US20130206287A1 - Co-based alloy - Google Patents

Co-based alloy Download PDF

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US20130206287A1
US20130206287A1 US13/816,905 US201113816905A US2013206287A1 US 20130206287 A1 US20130206287 A1 US 20130206287A1 US 201113816905 A US201113816905 A US 201113816905A US 2013206287 A1 US2013206287 A1 US 2013206287A1
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mass
based alloy
phase
temperature
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Inventor
Jun Sato
Shinya Imano
Mototsugu Osaki
Shigeki Ueta
Kiyohito Ishida
Toshihiro OMORI
Hiroaki Nishida
Masahiro Hayashi
Tomoki Shiota
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Tohoku University NUC
Mitsubishi Power Ltd
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Tohoku University NUC
Hitachi Ltd
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Assigned to HITACHI, LTD., TOHOKU UNIVERSITY reassignment HITACHI, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ISHIDA, KIYOHITO, OMORI, TOSHIHIRO, Osaki, Mototsugu, UETA, SHIGEKI, HAYASHI, MASAHIRO, NISHIDA, HIROAKI, SHIOTA, Tomoki, SATO, JUN, IMANO, SHINYA
Publication of US20130206287A1 publication Critical patent/US20130206287A1/en
Assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD. reassignment MITSUBISHI HITACHI POWER SYSTEMS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HITACHI, LTD.
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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
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • 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
    • 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
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0463—Cobalt
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a Co-based alloy suitable for various components required to have a high strength in a high-temperature environment, such as for a gas turbine, an aircraft engine, a chemical plant, a vehicle engine and a high-temperature furnace.
  • a Co-based suitable for casting such as for a gas turbine, an aircraft engine, a chemical plant, a vehicle engine and a high-temperature furnace.
  • it relates to a Co-based suitable for casting.
  • a Ni-based alloy, a Co-based alloy, an Fe-based alloy or the like have been known as a superalloy used at a high-temperature.
  • the Ni-based alloy is precipitation-strengthened by a ⁇ ′ phase having an L1 2 structure (Ni 3 (Al, Ti)), and exhibits a reverse temperature dependency where strength increases as a temperature increases.
  • the Ni-based alloy has excellent high-temperature properties such as heat resistance, corrosion resistance, oxidation resistance and creep resistance.
  • the Ni-based alloy is used for various purposes which require a high strength in a high-temperature environment.
  • the Ni-based alloy is inferior in machinability and hot workability.
  • the Co-based alloy is used rather than the Ni-based alloy for high-temperature applications when particularly corrosion resistance and ductility are required.
  • a conventional Co-based alloy has a lower high-temperature strength than the Ni-based alloy and is inferior in hot workability to the Ni-based alloy, since a ⁇ ′-type intermetallic compound effective for improving the high-temperature strength properties of the Co-based alloy was not known.
  • WO 2007/032293 A1 discloses a Co-based alloy including, by mass, 0.1 to 10% of Al, 3.0 to 45% of W, and the balance of Co and inevitable impurities, and having a precipitate of an L1 2 -type intermetallic compound Co 3 (Al, W).
  • WO 2007/032293 A1 discloses that a high-temperature strength is increased by uniformly and finely precipitating Co 3 (Al, W) in a matrix and that hot working becomes possible by adjusting the Co-based alloy to have a predetermined composition.
  • JP-A-2009-228024 discloses a Co-based alloy including not less than 0.1 and not more than 20.0 mass % of Cr, not less than 1.0 and not more than 6.0 mass % of Al, not less than 3.0 and not more than 26.0 mass % of W, not more than 50.0 mass % of Ni, and the balance of Co and inevitable impurities, and satisfying that Cr+Al is not less than 5.0 and not more than 20.0 mass %, and that a volume ratio of second phases composed of a ⁇ phase represented by A 7 B 6 and a Laves phase represented by A 2 B is not more than 10%.
  • JP-A-2009-228024 discloses that the Co-based alloy exhibits high-temperature strength equal to or greater than that of a Ni-based alloy, when the alloy includes predetermined amounts of Al and W and is subjected to homogenizing heat treatment and aging treatment under predetermined conditions to precipitate a Co 3 (Al, W) strengthening phase.
