EP2725110B1 - Superalliage à base de nickel sans rhénium résistant au fluage - Google Patents

Superalliage à base de nickel sans rhénium résistant au fluage Download PDF

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Publication number
EP2725110B1
EP2725110B1 EP12190156.5A EP12190156A EP2725110B1 EP 2725110 B1 EP2725110 B1 EP 2725110B1 EP 12190156 A EP12190156 A EP 12190156A EP 2725110 B1 EP2725110 B1 EP 2725110B1
Authority
EP
European Patent Office
Prior art keywords
nickel
content
based alloy
matrix
alloy
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
EP12190156.5A
Other languages
German (de)
English (en)
Other versions
EP2725110A1 (fr
Inventor
Ralf RETTIG
Robert F. Singer
Harald Helmer
Steffen Neumeier
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
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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 ES12190156.5T priority Critical patent/ES2625825T3/es
Priority to EP12190156.5A priority patent/EP2725110B1/fr
Priority to US14/061,190 priority patent/US9580774B2/en
Publication of EP2725110A1 publication Critical patent/EP2725110A1/fr
Application granted granted Critical
Publication of EP2725110B1 publication Critical patent/EP2725110B1/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%
    • 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%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion

Definitions

  • the present invention relates to a nickel-base alloy which is substantially free of rhenium, but at the same time achieves the creep resistance properties of the second-generation nickel-base super alloys.
  • nickel-base superalloys are used, for example, as blade materials, since these materials still have sufficient strength for the high mechanical loads even at high operating temperatures.
  • turbine blades are exposed in stationary gas turbines or jet engines in airliners an exhaust gas flow at temperatures of up to 1500 ° C and at the same time are subject to very high mechanical loads due to centrifugal forces. Under these conditions, it is particularly important that the creep resistance of the material used meets the requirements.
  • turbine blades In order to further increase the creep resistance, turbine blades have also been produced monocrystalline for several decades in order to further improve creep resistance by avoiding grain boundaries.
  • the alloys In the nickel-base superalloys of the so-called second and third generation currently in use, the alloys usually have the chemical element rhenium in a proportion of three or six percent by weight, since rhenium further improves creep resistance.
  • the alloy should be economical and efficient to produce and in particular easily castable and monocrystalline or directionally solidified.
  • the invention is based on the finding that rhenium contributes to the nickel-base superalloys in particular for solid-solution hardening of the ⁇ -matrix of the nickel-base super alloys. In order to be able to replace rhenium effectively, therefore, an alloying component must be present, which takes on the task of solid solution hardening of rhenium.
  • the invention addresses this point and suggests that tungsten can be used as an efficient solid solution hardener in the alloy.
  • tungsten is usually present not only in the ⁇ -matrix of nickel-base superalloys, but also in the precipitated ⁇ '-phases, which are usually formed by Ni 3 Al or Ni 3 Ti or mixtures thereof. This is where the invention starts by proposing nickel-base super alloys in which the alloy composition is optimized under given boundary conditions in such a way that the tungsten content in the ⁇ matrix is greater than in the precipitated ⁇ 'phases.
  • the boundary condition is a chemical composition of the alloy with an aluminum content of 11 to 11.2 at.%, Cobalt of 9.1 to 9.3 at.%, Chromium of 6 to 6.2 at. %, Molybdenum from 0.85 to 1.0 at.%, Tantalum from 3.3 to 3.5 at.%, Titanium from 1.5 to 1.7 at.%, Tungsten from 2.8 up to 3 at .-% and the rest nickel and unavoidable Impurities is given.
  • Such an alloy should continue to have as boundary condition a solidus temperature of more than 1320 ° C and the proportion of ⁇ '-phase should in the range of 40 to 50 vol .-%, in particular 44 to 46 vol .-% at a temperature in the range from 1050 ° C to 1100 ° C.
  • it should be stipulated as a boundary condition that the ⁇ / ⁇ 'mismatch at temperatures of 1050 ° C to 1100 ° C is in the range of -0.15% to -0.25%.
  • the ⁇ / ⁇ 'mismatch is defined as the normalized difference of the lattice constants of the two phases ⁇ and ⁇ ': a ⁇ ' - a ⁇ 1 / 2 * a ⁇ ' + a ⁇
  • the composition is selected such that the proportion of tungsten in the ⁇ matrix is greater than in the ⁇ 'phase.
  • An alloy having such a composition with a correspondingly high tungsten content in the ⁇ -matrix has the required mechanical strength at high temperatures and in particular the required creep resistance.
  • the composition of the alloy can be varied within the specified limits.
  • the alloy composition can be chosen so that at a temperature of 1050 ° C to 1100 ° C, the tungsten content in the ⁇ -matrix is ⁇ 3.5 at .-%.
  • the chemical composition is chosen so that the tungsten content in the ⁇ -matrix is maximum.
