EP2305847A1 - Superalliages à base de nickel et articles - Google Patents

Superalliages à base de nickel et articles Download PDF

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Publication number
EP2305847A1
EP2305847A1 EP10179691A EP10179691A EP2305847A1 EP 2305847 A1 EP2305847 A1 EP 2305847A1 EP 10179691 A EP10179691 A EP 10179691A EP 10179691 A EP10179691 A EP 10179691A EP 2305847 A1 EP2305847 A1 EP 2305847A1
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Prior art keywords
nickel
article
alloys
aluminum
tantalum
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EP10179691A
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German (de)
English (en)
Inventor
Akane Suzuki
Jr. Michael Francis Xavier Gigliotti
Shyh-Chin Huang
Pazhayannur Ramanathan Subramanian
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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%

Definitions

  • the present disclosure relates to nickel-based alloys, articles based thereupon, and methods of making the articles.
  • Gas turbine engines operate in extreme environments, exposing the engine components, especially those in the turbine section, to high operating temperatures and stresses. In order for the turbine components to endure these conditions, they are necessarily manufactured from a material capable of withstanding these severe conditions. Superalloys have been used in these demanding applications because they maintain their strength at up to 90% of their melting temperature and have excellent environmental resistance. Nickel-based superalloys, in particular, have been used extensively throughout gas turbine engines, e.g., in turbine blade, nozzle, and shroud applications. However, designs for improved gas turbine engine performance require alloys with even higher temperature capability.
  • SC single crystal
  • a defining characteristic of the first generation of SC superalloys is the absence of the alloying element rhenium (Re).
  • the second generation of SC superalloys such as CMSX-4, PWA-1484 and René N5, all contain about 3 wt% Re, pursuant to the discovery that the addition of this amount of Re can provide about a 50°F (28°C) improvement in rupture creep capability and the accompanying fatigue benefits.
  • third generation superalloys are characterized by inclusion of about 6 wt% Re; while fourth generation superalloys include about 6 wt % Re, as well as the alloying element ruthenium (Ru).
  • nickel based superalloy that exhibits all of the desirable properties for use in gas turbine engines, e.g., creep and fatigue strength, resistance to oxidation and corrosion at elevated temperatures, while yet minimizing, or eliminating, the use of rhenium.
  • the superalloy would also exhibit good castability so as to be suitable for use directionally solidified, single crystal articles. Finer primary dendrite arm spacing (PDAS) is preferred for better mechanical properties, since finer PDAS generally gives less grain defects, porosity, and better heat treatment response.
  • PDAS primary dendrite arm spacing
  • the rhenium-free, nickel-based alloy comprises from about 4.0 wt% to about 10 wt% cobalt (Co), from about 4.0 wt% to about 10 wt% chromium (Cr), from about 0.5 wt% to about 2.5 wt% molybdenum (Mo), from about 4.5 wt% to about 9 wt% tungsten (W), from about 4.0 wt% to about 6.5 wt% aluminum (Al), from about 1.5 wt% to about 3.0 wt% titanium (Ti), from about 4.0 wt% to about 9.0 wt% tantalum (Ta), from about 0 wt% to about 1.0 wt% hafnium (Hf), up to about 0.1 wt% carbon (C), up to about 0.01 wt% boron (B), with the remainder being nickel (Ni) and incidental
  • the article comprises a rhenium-free, nickel-based alloy comprising from about 4.0 wt% to about 10 wt% cobalt (Co), from about 4.0 wt% to about 10 wt% chromium (Cr), from about 0.5 wt% to about 2.5 wt% molybdenum (Mo), from about 4.5 wt% to about 9 wt% tungsten (W), from about 4.0 wt% to about 6.5 wt% aluminum (Al), from about 1.5 wt% to about 3.0 wt% titanium (Ti), from about 4.0 wt% to about 9.0 wt% tantalum (Ta), from about 0 wt% to about 1.0 wt% hafnium (Hf), up to about 0.1 wt% carbon (C), up to about 0.01 wt% boron (B), with the remainder being nickel (Ni) and incidental
  • the method comprises casting a nickel-based alloy into a mold and solidifying the casting into a single crystal or columnar structure with the primary dendrite arm spacing within the article less than about 400 ⁇ m.