  • the Co-based alloy including precipitated Co 3 (Al, W) as the strengthening phase ( ⁇ ′ phase) exhibits high-temperature strength properties equal to or greater than those of a Ni-based alloy.
  • the Co-based alloy including Al and W may have a second phase precipitate depending on heat treatment conditions, that is harmful to processing.
  • hot workability may be significantly decreased.
  • hot workability is an important property for an alloy for casting, and thus a balance between hot workability and strength is necessary.
  • a Co-based alloy according to the invention comprises
  • Mo, Nb, Ti and Ta in the impurities are as follows:
  • a Co-based alloy including Al and W easily generates a phase harmful to hot workability.
  • a harmful phase is generated within grains and in grain boundaries, and thus hot workability is significantly decreased.
  • the Co-based alloy when a Co-based alloy has a composition adjusted in a predetermined range (in particular Al and W contents) and is subjected to homogenizing heat treatment, the Co-based alloy can include less harmful phase.
  • a Co 3 (Al, W) strengthening phase ( ⁇ ′ phase) is precipitated.
  • carbide containing W and/or Cr is precipitated in addition to the ⁇ ′ phase after the aging treatment.
  • granular carbide can be precipitated in grain boundaries of a ⁇ phase matrix by optimizing the carbon content.
  • the granular carbide precipitated in the grain boundaries has a large effect of suppressing grain boundary sliding at a high temperature.
  • a predetermined amount of carbide is precipitated in the grain boundaries in addition to the precipitation of the ⁇ ′ phase, thereby a creep rupture property or high-temperature ductility, which is specifically required for a high-temperature material, is remarkably improved in comparison to a conventional Co-based alloy. Accordingly, a Co-based alloy having endurance strength equal to or greater than that of an existing Ni-based alloy can be obtained.
  • FIG. 1 is a photograph of a microstructure of a ruptured portion in a Co-based alloy (Example 1) before a creep rupture test.
  • FIG. 2 is a photograph of a microstructure of the ruptured portion in the Co-based alloy (Example 1) after the creep rupture test.
  • a Co-based alloy according to the invention includes following elements, and the balance is Co and inevitable impurities.
  • the elements, addition ranges thereof, and reasons for determining the ranges are explained as follows.
  • Precipitation of granular carbide in the grain boundaries is effective mainly for grain boundary strengthening, and improves hot workability and high-temperature strength.
  • the granular carbide precipitation has a large effect of improving a tensile and creep rupture properties.
  • the carbon content needs to be not less than 0.001 mass %. More preferably, the carbon content is not less than 0.005 mass %.
  • the carbon content needs to be less than 0.100 mass %. More preferably, the carbon content is less than 0.050 mass %.
  • carbide is precipitated in the grain boundaries in an optimum form by optimizing the carbon content in addition to the contents of Cr and W, thereby improving high-temperature ductility, and thus significant improvement of properties can be achieved.
  • carbide means various kinds of carbides mainly containing carbon and Cr and/or W.
  • Cr is effective for improving oxidation resistance since Cr bonds to oxygen and forms a dense Cr 2 O 3 layer on its surface. If a Cr content is low, it becomes difficult to form the dense Cr 2 O 3 layer, and sufficient oxidation resistance can not be obtained. In addition, Cr bonds to carbon and generates various kinds of carbides within grains and in grain boundaries, and thus, contributes to improvement of hot workability and high-temperature ductility. In order to obtain the effects, the Cr content needs to be not less than 9.0 mass %. Cr is added, more preferably, not less than 10.0 mass %, and further preferably, not less than 10.5 mass %.
  • the Cr content needs to be less than 20.0 mass %.
  • the Cr content is, more preferably, less than 19.5 mass %, and further preferably, less than 18.5 mass %.
  • carbide is precipitated in an optimum form by optimizing the Cr content, and thus, significant improvement of high-temperature ductility can be achieved.
  • Al stabilizes an L1 2 -type intermetallic compound phase ( ⁇ ′ phase) of Co 3 (Al, W).
  • ⁇ ′ phase intermetallic compound phase
  • Al is a necessary element for precipitating the metastable ⁇ ′ phase as a stable phase and improves high-temperature strength. If an Al content is low, a sufficient amount of the ⁇ ′ phase for improving strength properties can not be generated.
