EP2451986B2 - Superalliage a base de nickel - Google Patents

Superalliage a base de nickel Download PDF

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Publication number
EP2451986B2
EP2451986B2 EP10726136.4A EP10726136A EP2451986B2 EP 2451986 B2 EP2451986 B2 EP 2451986B2 EP 10726136 A EP10726136 A EP 10726136A EP 2451986 B2 EP2451986 B2 EP 2451986B2
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EP
European Patent Office
Prior art keywords
nickel
alloy
ppm
alloys
based super
Prior art date
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Not-in-force
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EP10726136.4A
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German (de)
English (en)
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EP2451986B1 (fr
EP2451986A1 (fr
Inventor
Mohamed Nazmy
Andreas KÜNZLER
Claus Paul Gerdes
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.)
Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland 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
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%

Definitions

  • the invention relates to the field of materials technology. It relates to a nickel-base superalloy, in particular for the production of single-crystal components (SX alloy) or components with directionally solidified structure (DS alloy), such as blades for gas turbines.
  • SX alloy single-crystal components
  • DS alloy directionally solidified structure
  • the alloy according to the invention can also be used for conventionally cast components.
  • Nickel-base superalloys are known. Single crystal components of these alloys have a very good material strength at high temperatures. As a result, z. B. the inlet temperature of gas turbines are increased, whereby the efficiency of the gas turbine increases.
  • Nickel-based superalloys for single crystal components as they are made US 4,643,782 .
  • EP 0 208 645 and US 5,270,123 for this purpose, mixed-crystal-hardening alloying elements, for example Re, W, Mo, Co, Cr, and ⁇ '-phase-forming elements, for example Al, Ta, and Ti, are included.
  • the content of high-melting alloying elements (W, Mo, Re) in the basic matrix (Austenitic ⁇ -phase) increases continuously with the increase of the stress temperature of the alloy.
  • W, Mo, Re high-melting alloying elements
  • the alloys disclosed in the above references have high creep strength, good LCF (low duty cycle fatigue) and HCF (high cycle fatigue) properties, and high oxidation resistance.
  • the alloy CMSX-4 US 4,643,782 when used experimentally in a gas turbine at a temperature above 1000 ° C, a strong coarsening of the ⁇ '-phase, which is associated with an increase in the creeping speed of the alloy adversely.
  • EP 1 359 231 B1 is a nickel-based superalloy is known, which has an improved castability and a higher oxidation resistance compared to known nickel-based superalloys and also z. B. is particularly suitable for large gas turbine single crystal components with a length of> 80 mm.
  • the nickel-base superalloy disclosed therein is characterized by the following chemical composition (in% by weight): 7.7-8.3 Cr, 5.0-5.25 Co, 2.0-2.1 Mo, 7.8-8.3 W, 5.8-6.1 Ta, 4.9 -5.1 Al, 1.3-1.4 Ti, 0.11-0.15 Si, 0.11-0.15 Hf, 200-750 ppm C, 50-400 ppm B, remainder nickel and production-related impurities.
  • the aim of the invention is to develop an alloy which, compared to the alloys known from the prior art, is characterized by a further property optimization with regard to use as a gas turbine component.
  • the invention is based on the object to develop a nickel-based superalloy, which has a high oxidation resistance and at the same time a high corrosion resistance (with different fuel properties) and to which is advantageously less expensive compared to known such nickel-based superalloys.
  • the alloy has a very high oxidation resistance and at the same time a high corrosion resistance at high temperatures. This is achieved in a surprising manner, especially by the relatively low Re addition.
  • the alloy 1.0-1.5. preferably has 1.5% by weight of Re. If the C content is only about 200-300 ppm and the boron content is 50-100 ppm, preferably 90 ppm, then these alloys according to the invention are particularly suitable for producing single-crystal components.
  • the alloy according to the invention has 0.1-0.2% by weight of Nb
  • This alloy has excellent properties at high temperatures and is also not too expensive due to the relatively low Re content.
  • This latter alloy is particularly suitable for the production of single crystal components.
  • Nickel-based superalloys having the chemical composition given in Table 1 were investigated (in% by weight): Table 1: Chemical composition of the investigated alloys IN738LC (DS) comparative alloy KNX1 (CC) KNX2 (CC) KNX3 (CC) KNX4 (CC) KNX0 (CC) comparative alloy Ni rest rest rest rest rest rest Cr 16 8.2 8.2 8.2 8.2 8.2 Co 8.5 5.2 5.2 5.2 5.2 Not a word 1.7 2.1 2.1 2.1 2.1 2.1 W 2.6 8.1 8.1 8.1 8.1 Ta 1.7 6.1 6.1 6.1 6.1 al 3.4 5 5 5 5 5 Ti 3.4 1.4 1.4 1.4 1.4 1.4 Hf - 0.6 0.1 0.1 0.1 12:11 C - 12:17 12:02 0095 12:17 12:02 B 12:01 0029 0009 0024 0029 0009 Si - 12:12 12:12 12:12 12:12 Nb 0.9 - 0.1 0.1 0.1 12:11 C
  • the alloy IN738LC is a comparative alloy known from the prior art
  • KNX0 is also a comparative alloy (according to EP 1 359 231 B1 )
  • the alloys KNX2 and KNX4 are alloys according to the invention and the alloys KNX1 and KNX3 are not inventive alloys.
  • the suffix CC stands in each case as an abbreviation for "conventionally cast”, ie conventionally cast alloys with conventional polygonal structure and the addition DS as an abbreviation for "directionally solidified”, ie for directionally solidified microstructure.
  • the alloys according to the invention and the comparative alloy differ, for example, in that the comparative alloy is not alloyed with C, Si, Hf and Re in contrast to the alloys according to the invention.
  • the presence of C in and along the grain boundaries reduces the diffusion process, which is a major cause of grain boundary weakness.
  • the castability of long single-crystal components for example, gas turbine blades with a length of about 200 to 230 mm, significantly improved.
  • nickel-base superalloys with low C and B contents are chosen according to claim 1 of the invention, these are useful as single crystal alloys, with higher contents of these elements (maximum 200-300 ppm C and 50-100 ppm B), the components produced from corresponding alloys can also be cast conventionally.
  • Re, W, Mo, Co, and Cr are alloy-strengthening alloying elements, and Al, Ta, and Ti are ⁇ '-phase-forming elements, all of which improve material strength at high temperatures. Since, in this regard, the content of high-melting alloying elements (W, Mo, Re) in the basic matrix is regarded as decisive for the increase in the maximum possible stress temperature of the alloy, these alloying elements, especially the Re, have hitherto been added in relatively large amounts.
  • the moderate rhenium content of the nickel-based superalloy according to the invention of preferably 1.5% by weight advantageously increases the creep resistance of the alloy on the one hand, and on the other hand does not cause such extremely high costs by this alloying element as is the case, for example, with the nickel known from the prior art Second and third generation base single crystal superalloys which have relatively high rhenium levels (about 3 to 6 wt% Re).
  • Fig. 1 are the results of tensile tests (yield strength, tensile strength, elongation) at room temperature for an alloy known from the prior art (DS IN738LC) and the alloy CC KNX1 The respective chemical composition of the alloys is given in Tab.
  • Fig. 2 is a quasi-isothermal oxidation diagram shown.
  • Fig. 3 shows, on the one hand, the dependence of creep resistance on the Larson-Miller parameter for the same alloys as in Fig. 1 and 2 .
  • the values of these two investigated alloys can be assigned to a single curve, ie they are comparable. But taking into account the fact that DS (or SX) alloys usually due to their microstructure have improved creep resistance over conventional non-directionally solidified multi-crystalline structures of alloys with comparable chemical composition, so significantly improved creep properties for inventive alloys with DS- or To expect SX structures.