  • the nickel-based superalloy comprises from about 4.0 wt% to about 10 wt% cobalt (Co), from about 4.0 wt% to about 10 wt% chromium (Cr), from about 0.5 wt% to about 2.5 wt% molybdenum (Mo), from about 4.5 wt% to about 9 wt% tungsten (W), from about 4.0 wt% to about 6.5 wt% aluminum (Al), from about 1.5 wt% to about 3.0 wt% titanium (Ti), from about 4.0 wt% to about 9.0 wt% tantalum (Ta), from about 0 wt% to about 1.0 wt% hafnium (Hf), up to about 0.1 wt% cobalt (Co), from about 4.0
  • FIG. 1 is a graphical representation of creep rupture life at 2000°F/20ksi for an alloy according to one embodiment described herein as compared to the conventional nickel-based alloy René N5 and an alloy MC2+ which is a modified alloy based on the conventional rhenium-free nickel-based alloy MC2 (comprising 5 wt% Co, 8 wt% Cr, 2 wt% Mo, 8 wt%, 5 wt% Al, 1.5 wt% Ti, 6 wt% Ta, with the remainder being Ni and incidental impurities) with additions of B, C and Hf;
  • FIG. 2 is a graphical representation of creep rupture life at 1800°F/30ksi for an alloy according to one embodiment described herein as compared to the conventional nickel-based alloy René N5 and the rhenium-free nickel-based alloy MC2+;
  • FIG. 3 is a graphical representation of the weight change after cyclic oxidation test at 2000°F for 500 cycles for an alloy according to one embodiment described herein as compared to the conventional nickel-based alloy René N5 and the rhenium-free nickel-based alloy MC2+.
  • ranges are inclusive and independently combinable (e.g., ranges of "up to about 25 wt.%, or, more specifically, about 5 wt.% to about 20 wt.%,” is inclusive of the endpoints and all intermediate values of the ranges of "about 5 wt.% to about 25 wt.%,” etc.).
  • the modifier "about” used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., includes the degree of error associated with measurement of the particular quantity).
  • the term “comprising” includes “consisting of”.
  • a rhenium-free, nickel-based alloy is provided. More specifically, the alloy comprises various levels and combinations of elements, in place of rhenium, so that cost savings are provided. Yet, articles formed from the alloys are processed in such a way as to comprise a dendritic structure further comprising fine primary dendrite arm spacing, i.e., wherein the nominal spacing between the dendrite arms is less than about 400 micrometers. As a result, the alloy can exhibit properties substantially similar to, or even improved over, those exhibited by Re-bearing alloys, and improved balance of properties over other rhenium-free, nickel-based alloys comprising the same, or similar, combinations of elements.
  • the nickel-based alloys disclosed can exhibit creep rupture lives substantially equivalent to, or better than, the creep rupture of life of conventional Re-bearing alloys, such as René N5 (3 wt% Re), both at 2000°F and 20 ksi, or 1800°F and 30 ksi. Additionally, the nickel-based alloys can exhibit oxidation resistance significantly better than that exhibited by some rhenium-free alloys, such as MC2+. And, in certain embodiments, the provided nickel-based alloys exhibit improved phase stability, with minimal, or even no, topologically-close-packed (TCP) phase formation, The ability to provide substantially similar properties as provided by Re-bearing alloys with a rhenium-free alloy provides a significant cost savings.
  • TCP topologically-close-packed
  • the rhenium-free, nickel-based alloys described herein comprise various combinations and concentrations of the elements molybdenum, tungsten, aluminum, titanium, tantalum and hafnium unique to the alloys described herein. By selecting preferred levels and ratios of the amount of these elements, desired properties, similar to those exhibited by rhenium-bearing alloys can be achieved.
  • the combined weight % of titanium, aluminum, tantalum and hafnium may be selected, e.g., to provide, or assist in providing, the desired strength in the gamma prime phase.
  • the combined weight % according to the relationship Al + 0.56Ti + 0.15 Ta + 0.15 Hf (weight %) may desirably be between about 7 and 10.
  • the combined weight % of titanium and aluminum, and the ratio therebetween, can be balanced in some embodiments. If the same is desired, the combined weight percent according to the relationship Al + 0.56 Ti (weight%) may desirably be between 6 and 8.0, and the ratio of titanium to aluminum (Ti/Al, weight %) is desirably higher than 0.35. Selecting levels titanium and aluminum in this fashion is believed to be capable of increasing the solid solution strength of the gamma phase of the alloy.
