EP3133178B1 - Superalliage a base de nickel optimise - Google Patents

Superalliage a base de nickel optimise Download PDF

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Publication number
EP3133178B1
EP3133178B1 EP15181489.4A EP15181489A EP3133178B1 EP 3133178 B1 EP3133178 B1 EP 3133178B1 EP 15181489 A EP15181489 A EP 15181489A EP 3133178 B1 EP3133178 B1 EP 3133178B1
Authority
EP
European Patent Office
Prior art keywords
nickel
equal
alloy
based alloy
less
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
EP15181489.4A
Other languages
German (de)
English (en)
Other versions
EP3133178A1 (fr
Inventor
Thomas GÖHLER
Ralf RETTIG
Robert F. Singer
Nils Ritter
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 ES15181489.4T priority Critical patent/ES2684780T3/es
Priority to EP15181489.4A priority patent/EP3133178B1/fr
Priority to US15/234,072 priority patent/US20170051382A1/en
Publication of EP3133178A1 publication Critical patent/EP3133178A1/fr
Application granted granted Critical
Publication of EP3133178B1 publication Critical patent/EP3133178B1/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
    • 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 a nickel-based alloy, in particular a nickel-based superalloy for high-temperature applications, preferably for use in turbomachines, such as aircraft engines, and a corresponding component of a turbomachine, in particular an aircraft engine made of such a nickel-based alloy.
  • nickel-base alloy is meant a material that has nickel in the main component.
  • a special embodiment of nickel-base alloys are nickel-based superalloys, which are understood to mean alloys which, owing to their particular composition and microstructure formation, can be used at high temperatures up to their melting point.
  • nickel-based alloy as used hereinafter, thus also encompasses the term nickel-base superalloy.
  • Nickel base superalloys are used in high temperature applications, e.g. B. in the construction of stationary gas turbines or aircraft engines, used because of their high temperature strength.
  • High-temperature application is understood to mean an application in which the operating temperature of a component produced from the alloy lies in a temperature range above half the melting temperature of the alloy.
  • the nickel base superalloys owe their good high temperature properties, and in particular their excellent high temperature strength, to a special microstructure characterized by a y matrix and ⁇ 'precipitates embedded therein.
  • the cubic face - centered y - phase of the matrix consists of the main constituent nickel as well as elements such as cobalt, chromium, molybdenum, rhenium and tungsten, which are added to nickel - base superalloys.
  • alloying constituents as tungsten, rhenium and molybdenum, solid solution strengthening of the y-matrix is achieved which gives the alloy strength in addition to precipitation hardening with the ⁇ 'precipitates.
  • the alloy constituents rhenium, tungsten and molybdenum additionally produce, in addition to the solid solution hardening of the y matrix, a stabilization of the ⁇ 'precipitates and counter their coarsening, which would lead to a decrease in the creep resistance.
  • TCP topologically closed packed
  • the ⁇ 'precipitation phases usually also have a cubic face centered structure with the composition Ni 3 (Al, Ti, Ta, Nb).
  • the strength of nickel-based superalloys can be increased by the formation of carbides that stabilize the grain boundaries and thus contribute to creep resistance.
  • nickel-base superalloys in high-temperature applications, such as the composition with respect to the refractory metals cobalt, chromium, molybdenum, rhenium and tungsten as mixed crystal former and the proportions of aluminum, tantalum and titanium selected as constituents of the ⁇ 'precipitates becomes.
  • the optimum composition of the alloying elements is important.
  • the density of the alloy should be kept as low as possible and a good and easy production and processability of the alloy can be ensured.
  • the present invention proposes providing an optimized composition of a nickel-based alloy, in particular with regard to the alloying elements cobalt, rhenium, tungsten, tantalum, aluminum and titanium, since these alloying elements considerably increase the structure and microstructure formation and the corresponding mechanical properties of the alloy influence.
