EP2832872B1 - Highly temperature resistant lightweight construction alloy made of NiAl - Google Patents
Highly temperature resistant lightweight construction alloy made of NiAl Download PDFInfo
- Publication number
- EP2832872B1 EP2832872B1 EP14176757.4A EP14176757A EP2832872B1 EP 2832872 B1 EP2832872 B1 EP 2832872B1 EP 14176757 A EP14176757 A EP 14176757A EP 2832872 B1 EP2832872 B1 EP 2832872B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- nial
- material according
- material comprises
- component
- temperature resistant
- 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.)
- Not-in-force
Links
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
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/007—Alloys based on nickel or cobalt with a light metal (alkali metal Li, Na, K, Rb, Cs; earth alkali metal Be, Mg, Ca, Sr, Ba, Al Ga, Ge, Ti) or B, Si, Zr, Hf, Sc, Y, lanthanides, actinides, as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/177—Ni - Si alloys
Definitions
- the present invention relates to a material which can be used in particular for applications in which a high heat resistance is required. Moreover, the present invention relates to a component of a turbomachine, in particular of an aircraft engine, of a corresponding material.
- turbomachines such as stationary gas turbines or aircraft engines
- certain components such as blades of the turbine area and in particular the low-pressure turbine area operating conditions that place high demands on the corresponding materials prevail.
- the materials have to endure high temperatures in the range of, for example, 800.degree. C. to 1200.degree. C. and, in addition, have to endure high mechanical loads, such as, for example, moving blades, which are moved at high rotational speeds.
- high operating temperatures and high mechanical forces places special demands on the heat resistance and creep resistance of corresponding materials.
- the nickel base superalloys currently used in such applications such as MAR M 247 (trade name of Martin Marietta), IN 100 (trade name of Special Metals) or CMSX 4 (trade name of Cannon Muskegon), have the disadvantage that the specific weight is relatively high, so that corresponding components have a high weight, which is disadvantageous for applications in aircraft engine construction.
- a suitable material is nickel - aluminum alloys based on the intermetallic compound NiAl. Examples are in the US 5,935,349 as well as in the scientific articles B. Zeumer, G.Sauthoff, Intermetallic NiAl-Ta alloys with strengthening Laves phase for high-temperature applcations I. Basic properties, Intermetallics 5 (1997) 563-577 and B. Zeumer, G. Sauthoff, Deformation behavior of intermetallic NiAlTa alloys with strengthening Laves phase for high-temperature applications II. Effects of alloying with Nb and other elements, Intermetallics 5 (1997) 641-649 , given. The alloys described therein have up to 50 at.% Ni and ternary Laves phases.
- a material having the features of the preamble of claim 1 is known from DE 25 21 563 A1 known.
- the material should be simple and easy to manufacture and process.
- the invention is based on the recognition that the Ni-Al alloys described in the prior art have a property profile for high-temperature applications and in particular for applications in the field of turbomachines, such as aircraft engines. can be further improved if the nickel content is increased over a proportion of 50 at.% Ni. Accordingly, a material is proposed which comprises more than 50 at.% Ni and ternary Laves phases based on intermetallic nickel aluminides.
- the intermetallic nickel aluminides can be formed by NiAl and / or Ni 3 Al, wherein the ternary Laves phases can be formed on the basis of Ni, Al and Ta and / or Nb.
- the material may comprise ternary Laves phases in the form of NiAlTa, NiAlNb and / or NiAl (Ta, Nb), wherein the components tantalum and niobium may be mixed in the ternary Laves phase NiAl (Ta, Nb) and, since tantalum and niobium can replace each other, the respective proportions of tantalum and niobium can vary in a wide range of different compositions.
- the ternary phases based on Ni, Al and Ta and / or Nb provide a corresponding increase in the strength and creep resistance of the material due to the presence of the corresponding grain boundaries of the NiAl crystallites and / or the Ni 3 Al crystallites.
- Such ternary Laves phases may be in the form of the hexagonal C14 structure while NiAl is in the B2 structure.
- the material has 50.1 to 70 at.% Ni, preferably 51 at.% To 60 at.% Ni, and furthermore and 0.5 at.% To 10 at.% Ta, in particular 1 at.% To 5 at.% Ta and / or 0.5 at.% to 10 at.% Nb, in particular 1 at.% to 5 at.% Nb, the remainder being formed by aluminum. Tantalum and niobium can be interchanged in the material so that the sum of tantalum and niobium can be in the range of 0.5 at.% To 10 at.% And especially 1 at.% To 5 at.%.
