 mm, in particular a maximum of 3 mm, preferably a maximum of 2 mm. Due to the box construction, high rigidity can thus be achieved in one embodiment, despite the low wall thickness and correspondingly low weight.
  • the two half-shell elements are firmly bonded together.
  • they can be welded together, preferably without additional material, in particular by laser or friction welding. This allows a light and reliable joint connection can be achieved.
  • they can also be glued or soldered together.
  • the two half-shell elements are connected to each other at impact, in particular with end faces of one axial leg of a U-profile of the half-shell elements. In this way, the weight can be reduced and / or the welding can be simplified.
  • half-shell elements can be connected to each other surface, in particular by welding of superimposed axial leg of the two half-shell elements.
  • the sealing element Before or after the cohesive bonding, the sealing element is arranged on an axial leg of the box profile. In particular, it may be made integral with one or both half-shell elements or connected to them prior to their connection. In a further development, the sealing element may be formed axially divided, wherein a part, in particular before the cohesive joining of the two half-shell elements together, with the first half-shell element and the other part is connected to the second half-shell element. Likewise, the sealing element can also be connected to the first and / or second half-shell element after the cohesive joining of the two half-shell elements.
  • the sealing element in particular a Honigwabendichtung or a connected thereto, preferably one-piece, carrier, a seam or joint of the cohesive joint connection of the two half-shell elements covers each other and thus secures the joint connection.
  • the sealing element can be connected to one or both half shell elements in a materially bonded manner, in particular welded, glued or soldered.
  • Fig. 1 shows in an axial section a part of a gas turbine with a vane arrangement with a plurality of vanes 10, at the radially inner (bottom in Fig. 1 ) Platform 11 a fishmouth seal carrier is suspended.
  • the fish-mouth seal carrier has a first half-shell element 1 and a second half-shell element 2 welded thereto, which together form a box profile with two substantially parallel axial limbs (1.1 + 2.1), (1.2 + 2.2) and two substantially parallel radial limbs 1.3, 2.3, which merge into each other in rounded corners.
  • a sealing element in the form of a stepped Honigwabendichtung 3 is disposed on an outer side of the radially inner axial leg (1.1 + 2.1).
  • the first and second half-shell elements each have an axial flange 1.4 and 2.4, respectively, for forming a fish mouth seal, which is formed integrally with the half-shell element and functions as a deflector of the fish-mouth seal. Opposite it radially lies the radially inner platform 11 of the vane arrangement. Radial between the platform 11 and the axial flange 1.4 and 2.4, respectively, an axial flange 20.1 and 21.1 of an adjacent blade assembly with blades 20 and 21 is arranged.
  • the axial flanges 1.4, 2.4 of the first and second half-shell elements extend substantially in the axial direction, wherein they have radial shoulders or steps.
  • the first half-shell element has a U-profile 1.1, 1.2, 1.3 to form the box profile and a thus formed integrally radial flange 1.5.
  • At the radial flange closes on the U-profile radially opposite side (above in Fig. 1 ) Axialflansch 1.4 to form the Fischmauldichtung.
  • the second half-shell element also has a radial flange 2.5 which is substantially parallel to the radial flange 1.5 of the first half-shell element and to which the axial flange 2.4 connects.
  • both half-shell elements joins on the axial flange 2.4 radially opposite side of the radial flange 2.5 a U-profile 2.1, 2.2, 2.3 to form the box profile, so that both half-shell elements each have a radial leg 1.3 and 2.3 and a part 1.1 or 2.1 of an axial leg (1.1 + 2.1) and a part 1.2 or 2.2 of the other axial leg (1.2 + 2.2) of the box profile form.
  • a slider 4 for suspending the fishmouth seal carrier on the vane arrangement is mounted on both sides between the radial flange 1.5 of the first half-shell element and the radial flange 2.5 of the second half-shell element.
  • the fish-mouth seal carrier on a bolt 5, which passes through openings in the radial flanges 1.5, 2.5 and arranged between these sliding body 4 and this determines.
  • the sliding body is received in a passage opening in the form of a slot 12 of the vane arrangement, so that the fish-mouth seal carrier is suspended by means of spoke centering on the vane arrangement.
  • the slider spaced the two radial flanges 1.5, 2.5 against each other and supports them against each other.
  • An additional plate 6 is fixed to the radial flange 1.5 of the first half-shell element. It is supported axially on the vane assembly and thus secures the fishmouth seal carrier axially.
  • the additional sheet is between the radial flange 1.5 of first half-shell element and the radial flange 2.5 of the second half-shell element, in particular the slider 4 and arranged by the bolt 5 frictionally fixed to the radial flange 1.5, in particular clamped between this and the slider 4.
  • the sealing element extends axially substantially from one radial leg 1.3 to the other radial leg 2.3 of the box section.
  • both half-shell elements 1.1-1.5, 2.1-2.5 are formed by casting molding or forging technology. Both half-shell elements are designed as sheet metal construction and have a wall thickness which is a maximum of 5 mm.
  • the two half-shell elements are then welded together without additional material, in particular by laser or friction welding. Both half-shell elements are connected to end faces of one axial limb 1.1, 2.1 of a U-profile of the half-shell elements in abutment with each other.
  • the sealing element 3 is arranged on the axial leg (1.1 + 2.1) of the box profile and welded thereto.
  • the sealing element 3 covers a seam or joint 7 of the cohesive joint connection of the two half-shell elements from each other and thus secures the joint connection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12188822.6A 2012-10-17 2012-10-17 Support de joint d'étanchéité pour ensemble statorique Not-in-force EP2722486B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP12188822.6A EP2722486B1 (fr) 2012-10-17 2012-10-17 Support de joint d'étanchéité pour ensemble statorique
US14/056,876 US9856736B2 (en) 2012-10-17 2013-10-17 Fish mouth seal carrier

