EP2832872A2 - Highly temperature resistant lightweight construction alloy made of NiAl - Google Patents
Highly temperature resistant lightweight construction alloy made of NiAl Download PDFInfo
- Publication number
- EP2832872A2 EP2832872A2 EP20140176757 EP14176757A EP2832872A2 EP 2832872 A2 EP2832872 A2 EP 2832872A2 EP 20140176757 EP20140176757 EP 20140176757 EP 14176757 A EP14176757 A EP 14176757A EP 2832872 A2 EP2832872 A2 EP 2832872A2
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- Prior art keywords
- nial
- material according
- component
- nickel
- temperature resistant
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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
- F01D5/12—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 NiAl-Ta 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.
- 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 can be further improved in terms of their property profile for high temperature applications and in particular for applications in the field of turbomachines, such as aircraft engines, if the nickel content exceeds 50% at.% Ni is increased. 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, NiAINb and / or NiAl (Ta, Nb), wherein the constituents 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 may be 50.1 to 70 at.% Ni, preferably 51 at.% To 60 at.% Ni and 0.5 at.% To 10 at.% Ta, in particular 1 at.% To 5 at.% Ta exhibit.
- the material may have 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.%.
- the material may contain other alloying constituents, such as chromium, iron, hafnium, molybdenum, carbon, silicon, titanium, vanadium, zirconium, as well as impurities and accompanying elements.
- components from turbomachines and preferably from aircraft engines may be formed from or contain the corresponding material.
- the material according to the invention for running 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 by the structure formation with NiAl and Ni 3 Al, as well as ternary Laves phases at the grain boundaries of the NiAl and Ni 3 Al grains, has high heat resistance and creep resistance at a low specific gravity.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Die vorliegende Erfindung betrifft einen Werkstoff für Anwendungen, die eine hohe Warmfestigkeit erfordern, auf Basis von intermetallischen Nickelaluminiden, wobei der Werkstoff mehr als 50 at.% Nickel und ternäre Laves - Phasen umfasst, sowie ein daraus hergestelltes Bauteil einer Strömungsmaschine, insbesondere eines Flugzeugtriebwerks.The present invention relates to a material for applications which require high heat resistance, based on intermetallic nickel aluminides, the material comprising more than 50 at.% Nickel and ternary Laves phases, as well as a component of a turbomachine, in particular an aircraft engine, produced therefrom.
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
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 can be further improved in terms of their property profile for high temperature applications and in particular for applications in the field of turbomachines, such as aircraft engines, if the nickel content exceeds 50% at.% Ni is increased. 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, NiAINb 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, NiAINb and / or NiAl (Ta, Nb), wherein the constituents 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.
Insbesondere kann der Werkstoff 50,1 bis 70 at.% Ni, vorzugsweise 51 at.% bis 60 at.% Ni und 0,5 at.% bis 10 at.% Ta, insbesondere 1 at.% bis 5 at.% Ta aufweisen. Zusätzlich oder alternativ zu Tantal kann der Werkstoff 0,5 at.% bis 10 at.% Nb, insbesondere 1 at.% bis 5 at.% Nb aufweisen, 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.In particular, the material may be 50.1 to 70 at.% Ni, preferably 51 at.% To 60 at.% Ni and 0.5 at.% To 10 at.% Ta, in particular 1 at.% To 5 at.% Ta exhibit. In addition or as an alternative to tantalum, the material may have 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.%.
Der Werkstoff kann auf Kosten des Aluminiums weitere Legierungsbestandteile, wie beispielsweise Chrom, Eisen, Hafnium, Molybdän, Kohlenstoff, Silizium, Titan, Vanadium, Zirkon sowie Verunreinigungen und Begleitelemente enthalten.At the expense of aluminum, the material may contain other alloying constituents, such as chromium, iron, hafnium, molybdenum, carbon, silicon, titanium, vanadium, zirconium, as well as impurities and accompanying elements.
Insbesondere Bauteile aus Strömungsmaschinen und vorzugsweise von Flugzeugtriebwerken können aus dem entsprechenden Werkstoff gebildet sein oder diesen enthalten. Vorallem 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 running 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 by the structure formation with NiAl and Ni 3 Al, as well as ternary Laves phases at the grain boundaries of the NiAl and Ni 3 Al grains, has high heat resistance and creep resistance at a low specific gravity.
