EP3024957B1 - Superlegierungen und daraus geformte komponenten - Google Patents

Superlegierungen und daraus geformte komponenten Download PDF

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EP3024957B1
EP3024957B1 EP14762119.7A EP14762119A EP3024957B1 EP 3024957 B1 EP3024957 B1 EP 3024957B1 EP 14762119 A EP14762119 A EP 14762119A EP 3024957 B1 EP3024957 B1 EP 3024957B1
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gamma
nickel
weight percent
creep
base superalloy
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French (fr)
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EP3024957A1 (de
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David Paul Mourer
Richard Didomizio
Timothy Hanlon
Daniel Yeuching Wei
Andrew Ezekiel Wessman
Kenneth Rees Bain
Andrew Martin Powell
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General Electric Co
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General Electric Co
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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

Definitions

  • the present invention generally relates to nickel-base alloy compositions, and more particularly to nickel-base superalloys suitable for components requiring a polycrystalline microstructure and high temperature hold time (dwell) capability, for example, turbine disks of gas turbine engines.
  • the turbine section of a gas turbine engine is located downstream of a combustor section and contains a rotor shaft and one or more turbine stages, each having a turbine disk (rotor) mounted or otherwise carried by the shaft and turbine blades mounted to and radially extending from the periphery of the disk.
  • Components within the combustor and turbine sections are often formed of superalloy materials to provide acceptable mechanical properties while at elevated temperatures resulting from the hot combustion gases. Higher compressor exit temperatures in modern high pressure ratio gas turbine engines can also necessitate the use of high performance nickel superalloys for compressor disks, blisks, and other components.
  • Suitable alloy compositions and microstructures for a given component depend on the particular temperatures, stresses, and other conditions to which the component is subjected.
  • airfoil components such as blades and vanes are often formed of equiaxed, directionally solidified (DS), or single crystal (SX) superalloys
  • turbine disks are typically formed of superalloys that must undergo carefully controlled forging, heat treatments, and surface treatments such as peening to produce a polycrystalline microstructure having a controlled grain structure and desirable mechanical properties.
  • Turbine disks are often formed of gamma prime ( ⁇ ') precipitation-strengthened nickel-base superalloys (hereinafter, gamma prime nickel-base superalloys) containing chromium, tungsten, molybdenum, rhenium and/or cobalt as principal elements that combine with nickel to form the gamma ( ⁇ ) matrix, and contain aluminum, titanium, tantalum, niobium, and/or vanadium as principal elements that combine with nickel to form the desirable gamma prime precipitate strengthening phase, principally Ni 3 (Al,Ti).
  • gamma prime nickel-base superalloys include René 88DT (R88DT; U.S. Patent No.
  • René 104 R104; U.S. Patent No. 6,521,175
  • certain nickel-base superalloys commercially available under the trademarks Inconel®, Nimonic®, and Udimet®.
  • R88DT has a composition of, by weight, about 15.0-17.0% chromium, about 12.0-14.0% cobalt, about 3.5-4.5% molybdenum, about 3.5-4.5% tungsten, about 1.5-2.5% aluminum, about 3.2-4.2% titanium, about 0.5.0-1.0% niobium, about 0.010-0.060% carbon, about 0.010-0.060% zirconium, about 0.010-0.040% boron, about 0.0-0.3% hafnium, about 0.0-0.01 vanadium, and about 0.0-0.01 yttrium, the balance nickel and incidental impurities.
  • R104 has a nominal composition of, by weight, about 16.0-22.4% cobalt, about 6.6-14.3% chromium, about 2.6-4.8% aluminum, about 2.4-4.6% titanium, about 1.4-3.5% tantalum, about 0.9-3.0% niobium, about 1.9-4.0% tungsten, about 1.9-3.9% molybdenum, about 0.0-2.5% rhenium, about 0.02-0.10% carbon, about 0.02-0.10% boron, about 0.03-0.10% zirconium, the balance nickel and incidental impurities.
  • Disks and other critical gas turbine engine components are often forged from billets produced by powder metallurgy (P/M), conventional cast and wrought processing, and spraycast or nucleated casting forming techniques.
  • Powder metallurgy P/M
  • Gamma prime nickel-base superalloys formed by powder metallurgy are particularly capable of providing a good balance of creep, tensile, and fatigue crack growth properties to meet the performance requirements of turbine disks and certain other gas turbine engine components.
  • a powder of the desired superalloy undergoes consolidation, such as by hot isostatic pressing (HIP) and/or extrusion consolidation.
  • HIP hot isostatic pressing