- components from turbomachines and preferably from aircraft engines may be formed from or contain the corresponding material.
- the material according to the invention for runners or guide vanes in the turbine of a turbomachine, in particular the low-pressure turbine.
- a material with 60 at.% Nickel, 2.5 at.% Tantalum and 2.5 at.% Niobium and 35 at.% Aluminum can be used, which through the structure formation with NiAl and Ni 3 Al and ternary Laves - phases At the grain boundaries of the NiAl and Ni 3 Al grains, with low specific gravity, it has high heat resistance and creep resistance.
Description
Die vorliegende Erfindung betrifft einen Werkstoff, der insbesondere für Anwendungen eingesetzt werden kann, bei denen eine hohe Warmfestigkeit erforderlich ist. Darüber hinaus betrifft die vorliegende Erfindung ein Bauteil einer Strömungsmaschine, insbesondere eines Flugzeugtriebwerks, aus einem entsprechenden Werkstoff.The present invention relates to a material which can be used in particular for applications in which a high heat resistance is required. Moreover, the present invention relates to a component of a turbomachine, in particular of an aircraft engine, of a corresponding material.
In Strömungsmaschinen, wie stationären Gasturbinen oder Flugzeugtriebwerken, herrschen für bestimmte Bauteile, wie beispielsweise Laufschaufeln des Turbinenbereichs und insbesondere des Niederdruckturbinenbereichs Einsatzbedingungen, die hohe Anforderungen an die entsprechenden Werkstoffe stellen. So müssen die Werkstoffe einerseits hohe Temperaturen im Bereich von beispielsweise 800°C bis 1200 °C aushalten und müssen zusätzlich hohe mechanische Belastungen ertragen, wie beispielsweise Laufschaufeln, die mit hohen Drehgeschwindigkeiten bewegt werden. Durch die Kombination von hohen Betriebstemperaturen und hohen mechanischen Kräften werden besondere Anforderungen an die Warmfestigkeit und Kriechbeständigkeit entsprechender Werkstoffe gestellt.In turbomachines, such as stationary gas turbines or aircraft engines, for certain components, such as blades of the turbine area and in particular the low-pressure turbine area operating conditions that place high demands on the corresponding materials prevail. On the one hand, the materials have to endure high temperatures in the range of, for example, 800.degree. C. to 1200.degree. C. and, in addition, have to endure high mechanical loads, such as, for example, moving blades, which are moved at high rotational speeds. The combination of high operating temperatures and high mechanical forces places special demands on the heat resistance and creep resistance of corresponding materials.
Die derzeit bei entsprechenden Anwendungen verwendeten Nickelbasis - Superlegierungen, wie beispielsweise MAR M 247 (Handelsname der Firma Martin Marietta), IN 100 (Handelsname der Firma Special Metals) oder CMSX 4 (Handelsname der Firma Cannon Muskegon), weisen jedoch den Nachteil auf, dass das spezifische Gewicht relativ hoch ist, sodass entsprechende Bauteile ein hohes Gewicht aufweisen, was für Anwendungen im Flugzeugtriebwerksbau nachteilig ist.However, the nickel base superalloys currently used in such applications, such as MAR M 247 (trade name of Martin Marietta), IN 100 (trade name of Special Metals) or CMSX 4 (trade name of Cannon Muskegon), have the disadvantage that the specific weight is relatively high, so that corresponding components have a high weight, which is disadvantageous for applications in aircraft engine construction.
Darüber hinaus können bei diesen bekannten Werkstoffen weitere Steigerungen der Leistungsfähigkeit der Strömungsmaschinen durch eine geeignete Erhöhung der Drehzahlen und/oder Erhöhung der Betriebstemperatur nur dadurch erzielt werden, dass entweder eine Reduzierung der Bauteillebensdauer oder eine Erhöhung des Bauteilgewichts in Kauf genommen werden oder eine separate Bauteilkühlung vorgesehen wird. All diese Maßnahmen erhöhen jedoch den entsprechenden Aufwand und die Kosten.In addition, with these known materials further increases in the performance of turbomachines by a suitable increase in rotational speeds and / or increasing the operating temperature can only be achieved by either a reduction in the component life or an increase in the weight of the component to be accepted or provided a separate component cooling becomes. However, all of these measures increase the expense and expense.
