EP2196550B1 - Matériau à base de NiAl, résistant aux températures élevées et à l'oxydation - Google Patents

Matériau à base de NiAl, résistant aux températures élevées et à l'oxydation Download PDF

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Publication number
EP2196550B1
EP2196550B1 EP09176306.0A EP09176306A EP2196550B1 EP 2196550 B1 EP2196550 B1 EP 2196550B1 EP 09176306 A EP09176306 A EP 09176306A EP 2196550 B1 EP2196550 B1 EP 2196550B1
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EP
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Prior art keywords
weight
nial
material according
temperature
materials
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Not-in-force
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EP09176306.0A
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German (de)
English (en)
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EP2196550A1 (fr
Inventor
Mohamed Nazmy
Markus Staubli
Andreas KÜNZLER
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General Electric Technology GmbH
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Alstom Technology AG
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    • 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

Definitions

  • the invention relates to the field of materials technology. It relates to a high-temperature-resistant material based on alloyed intermetallic NiAl, which even at temperatures above about 1527 ° C (1800 K) has not yet melted and which has a very good oxidation resistance at high operating temperatures.
  • the nickel aluminides are known to have high strength intermetallic materials which, although somewhat in competition with the nickel base superalloys, have a drawback to their low toughness and high DBT (Ductile Brittle Transition) compared to the ductile high tenacity Ni base superalloys.
  • Temperature R. Dariola: NiAl for Turbine Airfoil Application, Structural Intermetallics, The Minerals, Metals and Materials Society, 1993, pp. 495-504 ), which is reflected in low ductility of these materials at low temperatures.
  • the hot strength is insufficient.
  • their low density is advantageous.
  • Ni 3 Al materials with an Al content of about 10-13% by weight and the remainder Ni
  • ductility improvement is for example off US 4,478,791 and US 4,612,165 known.
  • DE 36 30 328 C2 It is proposed to add increased amounts of iron (14-17% by weight) in such Ni 3 Al materials in order to improve the hot toughness and processability.
  • the Al contents are there at about 10% by weight.
  • up to about 4% by weight of Mo and / or up to 0.1% by weight of C must be added.
  • intermetallic Ni aluminides are in need of improvement in terms of their high temperature and oxidation resistance due to the ever-increasing stress conditions in thermal turbomachines, in particular gas turbines. It is desirable to alloy intermetallic compounds such that, on the one hand, the ductility of the NiAl intermetallic materials is improved while maintaining the ordered atomic structure to achieve, for example, a high melting point and high strength values at high temperatures. In addition, the oxidation resistance should be very good.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a high temperature resistant material based on alloyed intermetallic NiAl, which has not melted even at temperatures above about 1527 ° C (1800 K) and which has a very good oxidation resistance at high operating temperatures ,
  • the material according to the invention has 1 to 6, preferably 4.7% by weight of Ta.
  • Ta acts as a precipitation hardener and increases high-temperature strength. If more than 6% by weight of Ta is adjusted, on the other hand, the oxidation resistance will be adversely affected.
  • iron in the stated range from 0.1 to 3, preferably from 0.2 to 1.6,% by weight serves to increase the ductility.
  • B is an element which solidifies the grain boundaries in the stated amounts of from 0.01 to 0.2, preferably 0.1,% by weight. Higher boron contents are critical, as they can lead to undesirable boron precipitations, which have an embrittling effect. The interaction of boron with the other constituents, in particular Ta, leads to good strength values.
  • Hf in the specified range of 0.1 to 1.5, preferably 0.2 to 1.2 wt .-%) and Pd (in the specified range of 0.1 to 5, preferably 0.5 wt -.%) Also contribute to increase the strength. If the mentioned ranges are exceeded, this disadvantageously leads to embrittlement of the material.
  • the inventive high-temperature material based on alloyed intermetallic NiAl has excellent properties at very high temperatures of 1300 ° C, in particular a good creep strength, and it also has an extremely high oxidation resistance.
  • the comparative alloys Hastelloy X, Haynes 214 and CMSX4 were tested in the fully heat-treated state (according to the manufacturer).
  • the alloys according to the invention were produced as follows: In a melting furnace (arc) in each case a button of about 50 g was melted for the six materials investigated. Subsequently, this button was heat treated at 1100 ° C for 12 hours and then cooled in the oven to room temperature.
  • Fig. 2 Such a statement can also be made Fig. 2 derived.
  • the weight change is shown as a function of the removal time to a maximum of 12 hours at 1300 ° C for different materials.
  • the largest change in weight and thus the worst oxidation resistance has the commercial nickel base superalloy Hastelloy X.
  • this comparative alloy After a storage time of about 12 hours at 1300 ° C, this comparative alloy has about four times greater weight change than the two inventive materials VHTIM-3 and VHTIM-6 , But the two other comparative alloys Haynes 214 and CMSX-4 show over the entire aging period adversely a higher weight change than the invention VHTIM-3 and VHTIM-6.
  • iron in the stated range from 0.1 to 3, preferably from 0.2 to 1.6,% by weight serves to increase the ductility.
  • B is an element which solidifies the grain boundaries in the stated amounts of from 0.01 to 0.2, preferably 0.1,% by weight. Higher boron contents are critical, as they can lead to undesirable boron precipitations, which have an embrittling effect. The interaction of boron with the other constituents, in particular Ta, leads to good strength values. On the other hand, by micro-alloying with B, an improvement in toughness is achieved.
  • Hf in the specified range of 0.1 to 1.5, preferably 0.2 to 1.2 wt .-%) and Pd (in the specified range of 0.1 to 5, preferably 0.5 wt -.%) Also contribute to increase the strength. If the mentioned ranges are exceeded, this disadvantageously leads to embrittlement of the material.
  • inventive high-temperature resistant and oxidation-resistant alloyed intermetallic Ni aluminides can be advantageously used for high-temperature components in gas turbines.
  • plating on heat shields or crowns on the tips of high pressure paddles may be cited.
  • Table 1 Chemical composition of the materials studied Ni Cr Co Not a word W Fe Mn Si C al Ta Y B re Hf Pd Ti Hastelloy X rest 22 1.5 9 0.6 18.5 0.5 0.5 0.1 0.3 - - - - - - - Haynes 214 rest 16 - - - 3 - - - - - 12:01 - - - - - CMSX4 rest 6.5 9 0.6 6 - - - - 5.6 6.5 - - 3 0.1 - 1 VHTIM-1 rest - - - - - 1.6 - - - 27.5 4.7 - 0.1 - 1.2 - - VHTIM-2 rest - - - - 1.6 - - - 27.5 4.7 - 0.1 1.2 0.5 - VHTIM-3 rest - - - - - 1.6 - - - 27.5 4.7 - - - 1.2 0.5 - VHTIM-3