  • Al improves oxidation resistance since it generates Al 2 O 3 .
  • the Al content needs to be not less than 2.0 mass %.
  • the Al content is, more preferably, not less than 2.5 mass %, and further preferably, not less than 3.0 mass %.
  • the Al content needs to be less than 5.0 mass %.
  • the Al content is, more preferably, less than 4.5 mass %, and further preferably, less than 4.3 mass %.
  • the “L1 2 -type intermetallic compound phase ( ⁇ ′ phase) of Co 3 (Al, W)” includes not only the ⁇ ′. phase made of Co, Al and W, but also that in which a part of a Co and/or an (Al, W) site is replaced by other element(s).
  • Tungsten stabilizes the L1 2 -type intermetallic compound phase ( ⁇ ′ phase) of Co 3 (Al, W).
  • Tungsten is a necessary element for generating the ⁇ ′ phase that is effective for obtaining a high-temperature strength. If the tungsten content is low, an amount of the ⁇ ′ phase sufficient for improving strength can not be generated.
  • the tungsten content is, more preferably, not less than 14.5 mass %, and further preferably, not less than 15.0 mass %.
  • the tungsten content needs to be less than 20.0 mass %.
  • the tungsten content is, more preferably, less than 19.0 mass %, and further preferably, less than 18.0 mass %.
  • the “A 7 B 6 compound ( ⁇ phase)” is a compound derived from Co 7 W 6 , and also includes a compound in which an A site (Co site) is replaced by Ni, Cr, Al, Fe or the like and a B site (W site) is replaced by Ta, Nb, Ti, Zr or the like.
  • Ni replaces a Co site to generate an L1 2 -type intermetallic compound phase of (Co, Ni) 3 (Al, W). Moreover, Ni is equally distributed in an matrix ⁇ phase and the strengthening ⁇ ′ phase. In particular, when a Co site of the ⁇ ′ phase is replaced by Ni, a solid solution temperature of the ⁇ ′ phase is increased and high-temperature strength is improved. In order to obtain the effect, the Ni content needs to be not less than 39.0 mass %. The Ni content is, more preferably, not less than 41.0 mass %, and further preferably, not less than 43.0 mass %.
  • the Ni content needs to be less than 55.0 mass %.
  • the Ni content is, more preferably, less than 52.0 mass %, and further preferably, less than 50.0 mass %.
  • Mo, Nb, Ti and Ta among the inevitable impurities particularly need to be within the following ranges.
  • Mo functions as a solid solution strengthening element. However, strengthening by Mo is smaller than that by Ta. Moreover, addition of Mo decreases oxidation resistance. Therefore, a Mo content needs to be less than 0.010 mass %.
  • Nb has an effect of improving a high-temperature strength in a Ni-based alloy since Ni 3 Nb as a ⁇ ′′ ( ⁇ double prime) phase is precipitated.
  • the ⁇ ′′ phase is not precipitated by addition of Nb in a Co-based alloy, thereby resulting in a decrease in hot workability and high-temperature strength due to a lowered melting point. Therefore, the Nb content needs to be less than 0.010 mass %.
  • Ti replaces an Al site of Ni 3 Al in a Ni-based alloy and is effective for strengthening the ⁇ ′ phase.
  • an excessive addition of Ti increases a ⁇ ′ solid solution temperature and decreases a melting point of a matrix, thereby resulting in a decrease in workability.
  • an excessive addition of Ti decreases a melting point, thereby resulting in a decrease in hot workability and high-temperature strength. Therefore, the Ti content needs to be less than 0.010 mass %.
  • Ta functions to effect solid-solution strengthening of a ⁇ ′ phase, and is effective for improving high-temperature strength.
  • high-temperature ductility is significantly decreased by an addition of Ta.
  • a Ta content needs to be less than 0.010 mass %.
  • the Co-based alloy according to the invention may further include one or more of the following elements.
  • the supplemental additional elements, ranges thereof, and reasons for determining the ranges are as follows.
  • boron and Zr function to strength grain boundaries, and promote to improve hot workability.
  • a boron content is preferably 0.0001 mass %.
  • a Zr content is preferably not less than 0.0001 mass %.
  • the boron content is preferably less than 0.020 mass %.
  • the Zr content is preferably less than 0.10 mass %.
