EP0237378B1 - Superalliage à matrice à base de nickel notamment élaboré en métallurgie des poudres et disque de turbomachine constitué en cet alliage - Google Patents

Superalliage à matrice à base de nickel notamment élaboré en métallurgie des poudres et disque de turbomachine constitué en cet alliage Download PDF

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Publication number
EP0237378B1
EP0237378B1 EP87400262A EP87400262A EP0237378B1 EP 0237378 B1 EP0237378 B1 EP 0237378B1 EP 87400262 A EP87400262 A EP 87400262A EP 87400262 A EP87400262 A EP 87400262A EP 0237378 B1 EP0237378 B1 EP 0237378B1
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EP
European Patent Office
Prior art keywords
superalloy
nickel
alloy
based matrix
weight
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.)
Expired
Application number
EP87400262A
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German (de)
English (en)
French (fr)
Other versions
EP0237378A1 (fr
Inventor
Christian Ducrocq
Didier Pierre Albert Lestrat
Bernard Paintendre
James Henry Davidson
Michel Marty
André Walder
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.)
Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Office National dEtudes et de Recherches Aerospatiales ONERA
Safran Aircraft Engines SAS
TECPHY
Original Assignee
Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Office National dEtudes et de Recherches Aerospatiales ONERA
Imphy SA
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
TECPHY
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Publication date
Application filed by Association pour la Recherche et le Developpement des Methodes et Processus Industriels, Office National dEtudes et de Recherches Aerospatiales ONERA, Imphy SA, Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, TECPHY filed Critical Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Publication of EP0237378A1 publication Critical patent/EP0237378A1/fr
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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
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%

Definitions

  • the present invention relates to a new family of nickel-based superalloys having the properties noted above, characterized in that the chemical composition in weight percentages, belongs to the following field: the remainder being essentially nickel.
  • these superalloys according to the invention are capable of being implemented by powder metallurgy techniques and the turbomachine disks constitute an interesting application.
  • the nickel-based superalloys generally have an essentially two-phase structure with: - a phase y of Ni, Co hardened mainly by elements in solid solution (W, Cr, Mo) - a hardening phase y of type A s B in which A is mainly formed of Ni, Co, Cr and B of AI, Ti Nb, Ta, Hf, V, Ta.
  • Tantalum also has, with respect to niobium, the disadvantage of increasing the density more strongly.
  • the alloys of the present invention do not contain Ta and are limited to 1.5% of Nb.
  • the invention provides contents of AI and Ti such that their ratio is close to 1 because, if it is known that Ti is a more favorable element than AI for the curing of the y phase beyond 650 ° C, it very quickly increases the solid solution re-temperature of this phase, making the implementation of the alloy difficult. For the same reason the sum of the elements AI + Ti is limited to 10% by weight.
  • Additional hardening may be obtained by the addition of Hf, up to a limit of 1% for processing reasons (reduction of the solidus and increase of the solvus Y).
  • the alloys of the present invention do not contain vanadium.
  • the present invention recommends a Mo content of between 6 and 8% by weight which, as shown in Table 2 (see in particular the examples of alloys according to the invention N 14 and N 16), results in high resistance values in tension and creep, the alloy nevertheless retains particularly low cracking fatigue-creep rates.
  • the invention recommends a chromium content of between 11 and 13% by weight.
  • Boron and carbon are known elements which can improve the creep resistance, but taking into account the chromium and molybdenum contents of the invention, and in order to avoid the excessive formation of carbides and borides, the invention limits their concentration by weight at 500 ppm.
  • Zirconium may be useful for fixing possible embrittling traces of sulfur, but the invention however limits its content to 500 ppm by weight to avoid the formation of phases with a low melting point.
  • Other elements such as Mg, Ca, Si, Y etc ... often used for the development of the alloy, can remain present at the level of traces without harming the properties of the alloys according to the invention.
  • superalloys in accordance with the invention can use any method such as to avoid the appearance of major segregations of the kind which appear when such alloys are used according to conventional foundry methods.
  • production of superalloys according to the invention can in particular be obtained by the known techniques of powder metallurgy and parts made of these alloys such as turbomachine rotor discs can for example be manufactured by known isostatic compaction processes with hot.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP87400262A 1986-02-06 1987-02-05 Superalliage à matrice à base de nickel notamment élaboré en métallurgie des poudres et disque de turbomachine constitué en cet alliage Expired EP0237378B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8601604A FR2593830B1 (fr) 1986-02-06 1986-02-06 Superalliage a matrice a base de nickel notamment elabore en metallurgie des poudres et disque de turbomachine constitue en cet alliage
FR8601604 1986-02-06