  • the tantalum content and the titanium content can be adjusted together to a value of ⁇ 3 at .-%, preferably ⁇ 4.5 at .-%, in particular ⁇ 5 at .-%.
  • a nickel-based alloy according to the present invention may have the following chemical composition: as well as the balance of nickel and unavoidable impurities.
  • the sulfur content may be limited to values of 2 ppm, in particular 1 ppm (parts per million) of sulfur and below in order to further improve the mechanical properties.
  • alloy according to the invention in particular articles, such as components of gas turbines, preferably turbine blades, and the like can be produced, which can be formed monocrystalline or directionally solidified.
  • the attached figure shows a Larson - Miller plot to illustrate the creep resistance of the alloy according to the invention in comparison with known alloys and a comparative alloy.
  • an alloy was prepared, the composition of which can be taken from the following table (Alloy 3). Alloys 1 and 2 were chosen as comparison alloys, alloy 1 being essentially of the same chemical composition as CMSX - 4 and alloy 2 being an alloy of a similar composition to CMSX - 4 but reduced by rhenium is. The constituents of the alloys are given in the table in percent by weight. alloy al Co Cr Not a word Ta Ti W re Hf Ni Alloy 1 5.6 9.0 6.5 0.6 6.5 1.0 6.0 3.0 0.1 rest Alloy 2 6.1 8.9 5.3 1.0 6.7 0.0 6.2 0.0 0.0 rest Alloy 3 4.8 8.6 5 1.4 10.1 1.3 8.8 0.0 0.0 rest
  • the alloy 3 according to the invention has a creep resistance similar to that of alloy 1, that of a nickel-base super alloy the second generation.
  • Alloy 2 has a much lower creep resistance, which is due to the lack of rhenium content and the lack of optimization of the alloy composition according to the present invention.
  • the teachings of the present invention can provide nickel-base superalloys that can dispense with the poorly-available element rhenium, yet provide high-temperature mechanical properties such as creep resistance, such as known rhenium-containing alloys.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Alliage à base de Nickel, qui est exempt de rhénium et présente une température de solidus de plus de 1320 °C, dans lequel des précipitations d'une phase γ' dans une matrice γ se présentent en fraction de 40 à 50 % en volume à des températures de 1050 °C à 1100 °C et l'ajustement erroné de γ/γ' à des températures de 1050 °C à 1100 °C se situe dans la plage de -0,15 % à -0,25 % et la composition chimique présente :
    de l'aluminium à raison de 11 à 11,2 % atomique,
    du cobalt à raison de 9,1 à 9,3 % atomique,
    du chrome à raison de 6 à 6,2 % atomique,
    du molybdène à raison de 0,85 à 1,0 % atomique,
    du tantale à raison de 3,3 à 3,5 % atomique,
    du titane à raison de 1,5 à 1,7 % atomique,
    du tungstène à raison de 2,8 à 3 % atomique, ainsi que
    du nickel pour le restant et des impuretés inévitables, dans lequel :
    la teneur en tungstène dans la matrice γ est supérieure à celle des phases γ' précipitées.
  2. Alliage à base de nickel selon la revendication 1,
    caractérisé en ce que
    la teneur en tungstène dans la matrice γ à une température de 1100 °C est supérieure à 3,5 % atomique.
  3. Alliage à base de nickel selon la revendication 1 ou 2,
    caractérisé en ce que
    la teneur en tungstène dans la matrice γ est maximale en fonction des autres composants d'alliage.
  4. Alliage à base de nickel selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    la teneur en tungstène et la teneur en molybdène dans la matrice γ constituent conjointement plus de 5 % atomique.
  5. Alliage à base de nickel selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    à une teneur en aluminium minimale, une teneur en tantale maximale et une teneur en titane moyenne sont réglées.
  6. Alliage à base de nickel selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    la teneur en tantale et la teneur en titane sont conjointement supérieures ou égales à 3 % atomique, de préférence à 4,5 % atomique, en particulier supérieures ou égales à 5 % atomique.
  7. Alliage à base de nickel selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    la teneur en soufre est inférieure ou égale à 2 ppm, de préférence inférieure ou égale à 1 ppm.
  8. Objet constitué d'un alliage à base de nickel selon l'une quelconque des revendications précédentes.
  9. Objet selon la revendication 8,
    caractérisé en ce que
    l'objet est solidifié en mode monocristallin ou de manière dirigée.
  10. Objet selon la revendication 8 ou 9,
    caractérisé en ce que
    l'objet est un composant, en particulier une pale d'une turbine à gaz ou d'un groupe motopropulseur.
EP12190156.5A 2012-10-26 2012-10-26 Superalliage à base de nickel sans rhénium résistant au fluage Not-in-force EP2725110B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES12190156.5T ES2625825T3 (es) 2012-10-26 2012-10-26 Súper-aleación a base de níquel exenta de renio y resistente a la fluencia
EP12190156.5A EP2725110B1 (fr) 2012-10-26 2012-10-26 Superalliage à base de nickel sans rhénium résistant au fluage
US14/061,190 US9580774B2 (en) 2012-10-26 2013-10-23 Creep-resistant, rhenium-free nickel base superalloy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12190156.5A EP2725110B1 (fr) 2012-10-26 2012-10-26 Superalliage à base de nickel sans rhénium résistant au fluage