  • the resulting billet is then isothermally forged at temperatures slightly below the gamma prime solvus temperature of the alloy to approach superplastic forming conditions, which allows the filling of the die cavity through the accumulation of high geometric strains without the accumulation of significant metallurgical strains.
  • These processing steps are designed to retain the fine grain size originally within the billet (for example, ASTM 10 to 13 or finer), achieve high plasticity to fill near-net-shape forging dies, avoid fracture during forging, and maintain relatively low forging and die stresses.
  • these alloys are then heat treated above their gamma prime solvus temperature (generally referred to as supersolvus heat treatment) to cause significant, uniform coarsening of the grains.
  • alloys such as R88DT and R104 have provided significant advances in high temperature capabilities of superalloys, further improvements are continuously being sought.
  • high temperature hold time (dwell) capability has emerged as an important factor for the high temperatures and stresses associated with more advanced military and commercial engine applications.
  • creep and crack growth characteristics of current alloys tend to fall short of the required capability to meet mission/life targets and requirements of advanced disk applications.
  • dwell creep and hold time
  • U.S. Patent Application Publication No. 2010/0303665 to Bain et al. is directed to gamma prime nickel-base superalloys capable of exhibiting improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior, when appropriately processed to form a component having a polycrystalline microstructure, most notably turbine disks of gas turbine engines.
  • a gamma-prime nickel-base superalloy that contains, by weight, 16.0 to 30.0% cobalt, 11.5 to 15.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 1.5 to 6.0% titanium, 1.0 to 5.0% tungsten, 1.0 to 5.0% molybdenum, up to 3.5% niobium, up to 1.0% hafnium, 0.02 to 0.20% carbon, 0.01 to 0.05% boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities.
  • the present invention provides a gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature capabilities, particularly creep at temperatures exceeding 1200°F (about 650°C).
  • a gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities.
  • the superalloy has a W+Nb-Cr value of at least -6 approaching zero, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 704°C (1300°F) and 689MPa (100 ksi) of at least 1000 hours.
  • a gamma-prime nickel-base superalloy contains, by weight: 17.0 to 20.5% cobalt; 10.5 to 12.5% chromium; 4.5 to 5.5% tantalum; 3.0 to 3.4% aluminum; 2.5 to 2.9% titanium; 3.0 to 5.0% tungsten; 2.5 to 3.0% molybdenum; 1.8 to 2.2% niobium; up to 0.6 hafnium; 0.048 to 0.068% carbon; 0.015 to 0.04% boron; 0.04 to 0.06% zirconium; the balance essentially nickel and impurities.
  • the superalloy has a W+Nb-Cr value of at least -6 approaching zero, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 704°C (1300°F) and 689MPa (100 ksi) of at least 1000 hours.
  • aspects of the invention include components that can be formed from the alloys described above, particular examples of which include turbine disks and compressor disks and blisks of gas turbine engines.
  • a significant advantage of the invention is the potential for balanced improvements in high temperature dwell properties, particularly improvements in creep characteristics at temperatures above 1200°F (about 650°C), while also having good producibility and good thermal stability. Improvements in other properties are also believed possible, particularly if appropriately processed using powder metallurgy, hot working, and heat treatment techniques.
  • the present invention is directed to gamma prime nickel-base superalloys, and particular those suitable for components produced by a hot working (e.g., forging) operation to have a polycrystalline microstructure.
  • a particular example represented in FIG. 1 is a high pressure turbine disk 10 for a gas turbine engine.
  • the invention will be discussed in reference to processing of a high-pressure turbine disk for a gas turbine engine, though those skilled in the art will appreciate that the teachings and benefits of this invention are also applicable to compressor disks and blisks of gas turbine engines, as well as numerous other components that are subjected to stresses at high temperatures and therefore require a high temperature dwell capability.
  • Disks of the type shown in FIG. 1 are typically produced by isothermally forging a fine-grained billet formed by powder metallurgy (PM), a cast and wrought processing, or a spraycast or nucleated casting type technique.
  • the billet can be formed by consolidating a superalloy powder, such as by hot isostatic pressing (HIP) or extrusion consolidation.
