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RU2014141355A - HEAT SHIELD ELEMENT FOR COMPRESSOR AIR CIRCUIT AROUND COMBUSTION CHAMBER - Google Patents

HEAT SHIELD ELEMENT FOR COMPRESSOR AIR CIRCUIT AROUND COMBUSTION CHAMBER Download PDF

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Publication number
RU2014141355A
RU2014141355A RU2014141355A RU2014141355A RU2014141355A RU 2014141355 A RU2014141355 A RU 2014141355A RU 2014141355 A RU2014141355 A RU 2014141355A RU 2014141355 A RU2014141355 A RU 2014141355A RU 2014141355 A RU2014141355 A RU 2014141355A
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RU
Russia
Prior art keywords
wall
combustion chamber
height
heat shield
extends
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RU2014141355A
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Russian (ru)
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RU2622590C2 (en
Inventor
Франсуа БЕНКЛЕР
Томас БРАНДЕНБУРГ
Ольга ДАЙСС
Томас ГРИБ
Марко ЛИНК
Николас САВИЛИУС
Даниель ФОГТМАНН
Ян ВИЛКЕС
Original Assignee
Сименс Акциенгезелльшафт
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Publication of RU2014141355A publication Critical patent/RU2014141355A/en
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Publication of RU2622590C2 publication Critical patent/RU2622590C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1. Элемент (14) теплозащитного экрана, предназначенный преимущественно для облицовки стенки (13) камеры сгорания, включающий в себя первую стенку (17) с горячей стороной (18), расположенной с возможностью подачи на нее горячей среды, с противолежащей горячей стороне (18) холодной стороной (19) и с круговой кромкой (24), которая проходит по первой боковой стороне (20), второй боковой стороне (21) и третьей боковой стороне (22) первой стенки (17) за пределы холодной стороны (19), в основном, до первой высоты (25), отличающийся тем, что круговая кромка (24) проходит на четвертой боковой стороне (23) до второй высоты (26), которая меньше первой высоты (25), при этом в основном, на второй высоте (26) вторая стенка (27) противолежит холодной стороне (19) и проходит по ширине четвертой боковой стороны (23) от четвертой боковой стороны (23) через часть длины смежных с четвертой боковой стороной (23) боковых сторон (20, 22), причем вторая стенка (27) на своем обращенном от четвертой боковой стороны (23) конце (28) имеет кромку (29), проходящую до первой высоты (25).2. Элемент (14) по п. 1, отличающийся тем, что он состоит из устойчивого к высоким температурам металла или из устойчивого к высоким температурам металлического сплава.3. Элемент (14) по п. 1 или 2, отличающийся тем, что он имеет большое количество расположенных по круговой кромке (24) отверстий (30) для охлаждающего воздуха.4. Элемент (14) по п. 3, отличающийся тем, что отверстия (30) для охлаждающего воздуха расположены, по меньшей мере, в зоне второй стенки (27) между первой стенкой (26) и второй стенкой (27).5. Элемент (14) по любому из пп. 1, 2 или 4, отличающийся тем, что он включает в себя дополнительно крепежное отверстие (31), окантовка (32) которого проходит от первой стенки (17) до первой высоты (25).6. Элемент (14) по п. 3, отличающийся тем, что он включает в себя дополнительно 1. The element (14) of the heat shield, designed primarily for facing the wall (13) of the combustion chamber, including the first wall (17) with a hot side (18) located with the possibility of supplying hot medium to it, with an opposite hot side (18 ) the cold side (19) and with a circular edge (24), which extends along the first side (20), the second side (21) and the third side (22) of the first wall (17) outside the cold side (19), basically to the first height (25), characterized in that the circular edge (24) extends over the solid side (23) to a second height (26), which is smaller than the first height (25), while basically, at the second height (26), the second wall (27) is opposite the cold side (19) and extends across the width of the fourth side (23) from the fourth lateral side (23) through a portion of the length of the lateral sides (20, 22) adjacent to the fourth lateral side (23), and the second wall (27) at its end (28) facing away from the fourth lateral side (23) has edge (29) extending to the first height (25) .2. Element (14) according to claim 1, characterized in that it consists of a metal resistant to high temperatures or from a metal alloy resistant to high temperatures. 3. Element (14) according to claim 1 or 2, characterized in that it has a large number of openings (30) located on the circular edge (24) for cooling air. 4. Element (14) according to claim 3, characterized in that the holes (30) for cooling air are located at least in the area of the second wall (27) between the first wall (26) and the second wall (27) .5. Element (14) according to any one of paragraphs. 1, 2 or 4, characterized in that it further includes a mounting hole (31), the edging (32) of which extends from the first wall (17) to the first height (25) .6. Element (14) according to claim 3, characterized in that it further includes

