EP2832872B1 - Alliage pour construction légère résistant à la chaleur en NiAl - Google Patents

Alliage pour construction légère résistant à la chaleur en NiAl Download PDF

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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
Application number
EP14176757.4A
Other languages
German (de)
English (en)
Other versions
EP2832872A2 (fr
EP2832872A3 (fr
Inventor
Wilfried Smarsly
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
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2832872A2 publication Critical patent/EP2832872A2/fr
Publication of EP2832872A3 publication Critical patent/EP2832872A3/fr
Application granted granted Critical
Publication of EP2832872B1 publication Critical patent/EP2832872B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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.

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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)

Claims (9)

  1. Matière pour applications exigeant une grande résistance à la chaleur, à base d'aluminures de nickel intermétalliques, la matière comprenant plus de 50 % en at. de nickel et de phases de Laves ternaires, caractérisée en ce qu'elle comprend de 50,1 % en at. à 70 % en at. de Ni et de 0,5 % en at. à 10 % en at. de Ta et/ou de 0,5 % en at. à 10 % en at. de Nb et le reste est constitué d'aluminium.
  2. Matière selon la revendication 1, caractérisée en ce qu'elle comprend du NiAl et/ou du Ni3Al.
  3. Matière selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle comprend des phases de Laves ternaires à base de Ni, Al et Ta et/ou Nb, en particulier de NiAlTa, NiAlNb et/ou NiAl(Ta,Nb).
  4. Matière selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle comprend de 51 % en at. à 60 % en at. de Ni.
  5. Matière selon la revendication 4, caractérisée en ce qu'elle comprend de 1 % en at. à 5 % en at. de Ta et/ou de 1 % en at. à 5 % en at. de Nb.
  6. Matière selon la revendication 4 ou la revendication 5, caractérisée en ce que le total de Ta et de Nb dans la matière est compris entre 0,5 % en at. et 10 % en at., en particulier entre 1 % en at. et 5 % en at.
  7. Matière selon l'une quelconque des revendications précédentes, caractérisée en ce que sa structure comprend des cristallites de NiAl et/ou des cristallites de Ni3Al aux joints de grains desquels sont disposées les phases de Laves ternaires.
  8. Composant d'une turbomachine, en particulier d'une turbine d'avion, formé à partir de la matière selon l'une quelconque des revendications précédentes ou qui comprend cette matière.
  9. Composant selon la revendication 8, caractérisé en ce que c'est une aube mobile ou directrice dans la turbine, en particulier la turbine basse pression d'une turbomachine.
EP14176757.4A 2013-07-29 2014-07-11 Alliage pour construction légère résistant à la chaleur en NiAl Not-in-force EP2832872B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013214767.8A DE102013214767A1 (de) 2013-07-29 2013-07-29 Hochwarmfeste Leichtbaulegierung aus NiAl

Publications (3)

Publication Number Publication Date
EP2832872A2 EP2832872A2 (fr) 2015-02-04
EP2832872A3 EP2832872A3 (fr) 2015-05-27
EP2832872B1 true EP2832872B1 (fr) 2016-05-04

Family

ID=51211553

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14176757.4A Not-in-force EP2832872B1 (fr) 2013-07-29 2014-07-11 Alliage pour construction légère résistant à la chaleur en NiAl

Country Status (4)

Country Link
US (1) US20150315919A1 (fr)
EP (1) EP2832872B1 (fr)
DE (1) DE102013214767A1 (fr)
ES (1) ES2581298T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017109156A1 (de) 2016-04-28 2017-11-02 Hochschule Flensburg Hochwarmfester Werkstoff und dessen Herstellung
CN106011539B (zh) * 2016-05-31 2017-10-31 中国科学院兰州化学物理研究所 一种镍铝/氧化钒/银宽温域自润滑复合材料及其制备方法

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884688A (en) * 1956-12-28 1959-05-05 Borolite Corp Sintered ni-al-zr compositions
DE2521563A1 (de) * 1975-05-15 1976-12-02 Heinz Dr Sprenger Hochwarmfeste nickellegierung
US5116691A (en) * 1991-03-04 1992-05-26 General Electric Company Ductility microalloyed NiAl intermetallic compounds
DE4324960A1 (de) * 1993-07-24 1995-01-26 Mtu Muenchen Gmbh Laufrad einer Turbomaschine, insbesondere einer Turbine eines Gasturbinentriebwerks
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 (de) * 2008-11-26 2010-05-31 Alstom Technology Ltd Hochtemperatur- und oxidationsbeständiges Material.

Also Published As

Publication number Publication date
EP2832872A2 (fr) 2015-02-04
ES2581298T3 (es) 2016-09-05
DE102013214767A1 (de) 2015-01-29
EP2832872A3 (fr) 2015-05-27
US20150315919A1 (en) 2015-11-05

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