  • the billet is typically forged at a temperature at or near the recrystallization temperature of the alloy but less than the gamma prime solvus temperature of the alloy, and under superplastic forming conditions. After forging, a supersolvus (solution) heat treatment is performed, during which grain growth occurs.
  • the supersolvus heat treatment is performed at a temperature above the gamma prime solvus temperature (but below the incipient melting temperature) of the superalloy to recrystallize the worked grain structure and dissolve (solution) the gamma prime precipitates in the superalloy.
  • the component is cooled at an appropriate rate to re-precipitate gamma prime within the gamma matrix or at grain boundaries, so as to achieve the particular mechanical properties desired.
  • the component may also undergo aging using known techniques.
  • compositions were performed to identify those compositions that appear to have the desired mechanical property characteristics for meeting advanced turbine engine needs, including creep and hold time fatigue crack growth rate (HTFCGR).
  • the analytical investigations also made use of commercially-available software packages along with proprietary databases to predict phase volume fractions based on composition, allowing for the further definition of compositions that approach or in some cases slightly exceed undesirable equilibrium phase stability boundaries.
  • solution temperatures and preferred amounts of gamma prime and carbides were defined to identify compositions with desirable combinations of mechanical properties, phase compositions and gamma prime volume fractions, while avoiding undesirable phases that could reduce in-service capability if equilibrium phases sufficiently form due to in-service environment characteristics.
  • regression equations or transfer functions were developed based on selected data obtained from historical disk alloy development work.
  • the investigations also relied on qualitative and quantitative data of the aforementioned nickel-base superalloys R88DT and R104.
  • Bain et al. identified superalloy compositions capable of achieving considerable improvements in hold time properties as well as improvements in creep capabilities.
  • a particular aspect of the present invention was to identify superalloy compositions capable of further improvements in creep properties in comparison to HL11. For this purpose, time to 0.2% creep at temperatures above 1200°F (about 650°C) was identified as desirable, with improved creep at temperatures of at least 1300°F (about 705°C) being specifically targeted.
  • compositional parameters were maintained, including the inclusion of hafnium for high temperature strength, chromium levels of about 10 weight percent or more for corrosion resistance, aluminum levels greater than the nominal R88DT level to maintain gamma prime (Ni 3 (Al, Ti, Nb, Ta)) stability, and cobalt levels sufficient to aid in minimizing stacking fault energy (desirable for good cyclic behavior) and controlling the gamma prime solvus temperature.
  • the regression equations and prior experience further indicated that narrowly controlled and balanced levels of refractory metals, particularly titanium, tungsten, niobium, chromium, hafnium and tantalum, would likely be necessary to achieve the desired high temperature creep properties.
  • regression factors relating to specific mechanical properties were utilized to narrowly identify potential alloy compositions that might be capable of exhibiting high temperature creep properties, and would not be otherwise identifiable without extensive experimentation with a very large number of alloys.
  • thermodynamic instability resulting from high refractory metal contents.
  • phase instability is often unpredictable, resulting in alloy compositions whose properties are far less than what had been predicted on the basis of analytical predictions utilizing elemental transfer functions.
  • brittle intermetallic phases that can have significant detrimental effects on properties, including such topologically close packed (TCP) phases as delta ( ⁇ ), sigma ( ⁇ ), eta ( ⁇ ), alpha ( ⁇ ) (such as ⁇ -Cr), A, and P phases.
  • eta phase Ni 3 Ti
  • the presence of absence of detrimental levels of these phases can and were assessed during the investigation on the basis of whether an observable amount of one or more of these phases could be detected by an optical examination at a minimum of 500X utilizing suitably etched metallographic samples.
  • alloy compositions were prepared and evaluated under a series of property tests that included not only high temperature creep at 1300°F (about 705°C), but also creep at higher temperatures, ultimate tensile strength (UTS), yield strength (YS), ductility, notched stress rupture (NSR), cycle and dwell fatigue crack growth rate (FCGR), low cycle fatigue (LCF), and sustained-peak low cycle fatigue (SPLCF).
  • the alloy compositions generally fell within two chemistry groups, one of which was identified as HL601 through HL614 (collectively, referred to herein as the HL6XX alloys or alloy series), and the other HL701 through HL710 (collectively, referred to herein as the HL7XX alloys or alloy series).