  • the combined weight % of molybdenum and tungsten according to the relationship Mo + 0.52 W is desirably between about 3 and 5.7. It has now been found that, by so selecting the levels of Mo + 0.52W, the solid solution strength of the gamma prime phase of the alloy can be enhanced. It has also been found that by so selecting the levels of Mo + 0.52W, e.g., so that less than 5.7 wt% is utilized in the present alloys, precipitation of topologically-close-packed (TCP) phase and formation of an insoluble eutectic gamma prime phase can be substantially avoided.
  • TCP topologically-close-packed
  • One or more of the above preferred relationships of elements may be utilized in different embodiments of the alloys described, and which and how many to utilize can depend on the properties desirably impacted in the alloy.
  • the alloys described herein comprise from about 4 wt% to about 10 wt% Co, from about 4 wt% to about 10 wt% Cr, from about 0.5 wt% to about 2.5 wt% molybdenum (Mo), from about 4.5 wt% to about 9 wt% tungsten (W), from about 4.0 wt% to about 6.5 wt% aluminum (Al), from about 1.5 wt% to about 3.0 wt% titanium (Ti), from about 4.0 wt% to about 9.0 wt% tantalum (Ta) and from about 0 wt% to about 1.0 wt% hafnium (Hf), up to about 0.1 wt% carbon (C), up to about 0.01 wt% boron (B), with the remainder being nickel (Ni) and incidental impurities.
  • Mo molybdenum
  • Mo molybdenum
  • W molybdenum
  • Al aluminum
  • Al aluminum
  • Ti titanium
  • the molybdenum content of the nickel based alloy may desirably be between about 0.5 wt% to about 2.5 wt%, or from about 0.5 wt% to about 2.1 wt%, or from about 1 wt% to about 2 wt%.
  • the tungsten content of the nickel-based alloy will desirably be from about 4.5 wt% to about 9.0 wt%, or from about 4.5 wt% to about 7.5 wt%, or from about 4.5 wt% to about 7 wt%.
  • the aluminum content of the nickel-based alloys may range from about 4 wt% to about 6.5 wt% or from about 4.5 wt% to about 6 wt%, or from about 4.5 wt% to about 5.6 wt%.
  • Some embodiments of the present nickel-based alloys may comprise titanium in amounts ranging from about 1.5 wt% to about 3 wt%, or from about 1.5 wt% to about 2.5 wt%.
  • tantalum may be present in amounts ranging from about 4 wt% to about 9 wt%, or from about 5 wt% to about 7.5 wt%, or from about 6 wt% to about 7.2 wt%.
  • Hafnium in certain embodiments, may be utilized in amounts ranging from about 0 wt% to about 1 wt%, or from about 0 wt% to about 0.5 wt%.
  • the nickel-based alloys may also comprise cobalt and chromium.
  • cobalt may generally be added in amounts of from about 4 wt% to about 10 wt%, or from about 5.5 wt% to about 8 wt%, or from about 6 wt% to about 8 wt%.
  • chromium may be included in amounts of from about 4 wt% to about 10 wt%. In some embodiments, chromium may be present in amounts of from about 6 wt% to about 8.5 wt%, or from about 7.0 wt% to about 8.5 wt%.
  • Carbon (C), boron (B), silicon (Si), germanium (Ge), yttrium (Y) and other rare earth metals may also be included in the present nickel-based alloys, if desired.
  • Carbon when utilized, may generally be utilized in the nickel-based alloys described herein in amounts of less than about 0.5 wt%. In some embodiments, amounts of carbon of from about 0.01 wt% to about 0.5 wt% may be used in the nickel-based alloys. An exemplary amount of carbon is from about 0.03 wt% to about 0.49 wt%.
  • Boron may be present in the nickel-base alloys in some embodiments in amounts of less than or equal to about 0.1 wt% of the nickel-based alloy. In some embodiments, amounts of boron between about 0.001 wt% and about 0.09 wt% may be included in the nickel based alloys. One exemplary amount of boron useful in the nickel based alloys is from about 0.004 wt% to about 0.075 wt%.
  • silicon may be included in certain embodiments of the nickel-based alloys. If so included, amounts of silicon of from about 0.05 wt% to about 1 wt% are appropriate, and exemplary amounts may range from about 0.1 wt% to about 0.5 wt%.
  • Yttrium if used, may be present in amounts of from about 0.01 wt% to about 0.1 wt%, and exemplary amounts range from about 0.03 wt% to about 0.05 wt%.
  • Appropriate amounts of germanium can range from 0 wt% to about 1 wt%, with exemplary amounts thereof ranging from about 0.2wt% to about 0.5 wt%.