Entsprechend ist bereits versucht worden, durch andere Materialien einerseits Gewicht einzusparen und andererseits die Werkstoffeigenschaften hinsichtlich Festigkeit, Kriechbeständigkeit und Warmfestigkeit zu steigern. Als potentielle Materialien sind hierfür intermetallische Verbindungen in Betracht gezogen worden, die aufgrund ihrer speziellen Bindungseigenschaften eine hohe Festigkeit aufweisen und aus chemischen Elementen gebildet werden können, die ein niedriges atomares Gewicht aufweisen.Accordingly, it has already been attempted to save weight by other materials on the one hand and on the other hand, the material properties in terms of strength, creep resistance and to increase heat resistance. As potential materials, there have been considered intermetallic compounds which, because of their specific bonding properties, have high strength and can be formed of chemical elements having a low atomic weight.
Ein geeignet erscheinendes Material sind Nickel - Aluminium - Legierungen auf Basis der intermetallischen Verbindung NiAl. Beispiele hierfür sind in der
Ein Werkstoff mit den Merkmalen des Oberbegriffs von Anspruch 1 ist aus der
Obwohl damit bereits gute Ergebnisse hinsichtlich der Warmfestigkeit und Kriechbeständigkeit erzielt worden sind, besteht ein weiterer Bedarf, Werkstoffe bereitzustellen, die in den Bereichen der Kriechbeständigkeit und Warmfestigkeit sowie des spezifischen Gewichts für den Einsatz im Flugzeugtriebwerksbau vorteilhaft sind.Although good results have already been achieved with respect to heat resistance and creep resistance, there is a further need to provide materials which are advantageous in the areas of creep resistance and heat resistance as well as specific gravity for use in aircraft engine construction.
Es ist deshalb Aufgabe der vorliegenden Erfindung, einen Werkstoff bereitzustellen, der für Hochtemperaturanwendungen durch eine hohe Warmfestigkeit und Kriechbeständigkeit geeignet ist und gleichzeitig ein niedriges spezifisches Gewicht aufweist, um das Bauteilgewicht für Bauteile aus diesem Werkstoff niedrig zu halten bzw. zu senken. Darüber hinaus soll der Werkstoff einfach und gut herstellbar und verarbeitbar sein.It is therefore an object of the present invention to provide a material which is suitable for high temperature applications by a high heat resistance and creep resistance and at the same time has a low specific weight in order to keep the component weight for components made of this material low or lower. In addition, the material should be simple and easy to manufacture and process.
Diese Aufgabe wird gelöst durch einen Werkstoff mit den Merkmalen des Anspruchs 1 sowie ein Bauteil mit den Merkmalen des Anspruchs 8. Vorteilhafte Ausgestaltungen der Erfindung sind Gegenstand der abhängigen Ansprüche.This object is achieved by a material having the features of claim 1 and a component having the features of claim 8. Advantageous embodiments of the invention are the subject of the dependent claims.
Die Erfindung geht aus von der Erkenntnis, dass die im Stand der Technik beschriebenen Ni-Al-Legierungen hinsichtlich ihres Eigenschaftsprofils für Hochtemperaturanwendungen und insbesondere für Anwendungen im Bereich von Strömungsmaschinen, wie Flugzeugtriebwerken, weiter verbessert werden können, wenn der Nickelanteil über einen Anteil von 50 at.% Ni erhöht wird. Entsprechend wird ein Werkstoff vorgeschlagen, der auf Basis von intermetallischen Nickelaluminiden mehr als 50 at.% Ni und ternäre Laves - Phasen umfasst.The invention is based on the recognition that the Ni-Al alloys described in the prior art have a property profile for high-temperature applications and in particular for applications in the field of turbomachines, such as aircraft engines. can be further improved if the nickel content is increased over a proportion of 50 at.% Ni. Accordingly, a material is proposed which comprises more than 50 at.% Ni and ternary Laves phases based on intermetallic nickel aluminides.
Die intermetallischen Nickelaluminide können durch NiAl und/oder Ni3Al gebildet sein, wobei die ternären Laves - Phasen auf Basis von Ni, Al und Ta und/oder Nb gebildet sein können.The intermetallic nickel aluminides can be formed by NiAl and / or Ni 3 Al, wherein the ternary Laves phases can be formed on the basis of Ni, Al and Ta and / or Nb.