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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)
  • Catalysts (AREA)
  • Heat Treatment Of Sheet Steel (AREA)

Claims (10)

  1. Superalliage à base de nickel, caractérisé par la composition chimique suivante (indications en % en poids) :
    7,7-8,3 Cr
    5,0-5,25 Co
    2,0-2,1 Mo
    7,8-8,3 W
    5,8-6,1 Ta
    4,9-5,1 Al
    1,0-1,5 Ti
    1,0-2,0 Re
    0,1-0,2 Nb
    0,11-0,15 Si
    0,1-0,7 Hf
    0,02-0,17 C
    50-400 ppm B
    le reste étant constitué de nickel et des impuretés dues au mode de fabrication.
  2. Superalliage à base de nickel selon la revendication 1, caractérisé par 1,0-1,5 % en poids de Re.
  3. Superalliage à base de nickel selon la revendication 2, caractérisé par 1,5 % en poids de Re.
  4. Superalliage à base de nickel selon la revendication 1, caractérisé par 0,1 % en poids de Nb.
  5. Superalliage à base de nickel selon l'une des revendications 1 à 4, caractérisé par 0,1-0,6 % en poids de Hf.
  6. Superalliage à base de nickel selon la revendication 5, caractérisé par 0,1 % en poids de Hf.
  7. Superalliage à base de nickel selon l'une des revendications 1 à 6, caractérisé par 0,02-0,095, de préférence 0,02-0,03 % en poids de C.
  8. Superalliage à base de nickel selon l'une des revendications 1 à 7, caractérisé par 50-100 ppm, de préférence 90 ppm de B.
  9. Superalliage à base de nickel selon la revendication 1, caractérisé par la composition chimique suivante (indications en % en poids) :
    8,2 Cr
    5,2 Co
    2,1 Mo
    8,1 W
    6,1 Ta
    5,0 Al
    1,4 Ti
    1,5 Re
    0,1-0,2 Nb
    0,12 Si
    0,1-0,6 Hf
    0,095-0,17 C
    240-290 ppm B
    le reste étant constitué de nickel et des impuretés dues au mode de fabrication.
  10. Superalliage à base de nickel selon la revendication 1, caractérisé par la composition chimique suivante (indications en % en poids)
    8,2 Cr
    5,2 Co
    2,1 Mo
    8,1 W
    6,1 Ta
    5,0 Al
    1,4 Ti
    1,5 Re
    0,1 Nb
    0,12 Si
    0,1 Hf
    200 ppm C
    90 ppm B
    le reste étant constitué de nickel et des impuretés dues au mode de fabrication.
EP10726136.4A 2009-07-09 2010-07-01 Superalliage a base de nickel Not-in-force EP2451986B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01069/09A CH701415A1 (de) 2009-07-09 2009-07-09 Nickel-Basis-Superlegierung.
PCT/EP2010/059368 WO2011003804A1 (fr) 2009-07-09 2010-07-01 Superalliage à base de nickel