  • one embodiment of the nickel-based alloys may comprise from about 4.0 wt% to about 10 wt% cobalt (Co), from about 4.0 wt% to about 10 wt% chromium (Cr), from about 0.5 wt% to about 2.5 wt% molybdenum (Mo), from about 4.5 wt% to about 9 wt% tungsten (W), from about 4.0 wt% to about 6.5 wt% aluminum (Al), from about 1.5 wt% to about 3.0 wt% titanium (Ti), from about 4.0 wt% to about 9.0 wt% tantalum (Ta), from about 0 wt% to about 1.0 wt% hafnium (Hf), up to about 0.1 wt% carbon (C), up to about 0.01 wt% boron (B), with the remainder being nickel (Ni) and incidental impurities.
  • Co cobalt
  • Cr chromium
  • Mo molybdenum
  • the nickel-based alloy may desirably comprise from about 5.5 wt% to about 8.0 wt% cobalt (Co), from about 6.0 wt% to about 8.5 wt% chromium (Cr), from about 0.5 wt% to about 2.1 wt% molybdenum (Mo), from about 4.5 wt% to about 7.5 wt% tungsten (W), from about 4.5 wt% to about 6.0 wt% aluminum (Al), from about 5.0 wt% to about 7.5 wt% tantalum (Ta), from about 0 wt% to about 0.5 wt% hafnium (Hf).
  • Co cobalt
  • Cr chromium
  • Mo molybdenum
  • Mo molybdenum
  • W 4.5 wt% to about 7.5 wt% tungsten
  • Al aluminum
  • Ta tantalum
  • Hf hafnium
  • the nickel-based alloy may desirably comprise from about 6.0 wt% to about 8.0 wt% cobalt (Co), from about 7.0 wt% to about 8.5 wt% chromium (Cr), from about 1.0 wt% to about 2.0 wt% molybdenum (Mo), from about 4.5 wt% to about 7 wt% tungsten (W), from about 4.5 wt% to about 5.6 wt% aluminum (Al), from about 1.5 wt% to about 2.5 wt% titanium (Ti), and from about 6.0 wt% to about 7.2 wt% tantalum (Ta).
  • Co cobalt
  • Cr chromium
  • Mo molybdenum
  • W 4.5 wt% to about 7 wt% tungsten
  • Al aluminum
  • Ti titanium
  • Ta tantalum
  • the nickel-based alloys may be processed according to any existing method(s) to form components for a gas turbine engine, including, but not limited to, powder metallurgy processes (e.g., sintering, hot pressing, hot isostatic processing, hot vacuum compaction, and the like), ingot casting, followed by directional solidification, investment casting, ingot casting followed by thermo-mechanical treatment, near-net-shape casting, chemical vapor deposition, physical vapor deposition, combinations of these and the like.
  • powder metallurgy processes e.g., sintering, hot pressing, hot isostatic processing, hot vacuum compaction, and the like
  • ingot casting followed by directional solidification
  • investment casting ingot casting followed by thermo-mechanical treatment, near-net-shape casting, chemical vapor deposition, physical vapor deposition, combinations of these and the like.
  • the desired components are provided in the form of a powder, particulates, either separately or as a mixture and heated to a temperature sufficient to melt the metal components, generally from about 1350°C to about 1600°C.
  • the molten metal is then poured into a mold in a casting process to produce the desired shape.
  • any casting method may be utilized, e.g., ingot casting, investment casting or near net shape casting.
  • the molten metal may desirably be cast by an investment casting process which may generally be more suitable for the production of parts that cannot be produced by normal manufacturing techniques, such as turbine buckets, that have complex shapes, or turbine components that have to withstand high temperatures.
  • the molten metals may be cast into turbine components by an ingot casting process.
  • the casting may be done using gravity, pressure, inert gas or vacuum conditions. In some embodiments, casting is done in a vacuum.
  • Directional solidification generally results in single-crystal or columnar structure, i.e., elongated grains in the direction of growth, and thus, higher creep strength for the airfoil than an equiaxed cast, and is suitable for use in some embodiments
  • the melt may be directionally solidified in a temperature gradient provided by liquid metal, for example, molten tin.
  • liquid metal for example, molten tin.
  • Liquid metal cooling method creates larger temperature gradient than conventional directional solidification method that uses radiant cooling, and provide a finer dendrite arm spacing. Finer dendrite arm spacing, in turn, can be beneficial to the mechanical properties of the alloy, as well as in the reduction of segregation within the same.