  • the nickel content of the alloy is the main constituent of the alloy, ie the constituent which has the highest content in wt.% Or at.% Of the alloy. It goes without saying that the corresponding alloy is always present only to 100%, so that no addition of the limits of the specified ranges of shares can be made in such a way that the composition of the alloy would make up less or more than 100%, or nickel not the corresponding largest would make a contribution. Rather, with the use of an alloying element with a high proportion, a corresponding reduction of other alloying elements must be carried out with a proportion corresponding to that stated.
  • the nickel-based alloy is characterized in particular by the fact that the proportion of tantalum is always greater than or equal to the proportion of aluminum, so that the ratio of the proportions of tantalum to aluminum in wt .-% is greater than or equal to 1, so c (Ta) / c (Al) ⁇ 1.
  • the ratio of tantalum to aluminum in wt.% Should be less than or equal to 2. It has been shown that an improved distribution of tungsten and molybdenum between the ⁇ matrix and the ⁇ 'precipitates is achievable, so that the proportion of tungsten and / or molybdenum in the ⁇ matrix is greater than in the ⁇ '. - excretions.
  • the ratio of the proportions of cobalt to tungsten in wt.% Is set to be greater than or equal to 2 and less than or equal to 5, because by increasing the cobalt content, an improvement in segregation performance, ie lower casting segregation and higher degree of homogenization achievable so that shorter or easier solution annealing cycles can be used.
  • the strength can be increased or the total tungsten content can be reduced while solid solution hardening remains the same, which in particular also has an advantageous effect on the density of the alloy.
  • the ratio of the proportions of cobalt to tungsten in% by weight can be less than or equal to 4.
  • the nickel-base alloy can be adjusted so that the ratio of the proportions of tungsten to molybdenum in wt.% Is greater than or equal to 1 and less than or equal to 4. In this way too, the goals of avoiding casting segregation, avoiding the formation of TCP phases, and better distribution of tungsten and molybdenum between the ⁇ matrix and the ⁇ 'precipitates can be achieved.
  • the ratio of the proportions of cobalt to rhenium in wt.% Greater than or equal to 1 and less than or equal to 2 can be selected.
  • the essential mechanical components for the mechanical properties aluminum, cobalt, chromium, molybdenum, rhenium, ruthenium, tantalum, titanium and / or tungsten may in particular with 5.0 to 7.0%, especially 5.5 to 6.0% Al and / or 10.5 to 15.0%, in particular 11.0 to 12.0% Co and / or 4.0 to 6.0%, especially 4.5 to 5.5% Cr and / or 1.1 to 2.5%, especially 1.1 to 2.0% Mo and / or 5.5 to 7.0%, especially 5.7 to 6.5% Re and / or 3.1 to 5.5%, especially 3.3 to 5.0% Ru and / or 5.0 to 9.0%, especially 5.5 to 8.0% Ta and / or 0 to 2.0%, especially 0.5 to 2.0%, preferably 1.1 to 1.7% Ti and / or 3.0 to 4.5%, in particular 3.5 to 4.5% W are zulegiert.
  • a corresponding alloy may have a density ⁇ 8.94 g per cm 3 , in particular ⁇ 8.85 g per cm 3, and preferably ⁇ 8.8 g per cm 3 .
  • the nickel-based alloy of the present invention can be used both monocrystalline and directionally solidified, wherein monocrystalline components are used in particular for high-temperature applications in aircraft engine construction.
  • the table below shows the composition of four alloys according to the invention with regard to the main constituents aluminum, cobalt, chromium, molybdenum, rhenium, ruthenium, tantalum, titanium, tungsten with the remainder nickel in% by weight, where further constituents, such as carbon, silicon, Manganese, phosphorus, sulfur, boron, copper, iron, hafnium, zirconium and yttrium may be present in total at a level of less than 0.7% by weight.
  • alloys have the properties given in the table below.
  • the highest possible MKH index is advantageous for the formation of a creep resistant and high temperature resistant alloy.
  • the proportion of alloying elements in the matrix can be determined by measurements using an atomic probe or a transmission electron microscope.