  • All of the alloys were targeted to have the following nominal levels, by weight, for certain alloy constituents: 3.2% Al; 0.030% B; 0.05% C; 2.5% Mo; 2.8% Ti, and 0.05% Zr.
  • the twenty-four alloys evaluated were targeted to have narrower test chemistries than the HL11 alloy of Bain et al., specifically with respect to cobalt, chromium, niobium, tantalum and tungsten.
  • the investigated ranges for these five elements were varied among the alloys to evaluate their effects on high temperature creep properties and detrimental TCP phases.
  • the cobalt levels were targeted over a range of about 18 to about 20 weight percent
  • the chromium levels were targeted over a range of about 10 to about 12 weight percent
  • the niobium levels were targeted over a range of about 1.5 to about 3.5 weight percent
  • the tantalum levels were targeted over a range of about 5 to about 6 weight percent
  • the tungsten levels were targeted over a range of about 3 to about 5 weight percent.
  • one of the HL7XX alloys (HL708) was evaluated with no intentional addition of hafnium. The actual chemistries of the HL6XX and HL7XX alloys are summarized in FIG. 2 .
  • phase formations that occur in multicomponent systems are a complex function of the elemental composition of the system. This is due to the complex thermodynamic interactions prevailing among the elements in a multicomponent system in an n-dimensional space, where n is the number of significant elements in the composition of the alloy.
  • FIG. 3 is a bar graph representing the 0.2% creep at 1300°F and 100 ksi (about 705°C and about 690 MPa) of eight of the ten HL7XX alloys: HL701, HL702, HL704-HL708, and HL710.
  • the best performing alloy, HL702 contained a relatively low amount of chromium (10.02 weight percent) relative to the targeted chromium range (10 to 12 weight percent), whereas the two poorest performing alloys, HL701 and HL703, had relatively high chromium levels (12.09 and 12.02 weight percent, respectively).
  • the next five best-performing alloys had chromium contents of 11.02, 11.02, 10.12, 10.85, and 10.80 weight percent, respectively, suggesting that a critical level of chromium may exist between 11.02 and 12.02 weight percent within the compositional space of the experimental alloys.
  • the six best-performing alloys had 0.2% creep lives exceeding 1000 hours, whereas HL701 and HL703 had creep lives of less than 1000 hours.
  • the performance of HL701 was attributed to an observable amount of phase instability.
  • FIG. 4 plots 0.2% creep at 1300°F and 100 ksi (about 705°C and about 690 MPa) versus W+Nb-Cr value for nine alloys from the HL6XX series and eight alloys form the HL7XX series that exhibited comparable or improved creep properties compared to the HL11 alloy and the commercial alloys R88DT and R104.
  • the plot shows that these alloys had W+Nb-Cr values of -6.0 or higher (approaching zero), and evidences that many of these HL6XX and HL7XX alloys exceeded HL11, R88DT, and R103 in terms of creep.
  • Eight experimental alloys that had creep lives of less than 1000 hours were determined to be unstable, resulting in observable amounts of TCP phases.
  • FIG. 4 plots 0.2% creep at 1300°F and 100 ksi (about 705°C and about 690 MPa) versus W+Nb-Cr value for nine alloys from the HL6XX series and eight alloys form
  • Creep life and phase stability also appeared to be sensitive to chromium content. Because alloys with a W+Nb-Cr value of -6 and higher included HL602 and HL603 with chromium contents of 12.00 and 12.08%, respectively, a chromium content not exceeding 12.5 weight percent was concluded to be acceptable in combination with the ranges of the other alloying constituents, particularly tungsten and niobium. A minimum chromium content was concluded to be 9.5% based on results obtained with alloys having a W+Nb-Cr value of at least -6 and a chromium content of about 10% (HL611, HL702, and HL704).
  • the levels of molybdenum that were investigated were generally within the lower half of the molybdenum range for the HL11 alloy in Bain et al., which was done with the intent of reducing the risk of TCP phase formation.
  • the level of cobalt was limited to a range of about 18 and 20 weight percent, cobalt was not considered to be critical as it freely substitutes for nickel in the gamma phase matrix.
  • alloy compositions identified in FIG. 2 and the alloys and alloying ranges identified in Table I were initially based on analytical predictions, the extensive analysis and resources relied on to make the predictions and identify these alloy compositions provide a strong indication for the potential of these alloys, and particularly the alloy compositions of Tables I, to achieve significant improvements in creep and hold time fatigue crack growth rate characteristics desirable for turbine disks of gas turbine engines.