Insbesondere kann der Werkstoff ternäre Laves - Phasen in Form von NiAlTa, NiAlNb und/oder NiAl(Ta,Nb) umfassen, wobei bei der ternären Laves - Phase NiAl(Ta,Nb) die Bestandteile Tantal und Niob gemischt vorliegen können und, da Tantal und Niob sich gegenseitig ersetzen können, die jeweiligen Anteile von Tantal und Niob in einem großen Bereich von unterschiedlichen Zusammensetzungen variieren können.In particular, the material may comprise ternary Laves phases in the form of NiAlTa, NiAlNb and / or NiAl (Ta, Nb), wherein the components tantalum and niobium may be mixed in the ternary Laves phase NiAl (Ta, Nb) and, since tantalum and niobium can replace each other, the respective proportions of tantalum and niobium can vary in a wide range of different compositions.
Die ternären Phasen auf Basis von Ni, Al und Ta und/oder Nb, sorgen durch das Vorhandensein an den entsprechenden Korngrenzen der NiAl - Kristallite und/oder der Ni3Al - Kristallite für eine entsprechende Erhöhung der Festigkeit und der Kriechbeständigkeit des Werkstoffs. Derartige ternäre Laves - Phasen können in Form der hexagonalen C14 -Struktur ausgebildet sein, während NiAl in der B2 - Struktur vorliegt.The ternary phases based on Ni, Al and Ta and / or Nb provide a corresponding increase in the strength and creep resistance of the material due to the presence of the corresponding grain boundaries of the NiAl crystallites and / or the Ni 3 Al crystallites. Such ternary Laves phases may be in the form of the hexagonal C14 structure while NiAl is in the B2 structure.
Erfindungsgemäß weist der Werkstoff 50,1 bis 70 at.% Ni, vorzugsweise 51 at.% bis 60 at.% Ni auf, sowie ferner und 0,5 at.% bis 10 at.% Ta, insbesondere 1 at.% bis 5 at.% Ta und/oder 0,5 at.% bis 10 at.% Nb, insbesondere 1 at.% bis 5 at.% Nb, wobei der Rest durch Aluminium gebildet wird. Tantal und Niob können in dem Werkstoff gegenseitig ausgetauscht werden, sodass die Summe aus Tantal und Niob im Bereich von 0,5 at.% bis 10 at.% und insbesondere 1 at.% bis 5 at.% liegen kann.According to the invention, the material has 50.1 to 70 at.% Ni, preferably 51 at.% To 60 at.% Ni, and furthermore and 0.5 at.% To 10 at.% Ta, in particular 1 at.% To 5 at.% Ta and / or 0.5 at.% to 10 at.% Nb, in particular 1 at.% to 5 at.% Nb, the remainder being formed by aluminum. Tantalum and niobium can be interchanged in the material so that the sum of tantalum and niobium can be in the range of 0.5 at.% To 10 at.% And especially 1 at.% To 5 at.%.
Insbesondere Bauteile aus Strömungsmaschinen und vorzugsweise von Flugzeugtriebwerken können aus dem entsprechenden Werkstoff gebildet sein oder diesen enthalten. Vor allem bietet es sich an, den erfindungsgemäßen Werkstoff für Lauf- oder Leitschaufeln in der Turbine einer Strömungsmaschine, insbesondere der Niederdruckturbine einzusetzen.In particular, components from turbomachines and preferably from aircraft engines may be formed from or contain the corresponding material. Above all, it makes sense to use the material according to the invention for runners or guide vanes in the turbine of a turbomachine, in particular the low-pressure turbine.
Beispielsweise kann ein Werkstoff mit 60 at.% Nickel, 2,5 at.% Tantal und 2,5 at.% Niob sowie 35 at.% Aluminium eingesetzt werden, welcher durch die Gefügeausbildung mit NiAl und Ni3Al sowie ternären Laves - Phasen an den Korngrenzen der NiAl - und Ni3Al - Körner bei niedrigem spezifischen Gewicht eine hohe Warmfestigkeit und Kriechbeständigkeit aufweist. For example, a material with 60 at.% Nickel, 2.5 at.% Tantalum and 2.5 at.% Niobium and 35 at.% Aluminum can be used, which through the structure formation with NiAl and Ni 3 Al and ternary Laves - phases At the grain boundaries of the NiAl and Ni 3 Al grains, with low specific gravity, it has high heat resistance and creep resistance.