  • Mg and Ca fix S and promote to improve hot workability.
  • a Mg content is preferably not less than 0.0001 mass %.
  • a Ca content is preferably not less than 0.0001 mass %.
  • the Mg content is preferably less than 0.10 mass %.
  • the Ca content is preferably less than 0.20 mass %.
  • the Co-based alloy according to the invention When the Co-based alloy according to the invention is subjected to casting, homogenizing heat treatment, hot working, solution treatment and aging treatment under conditions as described below, the Co-based alloy includes a matrix ⁇ phase, and a carbide and ⁇ ′ phase precipitated in the matrix.
  • the ⁇ ′ phase is precipitated mainly within grains of the matrix.
  • the carbide is precipitated both within the grains and in grain boundaries of the matrix.
  • the carbide is preferably precipitated in the grain boundaries.
  • a shape of the carbide precipitated in the grain boundaries is preferably granular.
  • the ⁇ phase, the ⁇ ′ phase and the carbide for suitable for various purposes can be obtained.
  • the aging treatment is not limited to one-step aging treatment, and may include multiple-step aging treatment of two steps or more.
  • raw materials are prepared so that the above composition of the Co-based alloy is obtained, and are melted and cast.
  • the invention does not limit a melting/casting method and conditions thereof, and various methods and conditions may be used.
  • the homogenizing heat treatment means that for removing solidification segregation generated in the melting/casting process and homogenizing the contents. Hot workability can be improved by the homogenizing.
  • the homogenizing heat treatment temperature is preferably 1000° C. or higher.
  • the homogenizing heat treatment temperature is preferably 1250° C. or lower.
  • the time period for the homogenizing heat treatment is preferably 10 hours or longer.
  • the alloy When the Co-based alloy is subjected to the homogenizing heat treatment under predetermined conditions and then cooled, the alloy has the ⁇ single phase and less harmful phase.
  • the Co-based alloy after the homogenizing heat treatment is subjected to hot working, and is formed into various shapes.
  • a hot working method and conditions thereof are not specifically limited, and various methods and conditions may be used for any purpose.
  • the hot-worked Co-based alloy is subjected to solution treatment.
  • the solution treatment is made for solid-soluting precipitates, such as ⁇ ′-phase or carbide, generated during the hot working process.
  • a temperature for the solution treatment is preferably within a range of 1000 to 1250° C.
  • Optimum time period for the solution treatment is determined depending on the solution treatment temperature. Generally, as the solution treatment temperature becomes high, the precipitates can be solid-soluted in a short time.
  • aging treatment is performed for the Co-based alloy after the solution treatment.
  • the ⁇ ′ phase composed of an L1 2 -type intermetallic compound of Co 3 (Al, W) can be precipitated in the ⁇ phase.
  • the carbide can be precipitated.
  • Conditions for the aging treatment are not specifically limited, and optimum conditions are selected depending on the composition of the alloy and/or purpose. Generally, as an aging temperature becomes high, and/or aging time becomes long, the precipitated amount of ⁇ ′ phase is increased, or a grain size of the ⁇ ′ phase becomes larger. It applies to the carbide.
  • the aging temperature is within a range of 500 to 1100° C. (preferably, 600 to 1000° C.), and the aging time is within a range of 1 to 100 hours, preferably, about 10 to 50 hours.
  • Multiple-step aging treatment at different temperatures may be employed.
  • the ⁇ ′ phases with different sizes can be precipitated.
  • large-sized ⁇ ′phase is effective for improving high-temperature properties, in particular, creep rupture property, while it decreases room-temperature properties.
  • small-sized ⁇ ′ phase is effective for improving room-temperature properties, while it decreases high-temperature properties.
  • an aging temperature for a first step is preferably in a range of 700 to 1100° C.
  • an aging temperature for a second step is preferably in a range of 500 to 900° C.
  • a Co-based alloy containing Al and W in general generates a phase harmful to hot workability.
  • excess W generates a harmful phase within grains and in grain boundaries, and hot workability is significantly decreased.
  • a Co-based alloy with less harmful phase can be obtained when it has a predetermined composition (in particular, Al and W contents) and is subjected to a homogenizing heat treatment under predetermined conditions.