Publications (2)

Publication Number Publication Date
EP0237378A1 EP0237378A1 (fr) 1987-09-16
EP0237378B1 true EP0237378B1 (fr) 1989-09-13

Family

ID=9331852

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87400262A Expired EP0237378B1 (fr) 1986-02-06 1987-02-05 Superalliage à matrice à base de nickel notamment élaboré en métallurgie des poudres et disque de turbomachine constitué en cet alliage

Country Status (6)

Country Link
US (1) US5104614A (enrdf_load_stackoverflow)
EP (1) EP0237378B1 (enrdf_load_stackoverflow)
JP (1) JPS6369935A (enrdf_load_stackoverflow)
CA (1) CA1312483C (enrdf_load_stackoverflow)
DE (1) DE3760560D1 (enrdf_load_stackoverflow)
FR (1) FR2593830B1 (enrdf_load_stackoverflow)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2299919C1 (ru) * 2006-03-02 2007-05-27 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Порошковый жаропрочный сплав на основе никеля
RU2348726C1 (ru) * 2007-08-27 2009-03-10 Открытое акционерное общество "Всероссийский Институт Легких сплавов" (ОАО ВИЛС) Жаропрочный порошковый сплав на основе никеля
RU2368683C1 (ru) * 2008-03-05 2009-09-27 Открытое акционерное общество "Всероссийский Институт Легких сплавов" (ОАО ВИЛС) Порошковый жаропрочный никелевый сплав
US11434300B2 (en) 2014-03-19 2022-09-06 Regeneron Pharmaceuticals, Inc. Methods and antibody compositions for tumor treatment

