EP2876177B1 - Matériau constitué d'une phase de laves et d'une phase fe-al ferritique - Google Patents

Matériau constitué d'une phase de laves et d'une phase fe-al ferritique Download PDF

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Publication number
EP2876177B1
EP2876177B1 EP13194100.7A EP13194100A EP2876177B1 EP 2876177 B1 EP2876177 B1 EP 2876177B1 EP 13194100 A EP13194100 A EP 13194100A EP 2876177 B1 EP2876177 B1 EP 2876177B1
Authority
EP
European Patent Office
Prior art keywords
material according
phase
laves phase
laves
ferritic
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
EP13194100.7A
Other languages
German (de)
English (en)
Other versions
EP2876177A1 (fr
Inventor
Wilfried Smarsly
Gerhard Sauthoff
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 EP13194100.7A priority Critical patent/EP2876177B1/fr
Priority to ES13194100.7T priority patent/ES2634089T3/es
Priority to US14/550,659 priority patent/US20150147220A1/en
Publication of EP2876177A1 publication Critical patent/EP2876177A1/fr
Application granted granted Critical
Publication of EP2876177B1 publication Critical patent/EP2876177B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • C22C27/02—Alloys based on vanadium, niobium, or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/26—Ferrous alloys, e.g. steel alloys containing chromium with niobium or tantalum

Definitions

  • the present invention relates to a material for components of turbomachines, in particular of stationary gas turbines and aircraft engines, which comprises at least one Laves phase and one ferritic phase with Fe and Al, as well as a corresponding component.
  • turbomachines such as stationary gas turbines or aircraft engines
  • components such as blades, disks and the like
  • turbomachinery which must withstand both the high temperatures and the aggressive environmental conditions in the operation of turbomachinery, and in particular at the partially prevailing high temperatures sufficient Must have strength and creep resistance.
  • various materials are known in the prior art, which meet the requirements together with suitable coatings.
  • the potential of previously used materials, such as iron and nickel - based alloys already largely exhausted, so that further efficiency gains for turbomachinery must be achieved, for example by higher working temperatures through novel materials.
  • Examples are in the DE 10 2005 061 790 A1 or the US 8,012,271 B2 described.
  • a material based on an iron-based alloy is proposed, which has intercalated Laves phases.
  • the iron-base alloy material is an iron-aluminum-chromium alloy
  • the Laves intermetallic phases are based on ternary systems containing the constituents iron, aluminum, niobium and / or tantalum.
  • Such materials have due to the ordered intermetallic phases, even at high temperatures high strengths, so they meet the requirements for the application for corresponding components in gas turbines at operating temperatures in the range of more than 730 ° C can meet.
  • the material should meet the other requirements for a high-temperature material for use in turbomachinery and components made of this material should be easy to manufacture.
  • the invention proposes a material which has fractions of a ferritic phase with iron and aluminum and at least one Laves phase, the proportion of the at least one Laves phase making up the largest proportion of the material.
  • the Laves phase (s) form the framework or matrix of the material and the incorporated ferritic phase serves to improve the ductility of the material, since the ferritic Fe - Al phase is less hard than the Laves. Phases are.
  • a material is proposed in which the largest proportion is formed by the hard and high-strength and heat-resistant Laves phases and a ferritic iron-aluminum phase and possibly further occurring phases have lower proportions of the material.
  • the material according to the invention contains 50 vol.% Or more Laves phase, in particular 60 vol.% Or more, preferably 70 vol.% Or more Laves phase, wherein only a single Laves phase can be present or several different Laves phases.
  • the Laves phases are intermetallic compounds according to the three structural types (MgCu 2 , MgZn 2 and MgNi 2 ), but the compounds given merely serve to describe the crystal structure but do not occur in this composition in the material according to the invention.
  • the Laves phases in the material according to the invention may in particular be ternary or multinary Laves phases which thus have at least three different components.
  • Multiphase Laves phases refer to Laves phases with four or more components.
  • the Laves phases may be a hexagonal intermetallic phase of composition MeMe ' 2 , where Me is metal.
  • Me Me
  • Me Me
  • quaternary or multinary Laves phases the composition is given by partial replacement of one of the components Me, Me' or Me".
  • the ternary Laves phase may be formed, in particular, on the basis of the ternary system FeTaAl, the Laves phase in particular comprising 15% by weight to 65% by weight of iron, 1% by weight to 15% by weight of aluminum and 0, 5 wt.% To 65 wt.% Tantalum may have.
  • the tantalum component in the ternary Laves phase can also be at least partially replaced by niobium, so that the Laves phase can also be formed by a quaternary system FeTaNbAl.
  • the ternary Laves phase may be formed on the basis of FeNbAl, such a ternary Laves phase in particular comprising 15% by weight to 65% by weight of iron, 1% by weight to 15% by weight of aluminum and 0 5% by weight to 55% by weight of niobium.
  • Laves phases based on ternary Laves phases may contain minor constituents of other elements present in the alloy, as described by the quaternary or multinary systems with sufficiently large proportions of such elements.
  • the Laves phases can also have chromium components, so that the described ternary Laves phases can be formed quaternary with a corresponding chromium component (FeCrTaAl or Fe-CrNbAl) or the Laves phase can be formed on the basis of a system FeCrAlTaNb. Chrome can at least partially replace the Fe content in these Laves phases.
  • the ferritic phase with iron and aluminum may be a cubic space-centered mixed crystal with aluminum and other alloying constituents.
  • the ferritic Fe-Al phase may additionally comprise chromium.
  • the material consists of 20 to 25 at.% Chromium, in particular 23 at.% Chromium, 5 to 35 at.% Aluminum, in particular 7 to 30 at.% Aluminum and 10 to 25 at.% Tantalum and / or niobium and Remaining iron and unavoidable impurities.
  • the corresponding material can be produced both by fusion metallurgy and by powder metallurgy.
  • alloy compositions are suitable for use: alloy Fe [At.%] Cr [At.%] Al [At.%] Ta [At.%] Nb [At.%] 1 40 23 27 10 0 2 40 23 27 7 3 3 40 23 27 3 7 4 40 23 27 0 10 5 60 23 7 10 0 6 60 23 7 7 3 7 60 23 7 3 7 8th 60 23 7 0 10 9 25 23 27 25 0 10 25 23 27 16 9 11 25 23 27 9 16 12 25 23 27 0 25 13 45 23 7 25 0 14 45 23 7 16 9 15 45 23 7 9 16 16 45 23 7 0 25
  • the proportions of aluminum, tantalum and niobium and correspondingly of iron can be varied, while for example a solid chromium content of the order of 23 at.% Can be provided. While the ratio of tantalum and niobium is set to values of 10 and 25 at.% Respectively, the aluminum content and, correspondingly, the iron content varies between a low aluminum content of the order of 7 at.% And a high aluminum content of the order of 27 at.%, so that correspondingly different iron contents are present. This makes it possible, in particular, to vary the ferritic Fe-Al-Cr phase and its properties, in particular with regard to ductility.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)