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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 (9)

  1. Alliage à base de nickel, destiné à des applications à haute température, en particulier en vue d'une utilisation dans des turbomachines, comprenant une composition chimique comprenant en pourcentage en poids : Al 3,7 à 7,0 Co 10 à 20 Cr 2,1 à 7,2 Mo 1,1 à 3,0 Re 5,5 à 9,2 Ru 3,1 à 8,5 Ta 4,1 à 11,9 Ti 0 à 3,3 W 2,1 à 4,9 C 0 à 0,05 Si 0 à 0,1 Mn 0 à 0,05 P 0 à 0,015 S 0 à 0,001 B 0 à 0,003 Cu 0 à 0,05 Fe 0 à 0,15 Hf 0 à 0,15 Zr 0 à 0,015 Y 0 à 0,001
    et le reste étant du nickel et des impuretés inévitables, le rapport de la proportion de Ta à la proportion de Al en pourcentage en poids étant supérieur ou égal 1 et inférieur ou égal à 2 et le rapport de la proportions de Co à la proportion de W en pourcentage en poids étant supérieur ou égal à 2 et inférieur ou égal à 5.
  2. Alliage à base de nickel selon la revendication 1,
    caractérisé en ce que
    le rapport de la proportion de Co à la proportion de W en pourcentage en poids est inférieur ou égal à 4.
  3. Alliage à base de nickel selon l'une des revendications précédentes,
    caractérisé en ce que
    le rapport de la proportion de W à la proportion de Mo en pourcentage en poids est supérieur ou égal à 1 et inférieur ou égal à 4.
  4. Alliage à base de nickel selon l'une des revendications précédentes,
    caractérisé en ce que
    le rapport de la proportion de Co à la proportion de Re en pourcentage en poids est supérieur ou égal à 1 et inférieur ou égal à 2.
  5. Alliage à base de nickel selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    l'alliage à base de nickel comporte, en pourcentage en poids,
    5,0 à 7,0 %, en particulier 5,5 à 6,0 % d'AI et/ou
    10,5 à 15,0 %, en particulier 11,0 à 12,0 % de Co et/ou
    4,0 à 6,0 %, en particulier 4,5 à 5,5 % de Cr et/ou
    1,1 à 2,5 %, en particulier 1,1 à 2,0 % de Mo et/ou
    5,5 à 7,0 %, en particulier 5,7 à 6,5 % de Re et/ou
    3,1 à 5,5 %, en particulier 3,3 à 5,0 % de Ru et/ou
    5,0 à 9,0 %, en particulier 5,5 à 8,0 % de Ta et/ou
    0 à 2,0 %, en particulier 0,5 à 2,0 %, de préférence de 1,1 à 1,7 %, de Ti et/ou
    3,0 à 4,5 %, en particulier 3,5 à 4,5 % de W.
  6. Alliage à base de nickel selon l'une des revendications précédentes,
    caractérisé en ce que
    la densité de l'alliage est inférieure ou égale à 9,09 g/cm3, en particulier inférieure ou égale à 8,94 g/cm3, de préférence inférieure ou égale à 8,85 g/cm3, plus préférablement inférieure ou égale à 8,80 g/cm3.
  7. Alliage à base de nickel selon l'une des revendications précédentes,
    caractérisé en ce que
    l'alliage comprend une matrice y et des précipités γ', la proportion de W et/ou de Mo dans la matrice y étant supérieure à celle des précipités γ'.
  8. Composant d'une turbomachine, en particulier d'un moteur d'avion, qui comprend un alliage à base de nickel selon l'une des revendications précédentes.
  9. Composant selon la revendication 8,
    caractérisé en ce que
    l'alliage à base de nickel est conçu pour être monocristallin ou à solidification dirigée.
EP15181489.4A 2015-08-19 2015-08-19 Superalliage a base de nickel optimise Not-in-force EP3133178B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES15181489.4T ES2684780T3 (es) 2015-08-19 2015-08-19 Superaleación basada en níquel optimizada
EP15181489.4A EP3133178B1 (fr) 2015-08-19 2015-08-19 Superalliage a base de nickel optimise
US15/234,072 US20170051382A1 (en) 2015-08-19 2016-08-11 Optimized nickel-based superalloy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15181489.4A EP3133178B1 (fr) 2015-08-19 2015-08-19 Superalliage a base de nickel optimise

Publications (2)

Publication Number Publication Date
EP3133178A1 EP3133178A1 (fr) 2017-02-22
EP3133178B1 true EP3133178B1 (fr) 2018-08-01

Family

ID=53886954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15181489.4A Not-in-force EP3133178B1 (fr) 2015-08-19 2015-08-19 Superalliage a base de nickel optimise

Country Status (3)

Country Link
US (1) US20170051382A1 (fr)
EP (1) EP3133178B1 (fr)
ES (1) ES2684780T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2768947C1 (ru) * 2021-06-24 2022-03-25 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение (ПАО "ОДК-УМПО") Жаропрочный никелевый сплав для литья деталей с монокристаллической структурой

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4012061A1 (fr) 2020-12-09 2022-06-15 MTU Aero Engines AG Alliage à base de nickel et composant le contenant
EP4032997A1 (fr) 2021-01-26 2022-07-27 MTU Aero Engines AG Alliage à base de nickel et composant fabriqué à partir de celui-ci

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5482789A (en) * 1994-01-03 1996-01-09 General Electric Company Nickel base superalloy and article
US6444057B1 (en) * 1999-05-26 2002-09-03 General Electric Company Compositions and single-crystal articles of hafnium-modified and/or zirconium-modified nickel-base superalloys
US6966956B2 (en) * 2001-05-30 2005-11-22 National Institute For Materials Science Ni-based single crystal super alloy
US6921586B2 (en) * 2002-02-05 2005-07-26 General Electric Company Ni-Base superalloy having a coating system containing a diffusion barrier layer
RU2415959C1 (ru) * 2007-03-12 2011-04-10 АйЭйчАй КОРПОРЕЙШН МОНОКРИСТАЛЛИЧЕСКИЙ СУПЕРСПЛАВ НА ОСНОВЕ Ni И СОДЕРЖАЩАЯ ЕГО ЛОПАТКА ТУРБИНЫ

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2768947C1 (ru) * 2021-06-24 2022-03-25 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение (ПАО "ОДК-УМПО") Жаропрочный никелевый сплав для литья деталей с монокристаллической структурой

Also Published As

Publication number Publication date
ES2684780T3 (es) 2018-10-04
US20170051382A1 (en) 2017-02-23
EP3133178A1 (fr) 2017-02-22

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