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (11)

  1. Matériau résistant aux températures élevées à base de NiAl intermétallique allié, caractérisé par la composition chimique suivante (indications en % en poids):
    26-30 Al,
    1-6 Ta,
    0,1-3 Fe,
    0,1-1,5 Hf,
    0,01-0,2 B,
    0-1 Ti,
    0,1-5 Pd,
    le reste étant du nickel et des impuretés dues à la fabrication.
  2. Matériau résistant aux températures élevées selon la revendication 1, caractérisé par 27-28 % en poids d'Al.
  3. Matériau résistant aux températures élevées selon la revendication 2, caractérisé par 27,5 % en poids d'Al.
  4. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 3, caractérisé par 2-5 % en poids de Ta.
  5. Matériau résistant aux températures élevées selon la revendication 4, caractérisé par 4,7 % en poids de Ta.
  6. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 5, caractérisé par 0,2-2 % en poids de Fe.
  7. Matériau résistant aux températures élevées selon la revendication 6, caractérisé par 1,6 % en poids de Fe.
  8. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 7, caractérisé par 0,2-1,2, de préférence 1,2 % en poids de Hf.
  9. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 8, caractérisé par 0,1 % en poids de B.
  10. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 9, caractérisé par 0,5 % en poids de Pd.
  11. Matériau résistant aux températures élevées selon l'une quelconque des revendications 1 à 10, caractérisé par 1 % en poids de Ti.
EP09176306.0A 2008-11-26 2009-11-18 Matériau à base de NiAl, résistant aux températures élevées et à l'oxydation Not-in-force EP2196550B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01844/08A CH699930A1 (de) 2008-11-26 2008-11-26 Hochtemperatur- und oxidationsbeständiges Material.