  • Co 3 (Al, W) strengthening phase ( ⁇ ′ phase) is precipitated by a solution treatment and an aging treatment under predetermined conditions after the hot working.
  • carbide containing W and/or Cr is precipitated in addition to the ⁇ ′ phase after the aging treatment.
  • granular carbide can be precipitated in the grain boundaries of a matrix ⁇ phase by optimizing the carbon content.
  • the granular carbide precipitated in the grain boundaries has a large effect of suppressing grain boundary sliding at a high temperature.
  • a creep rupture property (high-temperature ductility) specifically required for a high-temperature material is remarkably improved in comparison to a conventional Co-based alloy, by precipitating a predetermined amount of carbide in the grain boundaries in addition to the precipitation of the ⁇ ′ phase. Accordingly, the Co-based alloy having endurance strength equal to or greater than that of an existing Ni-based alloy can be obtained.
  • Alloys having compositions shown in Tables 1 and 2 were each melted in a vacuum induction furnace to obtain a 50 kg ingot. Each ingot prepared by melting was subjected to homogenizing heat treatment at 1200° C. for 16 hours. Then, the ingot was forged into a rod having a diameter of 16 mm. Solution treatment (ST) was performed for the forged material, under conditions of 1200° C. and followed by air cooling for one hour. Then, two-step aging treatment (AG) was performed under conditions of 900° C. for 24 hours followed by air cooling, and furthermore, under conditions of 800° C. for 24 hours followed by air cooling.
  • ST Solution treatment
  • AG two-step aging treatment
  • test piece having a test portion with a diameter of 8 mm and a test piece length of 90 mm was cut out from each material.
  • the test piece was subjected to a tensile test at 800° C. to measure 0.2% yield stress and tensile strength.
  • test piece having a parallel portion of 30 mm and a test piece length of 92.6 mm was cut out from each material.
  • a creep rupture test was performed under conditions of 800° C. and 294 MPa for the test piece to measure a rupture life, and elongation and reduction when rupturing.
  • a rectangular test piece having a size of 13 mm ⁇ 25 mm and a thickness of 2 mm was cut out from each material.
  • the test piece was continuously heated at 800° C. in an air atmosphere for 200 hours, and then was air cooled.
  • a weight increase by oxidation was calculated from a weight difference between before and after the test, and was used as an index of oxidation resistance.
  • Example 1 to 27 exhibits high strength at 800° C., and has 0.2% yield stress of 700 MPa or greater and tensile strength of 850 MPa or greater. Moreover, each specimen has elongation of 10% or greater, which representing high-temperature ductility.
  • Comparative Example 44 does not substantially contain carbon and has low tensile strength and elongation. This is because strengthening of grain boundary by carbide was not effected and rupture was early generated from the grain boundaries.
  • Example 1 to 27 had a rupture life of 1000 hours or longer, and had high elongation of 10% or greater and reduction of 20% or greater.
  • Comparative Example 44 does not substantially contain carbon and has a short rupture life and low elongation and reduction. This is because strengthening of grain boundary by carbide was not effected and rupture was early generated, as the case of high-temperature tensile property.
  • FIGS. 1 and 2 show microstructures of a ruptured portion of the Co-based alloy (Example 1) before and after the creep rupture test.
  • the ⁇ ′ phases precipitated in cubic or spherical grains are linked (raft structure) at a high-temperature and under a high stress.
  • precipitation of the carbide mainly containing W and Cr is observed in the grain boundaries. Since this is not observed in the microstructure after the test in the comparative examples, it is thought that high-temperature ductility behavior in the creep rupture test is closely related to the structural change of the ⁇ ′ phase and the precipitation of the carbide in the grain boundaries.
  • Examples 1 to 27 exhibit excellent oxidation resistance.
  • Example 1 770 990 17.0 1450 14.1 28.0 0.20
  • Example 2 752 954 15.8 1075 13.6 25.3 0.23
  • Example 3 766 976 15.3 1296 12.5 26.4 0.21
  • Example 4 714 878 16.6 1105 13.3 27.3 0.27
  • Example 5 737 942 16.8 1362 13.5 27.8 0.23
  • Example 6 763 971 16.8 1398 13.4 27.9 0.21
  • Example 7 749 954 16.7 1287 13.3 27.4 0.20
  • Example 8 737 882 13.6 1003 11.3 23.6 0.41
  • Example 9 760 940 15.2 1298 12.4 25.8 0.32
  • Example 10 735 923 14.5 1302 12.3 24.8 0.15
  • Example 11 720 895 14.3 1192 11.6 23.6 0.