Claims (12)

1. Элемент (14) теплозащитного экрана, предназначенный преимущественно для облицовки стенки (13) камеры сгорания, включающий в себя первую стенку (17) с горячей стороной (18), расположенной с возможностью подачи на нее горячей среды, с противолежащей горячей стороне (18) холодной стороной (19) и с круговой кромкой (24), которая проходит по первой боковой стороне (20), второй боковой стороне (21) и третьей боковой стороне (22) первой стенки (17) за пределы холодной стороны (19), в основном, до первой высоты (25), отличающийся тем, что круговая кромка (24) проходит на четвертой боковой стороне (23) до второй высоты (26), которая меньше первой высоты (25), при этом в основном, на второй высоте (26) вторая стенка (27) противолежит холодной стороне (19) и проходит по ширине четвертой боковой стороны (23) от четвертой боковой стороны (23) через часть длины смежных с четвертой боковой стороной (23) боковых сторон (20, 22), причем вторая стенка (27) на своем обращенном от четвертой боковой стороны (23) конце (28) имеет кромку (29), проходящую до первой высоты (25).1. The element (14) of the heat shield, designed primarily for facing the wall (13) of the combustion chamber, including the first wall (17) with a hot side (18) located with the possibility of supplying hot medium to it, with an opposite hot side (18 ) the cold side (19) and with a circular edge (24), which extends along the first side (20), the second side (21) and the third side (22) of the first wall (17) outside the cold side (19), basically to the first height (25), characterized in that the circular edge (24) extends over the solid side (23) to a second height (26), which is smaller than the first height (25), while basically, at the second height (26), the second wall (27) is opposite the cold side (19) and extends across the width of the fourth side (23) from the fourth lateral side (23) through a portion of the length of the lateral sides (20, 22) adjacent to the fourth lateral side (23), and the second wall (27) at its end (28) facing away from the fourth lateral side (23) has an edge (29) extending to a first height (25). 2. Элемент (14) по п. 1, отличающийся тем, что он состоит из устойчивого к высоким температурам металла или из устойчивого к высоким температурам металлического сплава.2. Element (14) according to claim 1, characterized in that it consists of a metal resistant to high temperatures or from a metal alloy resistant to high temperatures. 3. Элемент (14) по п. 1 или 2, отличающийся тем, что он имеет большое количество расположенных по круговой кромке (24) отверстий (30) для охлаждающего воздуха.3. Element (14) according to claim 1 or 2, characterized in that it has a large number of holes (30) located on the circular edge (24) for cooling air. 4. Элемент (14) по п. 3, отличающийся тем, что отверстия (30) для охлаждающего воздуха расположены, по меньшей мере, в зоне второй стенки (27) между первой стенкой (26) и второй стенкой (27).4. Element (14) according to claim 3, characterized in that the holes (30) for cooling air are located at least in the region of the second wall (27) between the first wall (26) and the second wall (27). 5. Элемент (14) по любому из пп. 1, 2 или 4, отличающийся тем, что он включает в себя дополнительно крепежное отверстие (31), окантовка (32) которого проходит от первой стенки (17) до первой высоты (25).5. Element (14) according to any one of paragraphs. 1, 2 or 4, characterized in that it further includes a mounting hole (31), the edging (32) of which extends from the first wall (17) to the first height (25). 6. Элемент (14) по п. 3, отличающийся тем, что он включает в себя дополнительно крепежное отверстие (31), окантовка (32) которого проходит от первой стенки (17) до первой высоты (25).6. Element (14) according to claim 3, characterized in that it further includes a mounting hole (31), the edging (32) of which extends from the first wall (17) to the first height (25). 