Publications (2)

Publication Number Publication Date
EP2196550A1 EP2196550A1 (fr) 2010-06-16
EP2196550B1 true EP2196550B1 (fr) 2015-05-27

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EP09176306.0A Not-in-force EP2196550B1 (fr) 2008-11-26 2009-11-18 Matériau à base de NiAl, résistant aux températures élevées et à l'oxydation

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Country Link
US (1) US8048368B2 (fr)
EP (1) EP2196550B1 (fr)
JP (1) JP5502435B2 (fr)
CH (1) CH699930A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012096937A1 (fr) * 2011-01-10 2012-07-19 Arcelormittal Investigacion Y Desarrollo S.L. Procédé de soudage d'aluminure de nickel
CN103160708B (zh) * 2013-04-12 2015-05-13 湖南科技大学 一种NiAl-2.5Ta-7.5Cr-20Co合金作为高温自润滑材料的应用
CN103160712B (zh) * 2013-04-12 2015-04-01 湖南科技大学 一种NiAl-2.5Ta-7.5Cr-1B合金作为高温自润滑材料的应用
DE102013214767A1 (de) * 2013-07-29 2015-01-29 MTU Aero Engines AG Hochwarmfeste Leichtbaulegierung aus NiAl
CN104032190B (zh) * 2014-06-19 2016-02-10 湖南科技大学 一种NiAl-2.5Ta-7.5Cr-1B-5Co-2.5Re合金作为碱腐蚀工况下自润滑耐磨材料的应用
DE102017009948A1 (de) * 2017-10-26 2019-05-02 Forschungszentrum Jülich GmbH Fachbereich Patente Verfahren zur Reparatur einkristalliner Werkstoffe

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4478791A (en) * 1982-11-29 1984-10-23 General Electric Company Method for imparting strength and ductility to intermetallic phases
US4612165A (en) * 1983-12-21 1986-09-16 The United States Of America As Represented By The United States Department Of Energy Ductile aluminide alloys for high temperature applications
GB2194549B (en) * 1986-09-01 1990-11-21 Us Energy High temperature fabricable nickel-iron aluminides
JPS63225722A (ja) * 1986-09-30 1988-09-20 Mitsubishi Heavy Ind Ltd 摺動部材
JPH03260028A (ja) * 1990-03-09 1991-11-20 Hitachi Ltd 延性のある高強度ニツケル系Ｌｌ↓２型金属間化合物基合金
JPH04180535A (ja) * 1990-11-13 1992-06-26 Kobe Steel Ltd Ｎｉ―Ａ１系合金
US5116438A (en) 1991-03-04 1992-05-26 General Electric Company Ductility NiAl intermetallic compounds microalloyed with gallium
JPH10341326A (ja) 1997-06-09 1998-12-22 Murata Mach Ltd Ｇ４ファクシミリアダプタ
JP2989169B2 (ja) * 1997-08-08 1999-12-13 日立金属株式会社 Ｎｉ−Ａｌ系金属間化合物ターゲットおよびその製造方法ならびに磁気記録媒体
JPH1192846A (ja) * 1997-09-17 1999-04-06 Sumitomo Electric Ind Ltd 焼結摩擦材およびその製造方法
US6153313A (en) * 1998-10-06 2000-11-28 General Electric Company Nickel aluminide coating and coating systems formed therewith
EP1327702A1 (fr) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Revêtement de liaison de type MCrAlY et procédé de depôt de ce revêtement de liason de type MCrAlY
US6998151B2 (en) * 2002-05-10 2006-02-14 General Electric Company Method for applying a NiAl based coating by an electroplating technique

Also Published As

Publication number Publication date
EP2196550A1 (fr) 2010-06-16
CH699930A1 (de) 2010-05-31
JP2010126813A (ja) 2010-06-10
US20100129256A1 (en) 2010-05-27
JP5502435B2 (ja) 2014-05-28
US8048368B2 (en) 2011-11-01

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