Claims (9)
- A material for applications that require high heat-resistance, based on intermetallic nickel aluminides, wherein the material comprises more than 50 at.% nickel and ternary Laves phases,
characterised in that the material comprises
50.1 at.% to 70 at.% Ni and
0.5 at.% to 10 at.% Ta and/or 0.5 at.% to 10 at.% Nb,
and the remainder is formed by aluminium. - A material according to claim 1,
characterised in that
the material comprises NiAl and/or Ni3Al. - A material according to one of the preceding claims,
characterised in that
the material comprises ternary Laves phases based on Ni, Al and Ta and/or Nb, in particular NiAlTa, NiAlNb and/or NiAl(Ta,Nb). - A material according to one of the preceding claims,
characterised in that
the material comprises 51 at.% to 60 at.% Ni. - A material according to claim 4,
characterised in that
the material comprises 1 at.% to 5 at.% Ta and/or 1 at.% to 5 at.% Nb. - A material according to claim 4 or 5,
characterised in that
the sum of Ta and Nb in the material amounts to between 0.5 at.% to 10 at.%, in particular 1 at.% to 5 at.%. - A material according to one of the preceding claims,
characterized in that
the structure of the material comprises NiAl crystallites and/or Ni3Al crystallites, at the grain boundaries of which the ternary Laves phases are arranged. - A component of a turbo-machine, in particular an aircraft engine, which is formed from or comprises the material according to one of the preceding claims.
- A component according to claim 8,
characterised in that
the component is a rotor blade or guide blade in the turbine, in particular the low-pressure turbine of a turbo-machine.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102013214767.8A DE102013214767A1 (en) | 2013-07-29 | 2013-07-29 | Highly heat-resistant lightweight alloy of NiAl |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP2832872A2 EP2832872A2 (en) | 2015-02-04 |
| EP2832872A3 EP2832872A3 (en) | 2015-05-27 |
| EP2832872B1 true EP2832872B1 (en) | 2016-05-04 |
Family
ID=51211553
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP14176757.4A Not-in-force EP2832872B1 (en) | 2013-07-29 | 2014-07-11 | Highly temperature resistant lightweight construction alloy made of NiAl |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20150315919A1 (en) |
| EP (1) | EP2832872B1 (en) |
| DE (1) | DE102013214767A1 (en) |
| ES (1) | ES2581298T3 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102017109156A1 (en) | 2016-04-28 | 2017-11-02 | Hochschule Flensburg | High-temperature resistant material and its production |
| CN106011539B (en) * | 2016-05-31 | 2017-10-31 | 中国科学院兰州化学物理研究所 | Wide temperature range self-lubricating composite of a kind of nickel aluminium/vanadium oxide/silver and preparation method thereof |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2884688A (en) * | 1956-12-28 | 1959-05-05 | Borolite Corp | Sintered ni-al-zr compositions |
| DE2521563A1 (en) * | 1975-05-15 | 1976-12-02 | Heinz Dr Sprenger | Heat resisting nickel alloys using directional solidification - to ppte. lamellar intermetallic cpds. which increase strength |
| US5116691A (en) * | 1991-03-04 | 1992-05-26 | General Electric Company | Ductility microalloyed NiAl intermetallic compounds |
| DE4324960A1 (en) * | 1993-07-24 | 1995-01-26 | Mtu Muenchen Gmbh | Impeller of a turbomachine, in particular a turbine of a gas turbine engine |
| US5935349A (en) | 1994-05-21 | 1999-08-10 | Siemens Aktiengesellschaft | Intermetallic nickel-aluminum base alloy and material formed of the alloy |
| US5516380A (en) * | 1994-10-14 | 1996-05-14 | General Electric Company | NiAl intermetallic alloy and article with improved high temperature strength |
| US6153313A (en) * | 1998-10-06 | 2000-11-28 | General Electric Company | Nickel aluminide coating and coating systems formed therewith |
| CH699930A1 (en) * | 2008-11-26 | 2010-05-31 | Alstom Technology Ltd | High temperature and oxidation resistant material. |
-
2013
- 2013-07-29 DE DE102013214767.8A patent/DE102013214767A1/en not_active Withdrawn
-
2014
- 2014-07-11 ES ES14176757.4T patent/ES2581298T3/en active Active
- 2014-07-11 EP EP14176757.4A patent/EP2832872B1/en not_active Not-in-force
- 2014-07-28 US US14/341,955 patent/US20150315919A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| EP2832872A3 (en) | 2015-05-27 |
| DE102013214767A1 (en) | 2015-01-29 |
| ES2581298T3 (en) | 2016-09-05 |
| EP2832872A2 (en) | 2015-02-04 |
| US20150315919A1 (en) | 2015-11-05 |
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