7. Камера (1) сгорания, имеющая стенку с одним концом со стороны горелки и с одним концом (8) со стороны турбины, причем стенка (13) камеры сгорания имеет окружное направление, включающая в себя большое количество элементов (14) теплозащитного экрана согласно любому из пп. 1-5, которые расположены на конце (8) со стороны турбины стенки (13) камеры сгорания с образованием двух камер (15, 16) в окружном направлении, причем четвертая боковая сторона (23) ориентирована к концу (8) со стороны турбины.7. The combustion chamber (1) having a wall with one end on the side of the burner and with one end (8) on the side of the turbine, the wall (13) of the combustion chamber having a circumferential direction, including a large number of elements (14) of a heat shield according to any of paragraphs. 1-5, which are located at the end (8) of the turbine side of the wall (13) of the combustion chamber with the formation of two chambers (15, 16) in the circumferential direction, with the fourth side (23) oriented towards the end (8) of the turbine side. 8. Камера (1) сгорания по п. 7, причем элементы (14) теплозащитного экрана закреплены на стенке (13) камеры сгорания посредством крепежных болтов.8. The combustion chamber (1) according to claim 7, wherein the elements (14) of the heat shield are fixed to the wall (13) of the combustion chamber by means of fixing bolts. 9. Камера (1) сгорания по п. 7 или 8, причем в стенке (13) камеры сгорания выполнены отверстия, с возможностью подачи охлаждающего средства к элементам (14) теплозащитного экрана.9. The combustion chamber (1) according to claim 7 or 8, moreover, holes are made in the wall (13) of the combustion chamber, with the possibility of supplying coolant to the heat shield elements (14). 10. Камера (1) сгорания по п. 7 или 8, причем в стенке (13) камеры сгорания расположен, по меньшей мере, один подводящий канал для каждого элемента (14) теплозащитного экрана в зоне, соответственно, второй стенки (27), который входит в, по меньшей мере, частично окружающую камеру (1) сгорания сборную емкость (36).10. The combustion chamber (1) according to claim 7 or 8, wherein at least one supply channel for each element (14) of the heat shield in the area of the second wall (27), respectively, is located in the wall (13) of the combustion chamber, which is included in at least partially surrounding the combustion chamber (1) of the collection tank (36). 11. Камера (1) сгорания по п. 9, причем в стенке (13) камеры сгорания расположен, по меньшей мере, один подводящий канал для каждого элемента (14) теплозащитного экрана в зоне, соответственно, второй стенки (27), который входит в, по меньшей мере, частично окружающую камеру (1) сгорания сборную емкость (36).11. The combustion chamber (1) according to claim 9, wherein at least one supply channel for each element (14) of the heat shield in the area of the second wall (27), which enters, is located in the wall (13) of the combustion chamber in at least partially surrounding the combustion chamber (1) the collection tank (36). 12. Газовая турбина с камерой (1) сгорания по любому из пп. 7-11, причем газовая турбина включает в себя, по меньшей мере, один заборный элемент (33) для воздуха компрессора, который, по меньшей мере, через один трубопровод (35) с клапаном (34) входит в сборную емкость (36). 12. Gas turbine with a combustion chamber (1) according to any one of paragraphs. 7-11, and the gas turbine includes at least one intake element (33) for compressor air, which, through at least one pipe (35) with valve (34) enters the collection tank (36).
RU2014141355A 2012-03-15 2013-03-12 Heat shield element for the compressor air pass by around the combustion chamber RU2622590C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012204103.6 2012-03-15
DE102012204103A DE102012204103A1 (en) 2012-03-15 2012-03-15 Heat shield element for a compressor air bypass around the combustion chamber
PCT/EP2013/055007 WO2013135702A2 (en) 2012-03-15 2013-03-12 Heat-shield element for a compressor-air bypass around the combustion chamber