Claims (15)

  1. Matériau pour composants d'une turbine à gaz, en particulier d'un propulseur d'aéronef, avec des fractions d'une phase ferritique avec de Fe et de l'Al et des fractions d'au moins une phase de laves,
    caractérisé en ce que le matériau est constitué de 20 à 25 % atomiques de Cr, de 5 à 35 % atomiques d'Al et de 10 à 25 % atomiques de tantale et/ou de niobium, le restant étant constitué de Fe et d'impuretés inévitables, dans lequel la fraction de la au moins une phase de laves constitue la plus grande partie du matériau, à savoir supérieure ou égale à 50 % en volume.
  2. Matériau selon la revendication 1,
    caractérisé en ce que :
    la fraction de l'au moins une phase de laves est supérieure ou égale à 60 % en volume, de préférence supérieure ou égale à 70 % en volume.
  3. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    la phase de laves est une phase laves ternaire ou multinaire.
  4. Matériau selon la revendication 3,
    caractérisé en ce que :
    la phase de laves ternaire ou multinaire est formée à base de FeTaAl.
  5. Matériau selon la revendication 4,
    caractérisé en ce que :
    la phase de laves à base de FeTaAl comprend en outre du Nb qui remplace en partie le Ta.
  6. Matériau selon la revendication 3,
    caractérisé en ce que :
    la phase de laves ternaire ou multinaire est formée à base de FeNbAl.
  7. Matériau selon la revendication 6,
    caractérisé en ce que :
    la phase de laves à base de FeNbAl comprend en outre du Ta qui remplace en partie le Nb.
  8. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    la phase de laves contient du Cr, qui remplace en particulier en partie le Fe.
  9. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    la phase de laves est formée à base de FeCrAlTaNb.
  10. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    la phase ferritique comprend en outre du Cr.
  11. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    dans la structure du matériau, la au moins une phase de laves forme une matrice ou un squelette, dans laquelle ou lequel la phase ferritique est imbriquée.
  12. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    le matériau présente aux environs de 23 % atomiques de Cr.
  13. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    le matériau présente 7 à 30 % atomiques d'Al.
  14. Matériau selon l'une quelconque des revendications précédentes,
    caractérisé en ce que :
    le matériau est fabriqué par métallurgie en fusion ou métallurgie des poudres.
  15. Composant d'une turbine à gaz, en particulier d'un propulseur d'aéronef, avec un matériau selon l'une quelconque des revendications précédentes.
EP13194100.7A 2013-11-22 2013-11-22 Matériau constitué d'une phase de laves et d'une phase fe-al ferritique Not-in-force EP2876177B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13194100.7A EP2876177B1 (fr) 2013-11-22 2013-11-22 Matériau constitué d'une phase de laves et d'une phase fe-al ferritique
ES13194100.7T ES2634089T3 (es) 2013-11-22 2013-11-22 Material que consta de fase Laves y fase Fe-Al ferrítica
US14/550,659 US20150147220A1 (en) 2013-11-22 2014-11-21 MATERIAL OF LAVES PHASE AND FERRITIC Fe-Al PHASE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13194100.7A EP2876177B1 (fr) 2013-11-22 2013-11-22 Matériau constitué d'une phase de laves et d'une phase fe-al ferritique

Publications (2)

Publication Number Publication Date
EP2876177A1 EP2876177A1 (fr) 2015-05-27
EP2876177B1 true EP2876177B1 (fr) 2017-07-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13194100.7A Not-in-force EP2876177B1 (fr) 2013-11-22 2013-11-22 Matériau constitué d'une phase de laves et d'une phase fe-al ferritique

Country Status (3)

Country Link
US (1) US20150147220A1 (fr)
EP (1) EP2876177B1 (fr)
ES (1) ES2634089T3 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040011435A1 (en) * 2002-07-17 2004-01-22 Wu James B. C. Wear-resistant, corrosion-resistant cobalt-based alloys
DE102005061790A1 (de) 2005-12-23 2007-07-05 Mtu Aero Engines Gmbh Werkstoff für Bauteile einer Gasturbine
DE102009039552B4 (de) * 2009-09-01 2011-05-26 Thyssenkrupp Vdm Gmbh Verfahren zur Herstellung einer Eisen-Chrom-Legierung

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Publication number Publication date
EP2876177A1 (fr) 2015-05-27
ES2634089T3 (es) 2017-09-26
US20150147220A1 (en) 2015-05-28

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