EP2354261B1 - Superalliage à base de nickel ayant un comportement de dégradation amélioré - Google Patents

Superalliage à base de nickel ayant un comportement de dégradation amélioré Download PDF

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Publication number
EP2354261B1
EP2354261B1 EP11151997.1A EP11151997A EP2354261B1 EP 2354261 B1 EP2354261 B1 EP 2354261B1 EP 11151997 A EP11151997 A EP 11151997A EP 2354261 B1 EP2354261 B1 EP 2354261B1
Authority
EP
European Patent Office
Prior art keywords
nickel
alloy
ppm
superalloy
phase
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
EP11151997.1A
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German (de)
English (en)
Other versions
EP2354261A1 (fr
Inventor
Mohamed Nazmy
Claus Paul Gerdes
Andreas KÜNZLER
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2354261A1 publication Critical patent/EP2354261A1/fr
Application granted granted Critical
Publication of EP2354261B1 publication Critical patent/EP2354261B1/fr
Not-in-force legal-status Critical Current
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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, which is characterized by an improved degradation behavior.
  • SX alloy single-crystal components
  • DS alloy directionally solidified structure
  • Nickel-based 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 such as those made from US 4,643,782 .
  • EP 0 208 645 and US 5,270,123 mixed-crystal-hardening alloying elements, for example Re, W, Mo, Co, Cr, and ⁇ -phase-forming elements, for example Al, Ta, and Ti, are contained.
  • 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.
  • 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.
  • grain boundaries are particularly detrimental to the high temperature properties of the single crystal components. While small-angle grain boundaries are comparatively small in small components, they are highly relevant in terms of castability, mechanical properties, and high temperature oxidation behavior for large SX or DS devices.
  • Grain boundaries are areas of high local disorder of the crystal lattice, because neighboring grains collide in these areas and thus there is a certain disorientation between the crystal lattices.
  • the aim of the invention is to avoid the disadvantages mentioned.
  • the invention is based on the object to develop a nickel-based superalloy of the type described above, which is characterized by an improved degradation behavior, ie z. B. subsequent to a long-term mechanical stress at high temperatures subsequently at room temperature the highest possible (residual) strength / hardness is present.
  • this alloy has the very good properties (good castability, good oxidation resistance at high temperatures, good creep strength) of EP 1 359 231 B1 has known alloy, but which additionally has no drop in the yield strength at room temperature after a previous high temperature creep, so has a good degradation behavior.
  • Nickel-based superalloys having the chemical composition given in Table 1 were investigated (in% by weight): Table 1: Chemical composition of the investigated alloys comparative alloy (VL) Inventive alloy (L) Ni rest rest Cr 8th 8th Co 5 5 Not a word 2 2 W 8th 8th Ta 6 6 al 5 5 Ti 1.4 1.4 Pt - 0.5 Nb - 0.2 Si 0.1 0.1 B 0008 0008 C 12:02 12:02 Hf 0.1 0.1
  • Alloy L is a nickel base superalloy for single crystal components whose composition falls within the scope of the present invention and which is a particularly preferred embodiment.
  • the comparative alloy VL is known from the prior art ( EP 1 359 231 B1 ) known. It differs from the alloy according to the invention in that it is not alloyed with Pt and Nb.
  • Platinum and niobium are elements which according to the present invention in controlled small amounts (Pt: 0.1-0.6, preferably 0.5 wt .-%, Nb: 0.1-0.5, preferably 0.2 wt .-%) to the EP 1 359 231 B1 known alloy (with a corresponding reduction of the residual amount of Ni) are added. These two elements affect the size of the lattice mismatch between the ⁇ 'and ⁇ phases, which in turn is responsible for the morphological changes in the phases and the residual strength of the material after high temperature creep of nickel-based single crystal superalloys responsible for.
  • micro-alloying with Pt and Nb within the specified limits means that at high temperatures, the lattice offset between ⁇ 'and ⁇ phases is approximately zero. This causes a lower tendency of the ⁇ '-phase for raft formation or even a suppression of this tendency, ie the ⁇ '-phase remains spherical.
  • Fig. 1a shows the structure of the comparative alloy VL
  • Fig. 2a the structure of the inventive alloy L in the initial state.
  • the ⁇ '-phase is uniformly distributed in both samples in the matrix ( ⁇ -phase) and has an approximately spherical shape.
  • Fig. 1 Federation Fig. 2b show the structure for the comparative alloy ( Fig. 1 b) and the alloy according to the invention ( Fig. 2b ) after cold deformation (cold rolling) and subsequent aging treatment at high temperatures with the following parameters: 1050 ° C / 204 h.
  • Fig. 3 is the dependence of the Vickers hardness at room temperature on the respective microstructure state of the comparative alloy VL and the inventive alloy L according to the FIGS. 1a) and 1b ) or 2a) and 2b) applied.
  • On the left is the hardness HV2 of the initial state and on the right the hardness HV2 after the treatment of the material under degrading conditions (cold rolling and annealing at 1050 ° C / 204 h).
  • the hardness HV2 in the alloy according to the invention is about 10% better than in the case of the comparative alloy.
  • the hardness HV2 measured at room temperature is expected to be lower in the case of both alloys compared to the respective initial state, but still more than 5% higher in the case of the alloy L according to the invention than in the case of the comparative alloy VL.