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Claims (11)

  1. Gamma-Prime-Superlegierung auf Nickel-Basis, umfassend, bezogen auf das Gewicht:
    16,0 bis 30,0 % Cobalt;
    9,5 bis 12,5 % Chrom;
    4,0 bis 6,0 % Tantal;
    2,0 bis 4,0 % Aluminium;
    2,0 bis 3,4 % Titan;
    3,0 bis 6,0 % Wolfram;
    1,0 bis 4,0 % Molybdän;
    1,5 bis 3,5 % Niob;
    bis zu 1,0 % Hafnium;
    0,02 bis 0,20 % Kohlenstoff;
    0,01 bis 0,05 % Bor;
    0,02 bis 0,10 % Zirconium;
    Rest Nickel und Verunreinigungen;
    wobei die Superlegierung einen W+Nb-Cr-Wert von zumindest -6 bis nahezu null hat, frei von wahrnehmbaren Mengen von Sigma- und Etaphasen ist und eine Zeit zum 0,2%igen Kriechen bei 704 °C (1300 °F) und 689 MPa (100 ksi) von zumindest 1000 Stunden aufweist.
  2. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Chromgehalt 10,0 bis 12,5 Gewichtsprozent beträgt.
  3. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Niobgehalt 1,8 bis 2,2 Gewichtsprozent beträgt.
  4. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Wolframgehalt 3,0 bis 5,0 Gewichtsprozent beträgt.
  5. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Chromgehalt 10,0 bis 12,5 Gewichtsprozent beträgt, der Niobgehalt 1,8 bis 2,2 Gewichtsprozent beträgt und der Wolframgehalt 3,0 bis 5,0 Gewichtsprozent beträgt.
  6. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Titangehalt 2,5 bis 2,9 Gewichtsprozent beträgt.
  7. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, wobei der Molybdängehalt 2,5 bis 3,0 Gewichtsprozent beträgt.
  8. Komponente, die aus der Gamma-Prime-Superlegierung auf Nickel-Basis von Anspruch 1 gebildet wird.
  9. Komponente nach Anspruch 8, wobei die Komponente eine Pulvermetallurgiekomponente, ausgewählt aus der Gruppe, bestehend aus Turbinenscheiben und Verdichterscheiben und Blisks von Gasturbinentriebwerken, ist.
  10. Gamma-Prime-Superlegierung auf Nickel-Basis nach Anspruch 1, bestehend aus, bezogen auf das Gewicht:
    17,0 bis 20,5 % Cobalt;
    10,0 bis 12,5 % Chrom;
    4,5 bis 5,5 % Tantal;
    3,0 bis 3,4 % Aluminium;
    2,5 bis 2,9 % Titan;
    3,0 bis 5,0 % Wolfram;
    2,5 bis 3,0 % Molybdän;
    1,8 bis 2,2 % Niob;
    bis zu 0,6 % Hafnium;
    0,048 bis 0,068 % Kohlenstoff;
    0,015 bis 0,04 % Bor;
    0,04 bis 0,06 % Zirconium;
    Rest Nickel und Verunreinigungen;
    wobei die Superlegierung einen W+Nb-Cr-Wert von zumindest -6 bis nahezu null hat, frei von wahrnehmbaren Mengen von Sigma- und Etaphasen ist und eine Zeit zum 0,2%igen Kriechen bei 704 °C (1300 °F) und 689 MPa (100 ksi) von zumindest 1000 Stunden aufweist.
  11. Komponente, die aus der Gamma-Prime-Superlegierung auf Nickel-Basis von Anspruch 10 gebildet wird.
EP14762119.7A 2013-07-23 2014-02-20 Superlegierungen und daraus geformte komponenten Active EP3024957B1 (de)

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US13/948,463 US9518310B2 (en) 2009-05-29 2013-07-23 Superalloys and components formed thereof
PCT/US2014/017336 WO2015012888A1 (en) 2013-07-23 2014-02-20 Superalloys and components formed thereof

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CN112760525B (zh) 2019-11-01 2022-06-03 利宝地工程有限公司 高γ′镍基超级合金、其用途及制造涡轮发动机构件的方法
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EP3024957A1 (de) 2016-06-01
CN105492639A (zh) 2016-04-13
JP2016532777A (ja) 2016-10-20
JP6356800B2 (ja) 2018-07-11
CN105492639B (zh) 2018-05-22
WO2015012888A1 (en) 2015-01-29
CA2918337A1 (en) 2015-01-29
CA2918337C (en) 2019-01-15

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