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1045607A (zh) * 1989-03-15 1990-09-26 中国科学院金属研究所 一种提高高温合金性能的方法
US5783318A (en) * 1994-06-22 1998-07-21 United Technologies Corporation Repaired nickel based superalloy
FR2726833B1 (fr) * 1994-11-16 1997-04-25 Snecma Procede de traitement thermique d'un superalliage a base de nickel
FR2737733B1 (fr) * 1995-08-09 1998-03-13 Snecma Superalliages a base de nickel stables a hautes temperatures
US6521175B1 (en) 1998-02-09 2003-02-18 General Electric Co. Superalloy optimized for high-temperature performance in high-pressure turbine disks
US6468368B1 (en) * 2000-03-20 2002-10-22 Honeywell International, Inc. High strength powder metallurgy nickel base alloy
DE60008116T2 (de) * 2000-09-29 2004-09-16 General Electric Co. Superlegierung mit optimiertem Hochtemperatur-Leistungsvermögen in Hochdruck-Turbinenscheiben
US6730264B2 (en) 2002-05-13 2004-05-04 Ati Properties, Inc. Nickel-base alloy
US6974508B1 (en) 2002-10-29 2005-12-13 The United States Of America As Represented By The United States National Aeronautics And Space Administration Nickel base superalloy turbine disk
US6969431B2 (en) * 2003-08-29 2005-11-29 Honeywell International, Inc. High temperature powder metallurgy superalloy with enhanced fatigue and creep resistance
US7156932B2 (en) * 2003-10-06 2007-01-02 Ati Properties, Inc. Nickel-base alloys and methods of heat treating nickel-base alloys
US20100008790A1 (en) * 2005-03-30 2010-01-14 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US7531054B2 (en) * 2005-08-24 2009-05-12 Ati Properties, Inc. Nickel alloy and method including direct aging
US7708846B2 (en) * 2005-11-28 2010-05-04 United Technologies Corporation Superalloy stabilization
FR2899240B1 (fr) * 2006-03-31 2008-06-27 Snecma Sa Alliage a base de nickel
US7985304B2 (en) * 2007-04-19 2011-07-26 Ati Properties, Inc. Nickel-base alloys and articles made therefrom
US8992700B2 (en) * 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
US8992699B2 (en) 2009-05-29 2015-03-31 General Electric Company Nickel-base superalloys and components formed thereof
US8177516B2 (en) * 2010-02-02 2012-05-15 General Electric Company Shaped rotor wheel capable of carrying multiple blade stages
FR2980485B1 (fr) * 2011-09-28 2014-07-04 Snecma Alliage a base de nickel
US9752215B2 (en) 2012-02-14 2017-09-05 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US9783873B2 (en) 2012-02-14 2017-10-10 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US9816159B2 (en) 2012-03-09 2017-11-14 Indian Institute Of Science Nickel-aluminium-zirconium alloys
US10563293B2 (en) 2015-12-07 2020-02-18 Ati Properties Llc Methods for processing nickel-base alloys
US20170291265A1 (en) 2016-04-11 2017-10-12 United Technologies Corporation Braze material for hybrid structures
US10718041B2 (en) 2017-06-26 2020-07-21 Raytheon Technologies Corporation Solid-state welding of coarse grain powder metallurgy nickel-based superalloys
FR3098849B1 (fr) 2019-07-16 2022-10-14 Safran Aircraft Engines Carter amélioré de module d’aéronef

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB733489A (en) * 1952-07-09 1955-07-13 Mond Nickel Co Ltd Improvements relating to nickel-chromium-cobalt alloys
US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part
BE756652A (fr) * 1969-09-26 1971-03-01 United Aircraft Corp Superalliages contenant des phases precipitees topologiquement d'assemblage serre
JPS49113707A (enrdf_load_stackoverflow) * 1973-02-15 1974-10-30
GB1512984A (en) * 1974-06-17 1978-06-01 Cabot Corp Oxidation resistant nickel alloys and method of making the same
JPS5128564A (en) * 1974-09-03 1976-03-10 Sugihide Kogyo Kk Senzai no sapuraisutando
DE2834222C3 (de) * 1978-08-04 1981-08-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verfahren zur Herstellung der Schaufel-Scheiben-Verbindung eines Turborotors
US4312682A (en) * 1979-12-21 1982-01-26 Cabot Corporation Method of heat treating nickel-base alloys for use as ceramic kiln hardware and product

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2299919C1 (ru) * 2006-03-02 2007-05-27 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Порошковый жаропрочный сплав на основе никеля
RU2348726C1 (ru) * 2007-08-27 2009-03-10 Открытое акционерное общество "Всероссийский Институт Легких сплавов" (ОАО ВИЛС) Жаропрочный порошковый сплав на основе никеля
RU2368683C1 (ru) * 2008-03-05 2009-09-27 Открытое акционерное общество "Всероссийский Институт Легких сплавов" (ОАО ВИЛС) Порошковый жаропрочный никелевый сплав
US11434300B2 (en) 2014-03-19 2022-09-06 Regeneron Pharmaceuticals, Inc. Methods and antibody compositions for tumor treatment

Also Published As

Publication number Publication date
JPH0581652B2 (enrdf_load_stackoverflow) 1993-11-15
FR2593830A1 (fr) 1987-08-07
DE3760560D1 (en) 1989-10-19
JPS6369935A (ja) 1988-03-30
CA1312483C (fr) 1993-01-12
EP0237378A1 (fr) 1987-09-16
FR2593830B1 (fr) 1988-04-08
US5104614A (en) 1992-04-14

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