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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 (3)

  1. Superalliage à base de nickel présentant un comportement de dégradation amélioré, caractérisé par la composition chimique suivante (données 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
    1,3 - 1,4 Ti
    0, 1 - 0,6 Pt
    0,1 - 0,5 Nb
    0,11 - 0,15 Si
    0,11 - 0,15 Hf
    200 - 750 ppm C
    50 - 400 ppm B,
    le reste étant du nickel et des impuretés dues à la fabrication.
  2. Superalliage à base de nickel selon la revendication 1, en particulier pour la fabrication de composants monocristallins, caractérisé par la composition chimique suivante (données 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
    1,3 - 1,4 Ti
    0,1 - 0,5 Pt
    0,1 - 0,2 Nb
    0,11 - 0,15 Si
    0,11 - 0, 15 Hf
    200 - 300 ppm C
    50 - 100 ppm B,
    le reste étant du nickel et des impuretés dues à la fabrication.
  3. Superalliage à base de nickel selon la revendication 2, caractérisé par la composition chimique suivante (données en % en poids):
    8 Cr
    5 Co
    2 Mo
    8 W
    6 Ta
    5 Al
    1,4 Ti
    0,5 Pt
    0,2 Nb
    0,1 Si
    0,1 Hf
    200 ppm C
    80 ppm B,
    le reste étant du nickel et des impuretés dues à la fabrication.
EP11151997.1A 2010-02-05 2011-01-25 Superalliage à base de nickel ayant un comportement de dégradation amélioré Not-in-force EP2354261B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH00142/10A CH702642A1 (de) 2010-02-05 2010-02-05 Nickel-Basis-Superlegierung mit verbessertem Degradationsverhalten.

Publications (2)

Publication Number Publication Date
EP2354261A1 EP2354261A1 (fr) 2011-08-10
EP2354261B1 true EP2354261B1 (fr) 2014-08-27

Family

ID=42077557

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11151997.1A Not-in-force EP2354261B1 (fr) 2010-02-05 2011-01-25 Superalliage à base de nickel ayant un comportement de dégradation amélioré

Country Status (5)

Country Link
US (1) US8696980B2 (fr)
EP (1) EP2354261B1 (fr)
JP (1) JP5787535B2 (fr)
CN (1) CN102146538B (fr)
CH (1) CH702642A1 (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.
FR2980485B1 (fr) * 2011-09-28 2014-07-04 Snecma Alliage a base de nickel
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
EP2949768B1 (fr) * 2014-05-28 2019-07-17 Ansaldo Energia IP UK Limited Précipitation gamma prime renforcée par un superalliage à base de nickel destinée à être utilisée dans un processus de fabrication d'additif à base de poudre

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1520630A (en) * 1974-07-08 1978-08-09 Johnson Matthey Co Ltd Platinum group metal-containing alloys
US4764225A (en) * 1979-05-29 1988-08-16 Howmet Corporation Alloys for high temperature applications
US4643782A (en) * 1984-03-19 1987-02-17 Cannon Muskegon Corporation Single crystal alloy technology
US4719080A (en) 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
GB2234521B (en) * 1986-03-27 1991-05-01 Gen Electric Nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries
US5435861A (en) 1992-02-05 1995-07-25 Office National D'etudes Et De Recherches Aerospatiales Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production
FR2686902B1 (fr) * 1992-02-05 1994-07-29 Onera (Off Nat Aerospatiale) Superalliage monocristallin a base de nickel a tenue a l'oxydation amelioree et procede de preparation.
US5270123A (en) * 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
CH695497A5 (de) * 2002-04-30 2006-06-15 Alstom Technology Ltd Nickel-Basis-Superlegierung.
JP4885530B2 (ja) * 2005-12-09 2012-02-29 株式会社日立製作所 高強度高延性Ｎｉ基超合金と、それを用いた部材及び製造方法

Also Published As

Publication number Publication date
JP2011162878A (ja) 2011-08-25
CH702642A1 (de) 2011-08-15
CN102146538B (zh) 2015-07-22
EP2354261A1 (fr) 2011-08-10
JP5787535B2 (ja) 2015-09-30
US8696980B2 (en) 2014-04-15
US20110194972A1 (en) 2011-08-11
CN102146538A (zh) 2011-08-10

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