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12188822.6A EP2722486B1 (fr) 2012-10-17 2012-10-17 Support de joint d'étanchéité pour ensemble statorique

Publications (2)

Publication Number Publication Date
EP2722486A1 true EP2722486A1 (fr) 2014-04-23
EP2722486B1 EP2722486B1 (fr) 2016-12-07

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP12188822.6A Not-in-force EP2722486B1 (fr) 2012-10-17 2012-10-17 Support de joint d'étanchéité pour ensemble statorique

Country Status (2)

Country Link
US (1) US9856736B2 (fr)
EP (1) EP2722486B1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2960555A1 (fr) * 2014-06-25 2015-12-30 MTU Aero Engines GmbH Système de joint à brosse pour sceller un intervalle entre les éléments d'une turbomachine qui peuvent être déplacés les uns par rapport aux autres
FR3039589A1 (fr) * 2015-07-28 2017-02-03 Snecma Etage de turbomachine, en particulier de turbine basse-pression
EP3208426A1 (fr) 2016-02-18 2017-08-23 MTU Aero Engines GmbH Segment d'aube directrice pour turbomachine
EP3409897A1 (fr) * 2017-05-29 2018-12-05 MTU Aero Engines GmbH Agencement d'étanchéité pour une turbomachine, méthode de fabrication de l'agencement d'étanchéité et turbomachine
EP3483399A1 (fr) * 2017-11-09 2019-05-15 MTU Aero Engines GmbH Dispositif d'étanchéité pour une turbomachine, procédé de fabrication d'un dispositif d'étanchéité et turbomachine
EP3517734A1 (fr) * 2018-01-29 2019-07-31 MTU Aero Engines GmbH Module d'étanchéité pour une turbomachine
IT201900013218A1 (it) * 2019-07-29 2021-01-29 Ge Avio Srl Fascia interna per motore a turbina.
WO2021186135A1 (fr) * 2020-03-19 2021-09-23 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une piece annulaire de serrage
FR3113298A1 (fr) * 2020-08-10 2022-02-11 Safran Aircraft Engines Porte-abradable d’un distributeur basse pression comprenant une unique tôle
EP4345251A1 (fr) * 2022-09-22 2024-04-03 MTU Aero Engines AG Module pour une turbomachine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013212465B4 (de) * 2013-06-27 2015-03-12 MTU Aero Engines AG Dichtanordnung für eine Strömungsmaschine, eine Leitschaufelanordnung und eine Strömungsmaschine mit einer derartigen Dichtanordnung
EP2818643B1 (fr) * 2013-06-27 2018-08-08 MTU Aero Engines GmbH Dispositif d'étanchéité et turbomachine
DE102016222608A1 (de) * 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
DE102017209420A1 (de) 2017-06-02 2018-12-06 MTU Aero Engines AG Dichtungsanordnung mit angeschweißtem Dichtungsblech, Strömungsmaschine und Herstellungsverfahren
DE102018210513A1 (de) * 2018-06-27 2020-01-02 MTU Aero Engines AG Rotor für eine Strömungsmaschine und Strömungsmaschine mit einem solchen Rotor
FR3126014A1 (fr) * 2021-08-05 2023-02-10 Safran Aircraft Engines Distributeur pour turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215435A (en) * 1991-10-28 1993-06-01 General Electric Company Angled cooling air bypass slots in honeycomb seals
EP1614862A1 (fr) * 2004-07-07 2006-01-11 Hitachi, Ltd. Turbine à gas et méthode de refroidissement et d' étanchement d'une turbine à gas
FR2928963A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur de turbine pour une turbomachine.
US20110052380A1 (en) * 2008-03-19 2011-03-03 Snecma Sectored distributor for turbomachine
DE102010055435A1 (de) * 2010-12-21 2012-06-21 Rolls-Royce Deutschland Ltd & Co Kg Innendeckband einer Gasturbine