Publications (3)

Publication Number Publication Date
EP2451986A1 EP2451986A1 (fr) 2012-05-16
EP2451986B1 EP2451986B1 (fr) 2013-08-21
EP2451986B2 true EP2451986B2 (fr) 2017-10-18

Family

ID=41198665

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10726136.4A Not-in-force EP2451986B2 (fr) 2009-07-09 2010-07-01 Superalliage a base de nickel

Country Status (6)

Country Link
US (1) US9017605B2 (fr)
EP (1) EP2451986B2 (fr)
JP (1) JP5595495B2 (fr)
CH (1) CH701415A1 (fr)
RU (1) RU2525952C2 (fr)
WO (1) WO2011003804A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH701415A1 (de) 2009-07-09 2011-01-14 Alstom Technology Ltd Nickel-Basis-Superlegierung.
WO2013167513A1 (fr) 2012-05-07 2013-11-14 Alstom Technology Ltd Procédé de fabrication d'éléments en superalliages monocristallins (sx) ou solidifiés de manière directionnelle (ds)
JP6016016B2 (ja) * 2012-08-09 2016-10-26 国立研究開発法人物質・材料研究機構 Ｎｉ基単結晶超合金
RU2685455C2 (ru) * 2015-12-15 2019-04-18 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Литейный никелевый сплав с равноосной структурой

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) † 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties
JP2001294959A (ja) † 2000-04-17 2001-10-26 Mitsubishi Heavy Ind Ltd 単結晶Ｎｉ基耐熱合金およびタービン翼
EP1319729A1 (fr) † 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel
EP1184473B1 (fr) † 2000-08-30 2005-01-05 Kabushiki Kaisha Toshiba Alliages monocristallins à base de nickel et méthode de fabriction et éléments d'un turbine à gaz à des hautes températures à partir de ceux-ci
EP1900839A1 (fr) † 2006-09-07 2008-03-19 ALSTOM Technology Ltd Procédé pour le traitement thermique de superalliages à base de Ni

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4643782A (en) * 1984-03-19 1987-02-17 Cannon Muskegon Corporation Single crystal alloy technology
US5270123A (en) * 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
RU2088685C1 (ru) * 1995-03-14 1997-08-27 Уфимский государственный авиационный технический университет Жаропрочный сплав на никелевой основе
US6190471B1 (en) 1999-05-26 2001-02-20 General Electric Company Fabrication of superalloy articles having hafnium- or zirconium-enriched protective layer
RU2186144C1 (ru) * 2000-11-16 2002-07-27 Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Никелевый жаропрочный сплав для монокристального литья и изделие, выполненное из этого сплава
CH695497A5 (de) * 2002-04-30 2006-06-15 Alstom Technology Ltd Nickel-Basis-Superlegierung.
US6905559B2 (en) * 2002-12-06 2005-06-14 General Electric Company Nickel-base superalloy composition and its use in single-crystal articles
US8852500B2 (en) 2006-03-20 2014-10-07 National Institute For Materials Science Ni-base superalloy, method for producing the same, and turbine blade or turbine vane components
CH701415A1 (de) 2009-07-09 2011-01-14 Alstom Technology Ltd Nickel-Basis-Superlegierung.
CH702642A1 (de) * 2010-02-05 2011-08-15 Alstom Technology Ltd Nickel-Basis-Superlegierung mit verbessertem Degradationsverhalten.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) † 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties
JP2001294959A (ja) † 2000-04-17 2001-10-26 Mitsubishi Heavy Ind Ltd 単結晶Ｎｉ基耐熱合金およびタービン翼
EP1184473B1 (fr) † 2000-08-30 2005-01-05 Kabushiki Kaisha Toshiba Alliages monocristallins à base de nickel et méthode de fabriction et éléments d'un turbine à gaz à des hautes températures à partir de ceux-ci
EP1319729A1 (fr) † 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel
EP1900839A1 (fr) † 2006-09-07 2008-03-19 ALSTOM Technology Ltd Procédé pour le traitement thermique de superalliages à base de Ni

Also Published As

Publication number Publication date
JP5595495B2 (ja) 2014-09-24
RU2012104486A (ru) 2013-08-20
US20120128527A1 (en) 2012-05-24
EP2451986B1 (fr) 2013-08-21
EP2451986A1 (fr) 2012-05-16
WO2011003804A1 (fr) 2011-01-13
CH701415A1 (de) 2011-01-14
RU2525952C2 (ru) 2014-08-20
JP2012532982A (ja) 2012-12-20
US9017605B2 (en) 2015-04-28

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