Publications (2)

Publication Number Publication Date
EP2725110A1 EP2725110A1 (fr) 2014-04-30
EP2725110B1 true EP2725110B1 (fr) 2017-05-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP12190156.5A Not-in-force EP2725110B1 (fr) 2012-10-26 2012-10-26 Superalliage à base de nickel sans rhénium résistant au fluage

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US (1) US9580774B2 (fr)
EP (1) EP2725110B1 (fr)
ES (1) ES2625825T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150308449A1 (en) * 2014-03-11 2015-10-29 United Technologies Corporation Gas turbine engine component with brazed cover
EP2927336A1 (fr) 2014-04-04 2015-10-07 MTU Aero Engines GmbH Alliage à base de nickel à propriétés matricielles optimisées
ES2682362T3 (es) 2015-05-05 2018-09-20 MTU Aero Engines AG Superaleación a base de níquel exenta de renio con baja densidad

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4582548A (en) * 1980-11-24 1986-04-15 Cannon-Muskegon Corporation Single crystal (single grain) alloy
US6039920A (en) * 1997-05-12 2000-03-21 W. C. Heraeus Gmbh & Co. Kg Process for making rhenium-containing alloys
JP2000144289A (ja) * 1998-11-02 2000-05-26 United Technol Corp <Utc> 安定に熱処理可能なニッケル基超合金単結晶物体及び組成物並びにガスタービン用部品
DE19983957B4 (de) * 1999-06-02 2008-08-21 Alstom Beschichtungszusammensetzung für Hochtemperturschutz
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
US20130230405A1 (en) 2007-08-31 2013-09-05 Kevin Swayne O'Hara Nickel base superalloy compositions being substantially free of rhenium and superalloy articles
US8876989B2 (en) 2007-08-31 2014-11-04 General Electric Company Low rhenium nickel base superalloy compositions and superalloy articles
US20100135846A1 (en) * 2008-12-01 2010-06-03 United Technologies Corporation Lower cost high strength single crystal superalloys with reduced re and ru content
US20110076182A1 (en) * 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
US20110076181A1 (en) 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
US20110076180A1 (en) 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles

Also Published As

Publication number Publication date
US9580774B2 (en) 2017-02-28
ES2625825T3 (es) 2017-07-20
US20140119941A1 (en) 2014-05-01
EP2725110A1 (fr) 2014-04-30

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