Family Cites Families (4)

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US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
JP2004202544A (ja) * 2002-12-25 2004-07-22 Daido Steel Co Ltd 異形断面をもつ多角形環状体部品の製造方法
DE102004034312A1 (de) * 2004-07-15 2006-02-02 Mtu Aero Engines Gmbh Dichtungsanordnung und Verfahren zur Herstellung eines Dichtkörpers für eine Dichtungsanordnung
US9080449B2 (en) * 2011-08-16 2015-07-14 United Technologies Corporation Gas turbine engine seal assembly having flow-through tube

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215435A (en) * 1991-10-28 1993-06-01 General Electric Company Angled cooling air bypass slots in honeycomb seals
EP1614862A1 (fr) * 2004-07-07 2006-01-11 Hitachi, Ltd. Turbine à gas et méthode de refroidissement et d' étanchement d'une turbine à gas
FR2928963A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur de turbine pour une turbomachine.
US20110052380A1 (en) * 2008-03-19 2011-03-03 Snecma Sectored distributor for turbomachine
DE102010055435A1 (de) * 2010-12-21 2012-06-21 Rolls-Royce Deutschland Ltd & Co Kg Innendeckband einer Gasturbine

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2960555A1 (fr) * 2014-06-25 2015-12-30 MTU Aero Engines GmbH Système de joint à brosse pour sceller un intervalle entre les éléments d'une turbomachine qui peuvent être déplacés les uns par rapport aux autres
US10094230B2 (en) 2014-06-25 2018-10-09 MTU Aero Engines AG Brush seal system for sealing a clearance between components of a turbo engine that are movable in relation to one another
FR3039589A1 (fr) * 2015-07-28 2017-02-03 Snecma Etage de turbomachine, en particulier de turbine basse-pression
EP3208426A1 (fr) 2016-02-18 2017-08-23 MTU Aero Engines GmbH Segment d'aube directrice pour turbomachine
DE102016202519A1 (de) 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine
US10895162B2 (en) 2016-02-18 2021-01-19 MTU Aero Engines AG Guide vane segment for a turbomachine
US10808561B2 (en) 2017-05-29 2020-10-20 MTU Aero Engines AG Seal arrangement for a turbomachine, method for manufacturing a seal arrangement and turbomachine
EP3409897A1 (fr) * 2017-05-29 2018-12-05 MTU Aero Engines GmbH Agencement d'étanchéité pour une turbomachine, méthode de fabrication de l'agencement d'étanchéité et turbomachine
EP3483399A1 (fr) * 2017-11-09 2019-05-15 MTU Aero Engines GmbH Dispositif d'étanchéité pour une turbomachine, procédé de fabrication d'un dispositif d'étanchéité et turbomachine
US10865651B2 (en) 2017-11-09 2020-12-15 MTU Aero Engines AG Sealing assembly for a fluid kinetic machine, method for producing a sealing assembly as well as fluid kinetic machine
EP3517734A1 (fr) * 2018-01-29 2019-07-31 MTU Aero Engines GmbH Module d'étanchéité pour une turbomachine
US10844737B2 (en) 2018-01-29 2020-11-24 MTU Aero Engines AG Additively manufactured module for a turbomachine
IT201900013218A1 (it) * 2019-07-29 2021-01-29 Ge Avio Srl Fascia interna per motore a turbina.
WO2021186135A1 (fr) * 2020-03-19 2021-09-23 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une piece annulaire de serrage
FR3108358A1 (fr) * 2020-03-19 2021-09-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une pièce annulaire de serrage.
FR3113298A1 (fr) * 2020-08-10 2022-02-11 Safran Aircraft Engines Porte-abradable d’un distributeur basse pression comprenant une unique tôle
EP4345251A1 (fr) * 2022-09-22 2024-04-03 MTU Aero Engines AG Module pour une turbomachine

Also Published As

Publication number Publication date
US9856736B2 (en) 2018-01-02
EP2722486B1 (fr) 2016-12-07
US20140105725A1 (en) 2014-04-17

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