Claims (9)
dadurch gekennzeichnet, dass
der Werkstoff mehr als 50 at.% Nickel und ternäre Laves - Phasen umfasst.Material for high temperature applications based on intermetallic nickel aluminides,
characterized in that
the material comprises more than 50 at.% nickel and ternary Laves phases.
dadurch gekennzeichnet, dass
der Werkstoff NiAl und/oder Ni3Al umfasst.Material according to claim 1,
characterized in that
the material comprises NiAl and / or Ni 3 Al.
dadurch gekennzeichnet, dass
der Werkstoff ternäre Laves - Phasen auf Basis von Ni, Al und Ta und/oder Nb, insbesondere NiAlTa, NiAINb und/oder NiAl(Ta,Nb) umfasst.Material according to one of the preceding claims,
characterized in that
the material comprises ternary Laves phases based on Ni, Al and Ta and / or Nb, in particular NiAlTa, NiAINb and / or NiAl (Ta, Nb).
dadurch gekennzeichnet, dass
der Werkstoff 50,1 at.% bis 70 at.% Ni, vorzugsweise 51 at.% bis 60 at.% Ni 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 und Rest Aluminium umfasst.Material according to one of the preceding claims,
characterized in that
the material 50.1 at.% to 70 at.% Ni, preferably 51 at.% to 60 at.% Ni 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 and the balance aluminum.
dadurch gekennzeichnet, dass
ein Teil des Aluminiums ersetzt ist durch Verunreinigungen, Begleitelemente oder weitere Legierungselemente.Material according to claim 4,
characterized in that
a part of the aluminum is replaced by impurities, accompanying elements or other alloying elements.
dadurch gekennzeichnet, dass
die Summe aus Ta und Nb im Werkstoff zwischen 0,5 at.% bis 10 at.%, insbesondere 1 at.% bis 5 at.% beträgt.Material according to claim 4 or 5,
characterized in that
the sum of Ta and Nb in the material is between 0.5 at.% to 10 at.%, in particular 1 at.% to 5 at.%.
dadurch gekennzeichnet, dass
das Gefüge des Werkstoffs NiAl - Kristallite und/oder Ni3Al - Kristallite umfasst, an deren Korngrenzen die ternären Laves - Phasen angeordnet sind.Material according to one of the preceding claims,
characterized in that
comprises the structure of the material NiAl crystallites and / or Ni 3 Al crystallites, at the grain boundaries of which the ternary Laves phases are arranged.
dadurch gekennzeichnet, dass
das Bauteil eine Lauf - oder Leitschaufel in der Turbine, insbesondere der Niederdruckturbine einer Strömungsmaschine ist.Component according to claim 8,
characterized in that
the component is a runner or guide vane in the turbine, in particular the low - pressure turbine of a turbomachine.
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 true EP2832872A2 (en) | 2015-02-04 |
| EP2832872A3 EP2832872A3 (en) | 2015-05-27 |
| EP2832872B1 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106011539A (en) * | 2016-05-31 | 2016-10-12 | 中国科学院兰州化学物理研究所 | Wide-temperature range and self-lubricating nickel aluminum/vanadium oxide/silver composite material and preparation method thereof |
Families Citing this family (1)
| 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 |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5935349A (en) | 1994-05-21 | 1999-08-10 | Siemens Aktiengesellschaft | Intermetallic nickel-aluminum base alloy and material formed of the alloy |
Family Cites Families (7)
| 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 |
| 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 EP EP14176757.4A patent/EP2832872B1/en not_active Not-in-force
- 2014-07-11 ES ES14176757.4T patent/ES2581298T3/en active Active
- 2014-07-28 US US14/341,955 patent/US20150315919A1/en not_active Abandoned
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5935349A (en) | 1994-05-21 | 1999-08-10 | Siemens Aktiengesellschaft | Intermetallic nickel-aluminum base alloy and material formed of the alloy |
Non-Patent Citations (2)
| Title |
|---|
| ARTIKELN B. ZEUMER; G.SAUTHOFF: "Intermetallic NiAl-Ta alloys with strengthening Laves phase for high-temperature applcations I. Basic properties", INTERMETALLICS, vol. 5, 1997, pages 563 - 577, XP004092045, DOI: doi:10.1016/S0966-9795(97)00031-9 |
| B. ZEUMER; G. SAUTHOFF: "Deformation behaviour of intermetallic NiAl-Ta alloys with strengthening Laves phase for high-temperature applications II. Effects of alloying with Nb and other elements", INTERMETALLICS, vol. 5, 1997, pages 641 - 649, XP004098783, DOI: doi:10.1016/S0966-9795(97)00046-0 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106011539A (en) * | 2016-05-31 | 2016-10-12 | 中国科学院兰州化学物理研究所 | Wide-temperature range and self-lubricating nickel aluminum/vanadium oxide/silver composite material and preparation method thereof |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| ES2581298T3 (en) | 2016-09-05 |
| US20150315919A1 (en) | 2015-11-05 |
| EP2832872A3 (en) | 2015-05-27 |
| DE102013214767A1 (en) | 2015-01-29 |
| EP2832872B1 (en) | 2016-05-04 |
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