Publications (2)

Publication Number Publication Date
RU2014141355A true RU2014141355A (en) 2016-05-10
RU2622590C2 RU2622590C2 (en) 2017-06-16

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RU2014141355A RU2622590C2 (en) 2012-03-15 2013-03-12 Heat shield element for the compressor air pass by around the combustion chamber

Country Status (6)

Country Link
US (1) US20150027128A1 (en)
EP (1) EP2809994B1 (en)
CN (1) CN104169648B (en)
DE (1) DE102012204103A1 (en)
RU (1) RU2622590C2 (en)
WO (1) WO2013135702A2 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012204162A1 (en) * 2012-03-16 2013-09-19 Siemens Aktiengesellschaft Ring combustor bypass
US10408451B2 (en) 2013-09-11 2019-09-10 Siemens Aktiengesellschaft Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
US10088161B2 (en) * 2013-12-19 2018-10-02 United Technologies Corporation Gas turbine engine wall assembly with circumferential rail stud architecture
US10645404B2 (en) 2014-03-24 2020-05-05 Qualcomm Incorporated Generic use of HEVC SEI messages for multi-layer codecs
DE102014206018A1 (en) * 2014-03-31 2015-10-01 Siemens Aktiengesellschaft Gas turbine plant
DE102014214981B3 (en) * 2014-07-30 2015-12-24 Siemens Aktiengesellschaft Side-coated heat shield element with impingement cooling on open spaces
DE102014221225A1 (en) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Heat shield element and method for its production
DE102015202097A1 (en) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ring combustion chamber with bypass segment
CN104654359B (en) * 2015-02-13 2017-12-19 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of flow guiding structure of combustion chamber premixer fuel nozzle
CN104654358B (en) * 2015-02-13 2017-09-15 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of combustion chamber premixer fuel nozzle with flow guiding structure
DE102015205975A1 (en) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs heat shield element
DE102015215207A1 (en) * 2015-08-10 2017-02-16 Siemens Aktiengesellschaft Combustion chamber for a gas turbine and heat shield element for lining such a combustion chamber
EP3320266B1 (en) * 2015-08-27 2019-03-20 Siemens Aktiengesellschaft Metal heat shield element with an optimized cooling air function
DE102015224524A1 (en) * 2015-12-08 2017-06-08 Siemens Aktiengesellschaft Combustion chamber with resonators
US10237339B2 (en) * 2016-08-19 2019-03-19 Microsoft Technology Licensing, Llc Statistical resource balancing of constrained microservices in cloud PAAS environments
DE102018204453B4 (en) 2018-03-22 2024-01-18 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
DE102020116245B4 (en) * 2020-06-19 2024-03-07 Man Energy Solutions Se Gas turbine assembly with combustion chamber air bypass

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2312654A1 (en) * 1975-05-28 1976-12-24 Snecma COMBUSTION CHAMBERS IMPROVEMENTS FOR GAS TURBINE ENGINES
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
GB9018014D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
DE19730751A1 (en) * 1996-07-24 1998-01-29 Siemens Ag Ceramic component for heat-protective cladding
FR2752916B1 (en) * 1996-09-05 1998-10-02 Snecma THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER
US6358041B1 (en) * 2000-04-21 2002-03-19 Eastman Chemical Company Threaded heat shield for burner nozzle face
JP2002317650A (en) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd Gas turbine combustor
EP1284390A1 (en) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Thermal shield for a component carrying hot gases, especially for structural components of gas turbines
JP2003201863A (en) * 2001-10-29 2003-07-18 Mitsubishi Heavy Ind Ltd Combustor and gas turbine with it
RU2243448C2 (en) * 2002-12-18 2004-12-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Combustion chamber
EP1482246A1 (en) * 2003-05-30 2004-12-01 Siemens Aktiengesellschaft Combustion chamber
EP1486730A1 (en) * 2003-06-11 2004-12-15 Siemens Aktiengesellschaft Heatshield Element
EP1507116A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber
US7363763B2 (en) * 2003-10-23 2008-04-29 United Technologies Corporation Combustor
GB0425794D0 (en) * 2004-11-24 2004-12-22 Rolls Royce Plc Acoustic damper
EP1715249A1 (en) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Heat Shield Element and Combustion Chamber with a Heat Shield
WO2009053417A2 (en) * 2007-10-26 2009-04-30 Siemens Aktiengesellschaft Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring
EP2182285A1 (en) * 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Burner insert for a gas turbine combustion chamber and gas turbine
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
US9416970B2 (en) * 2009-11-30 2016-08-16 United Technologies Corporation Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel
US8499566B2 (en) * 2010-08-12 2013-08-06 General Electric Company Combustor liner cooling system
EP2960436B1 (en) * 2014-06-27 2017-08-09 Ansaldo Energia Switzerland AG Cooling structure for a transition piece of a gas turbine
DE102015205975A1 (en) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs heat shield element

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CN104169648B (en) 2016-03-02
RU2622590C2 (en) 2017-06-16
US20150027128A1 (en) 2015-01-29
WO2013135702A2 (en) 2013-09-19
EP2809994B1 (en) 2016-05-04
WO2013135702A3 (en) 2013-11-14
CN104169648A (en) 2014-11-26
EP2809994A2 (en) 2014-12-10
DE102012204103A1 (en) 2013-09-19

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