  • the castings comprising the nickel-based alloy may then be typically subjected to different heat treatments in order to optimize the strength as well as to increase creep resistance.
  • the castings are desirably solution heat treated at a temperature between the solidus and gamma prime solvus temperatures.
  • Solidus is a temperature at which alloy starts melting during heating, or finishes solidification during cooling from liquid phase.
  • Gamma prime solvus is a temperature at which gamma prime phase completely dissolves into gamma matrix phase during heating, or starts precipitating in gamma matrix phase during cooling.
  • Such heat treatments generally reduce the presence of segregation.
  • alloys are heat treated below gamma prime solvus temperature to form gamma prime precipitates.
  • the nickel-based alloys described herein may thus be processed into a variety of airfoils for large gas turbine engines. Because the preferred levels and ratios of elements are selected in the alloys, they and the articles and gas turbine engine components made therefrom exhibit improved high temperature strength, as well as improved oxidation resistance. Further, high gradient casting, may be used in some embodiments to provide fine dendrite arm spacing, so that further improvements in mechanical properties can be seen. Examples of components or articles suitably formed from the alloys described herein include, but are not limited to buckets (or blades), nonrotating nozzles (or vanes), shrouds, combustors, and the like. Components/articles thought to find particular benefit in being formed form the alloys described herein include nozzles and buckets.
  • This example was undertaken to demonstrate the improvement in properties that can be seen nickel-based alloys according to embodiments described herein and not comprising rhenium, as compared to a conventional nickel-based alloy comprising rhenium, René N5, and a modified nickel-based rhenium-free alloy, MC2+, based on MC2 (comprising 5 wt% Co, 8 wt% Cr, 2 wt% Mo, 8 wt%, 5 wt% Al, 1.5 wt% Ti, 6 wt% Ta, with the remainder being Ni and incidental impurities) where carbon, boron and hafnium were added to the original composition.
  • the samples were prepared by taking the various components thereof and heating them to a temperature of 1500 ⁇ 1550°C.
  • the molten alloys were poured into a ceramic mold and directionally solidified into single-crystal form via high gradient casting using the liquid metal cooling method, wherein the alloys were directionally solidified in a temperature gradient provided by a molten tin bath.
  • Liquid metal cooling method creates larger temperature gradient than conventional directional solidification method that uses radiant cooling, and provide a finer dendrite arm spacing.
  • the primary dendrite arm spacing was between about 170 ⁇ m and 260 ⁇ m.
  • a two phase gamma plus gamma prime microstructure was achieved by solution treatment at temperatures between the solidus and solvus temperatures, followed by aging treatment at 1100°C and stabilization treatment at 900°C.
  • the solution treatment temperatures were between 1250°C and 1310°C, and alloys were hold at the temperature for 6 to 10 hours, followed by air cool.
  • Aging treatment was conducted at 1100°C for 4 hours, followed by air cool.
  • Stabilization treatment was conducted at 900°C for 24 hours, followed by air cool.
  • the samples were then subjected to creep testing and cyclic oxidation testing. More specifically, for the creep testing the samples were cut into cylindrical dogbone type creep sample with a total length of 1.37 inches and the gauge diameter of about 0.1 inch. The testing was conducted in a tensile testing machine at a temperature of 2000°F, under a stress of 20 kilograms per square inch (ksi), and again at a temperature of 1800°F, under a stress of 30 ksi. The time taken to rupture was measured and recorded as a function of the samples ability to display creep resistance.
  • Alloy 12 (comprising 1.4 wt% molybdenum, 7.0 wt% tungsten, 6.0 wt% tantalum and 0.15 wt% hafnium) exhibits approximately equivalent creep resistance to René N5.

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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)
EP10179691A 2009-09-30 2010-09-24 Superalliages à base de nickel et articles Withdrawn EP2305847A1 (fr)

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US12/571,013 US20110076182A1 (en) 2009-09-30 2009-09-30 Nickel-Based Superalloys and Articles

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EP2725110A1 (fr) * 2012-10-26 2014-04-30 MTU Aero Engines GmbH Superalliage à base de nickel sans rhénium résistant au fluage
EP3091095A1 (fr) 2015-05-05 2016-11-09 MTU Aero Engines GmbH Superalliage à base de nickel sans rhénium à faible densité

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US9580774B2 (en) 2012-10-26 2017-02-28 MTU Aero Engines AG Creep-resistant, rhenium-free nickel base superalloy
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