  • the Co-based alloy according to the invention can be used for various components required to have a high strength in a high-temperature environment, such as a gas turbine component, an aircraft engine component, a chemical plant component, a vehicle engine component or a high-temperature furnace component.

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US13/816,905 2010-08-23 2011-08-15 Co-based alloy Abandoned US20130206287A1 (en)

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JP2010-186562 2010-08-23
JP2010186562A JP5582532B2 (ja) 2010-08-23 2010-08-23 Ｃｏ基合金
PCT/JP2011/068505 WO2012026354A1 (ja) 2010-08-23 2011-08-15 Ｃｏ基合金

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US (1) US20130206287A1 (de)
EP (1) EP2610360B1 (de)
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US20100061883A1 (en) * 2008-09-08 2010-03-11 Alstom Technology Ltd High-temperature-resistant cobalt-base superalloy
US20170254153A1 (en) * 2016-03-04 2017-09-07 Baker Hughes Incorporated Polycrystalline diamond compacts, methods of forming polycrystalline diamond, and earth-boring tools
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US20100061883A1 (en) * 2008-09-08 2010-03-11 Alstom Technology Ltd High-temperature-resistant cobalt-base superalloy
US11180830B2 (en) 2016-01-08 2021-11-23 Siemens Energy Global GmbH & Co. KG γ, γ′ cobalt based alloys for additive manufacturing methods or soldering, welding, powder and component
US20170254153A1 (en) * 2016-03-04 2017-09-07 Baker Hughes Incorporated Polycrystalline diamond compacts, methods of forming polycrystalline diamond, and earth-boring tools
US10287824B2 (en) 2016-03-04 2019-05-14 Baker Hughes Incorporated Methods of forming polycrystalline diamond
RU2738443C2 (ru) * 2016-03-04 2020-12-14 Бейкер Хьюз, Э Джии Компани, Ллк Поликристаллическая алмазная вставка, способ формирования поликристаллического алмаза и буровой инструмент
US10883317B2 (en) 2016-03-04 2021-01-05 Baker Hughes Incorporated Polycrystalline diamond compacts and earth-boring tools including such compacts
US11396688B2 (en) 2017-05-12 2022-07-26 Baker Hughes Holdings Llc Cutting elements, and related structures and earth-boring tools
US11807920B2 (en) 2017-05-12 2023-11-07 Baker Hughes Holdings Llc Methods of forming cutting elements and supporting substrates for cutting elements
US11292750B2 (en) * 2017-05-12 2022-04-05 Baker Hughes Holdings Llc Cutting elements and structures
US10857595B2 (en) 2017-09-08 2020-12-08 Mitsubishi Hitachi Power Systems, Ltd. Cobalt based alloy additive manufactured article, cobalt based alloy product, and method for manufacturing same
US11325189B2 (en) 2017-09-08 2022-05-10 Mitsubishi Heavy Industries, Ltd. Cobalt based alloy additive manufactured article, cobalt based alloy product, and method for manufacturing same
US11885182B2 (en) 2018-05-30 2024-01-30 Baker Hughes Holdings Llc Methods of forming cutting elements
US12018533B2 (en) * 2018-05-30 2024-06-25 Baker Hughes Holdings Llc Supporting substrates for cutting elements, and related methods
US12098597B2 (en) 2018-05-30 2024-09-24 Baker Hughes Holdings Llc Cutting elements, and related earth-boring tools, supporting substrates, and methods
US11536091B2 (en) * 2018-05-30 2022-12-27 Baker Hughes Holding LLC Cutting elements, and related earth-boring tools and methods
US11613795B2 (en) 2019-03-07 2023-03-28 Mitsubishi Heavy Industries, Ltd. Cobalt based alloy product and method for manufacturing same
US11499208B2 (en) 2019-03-07 2022-11-15 Mitsubishi Heavy Industries, Ltd. Cobalt based alloy product
US11427893B2 (en) 2019-03-07 2022-08-30 Mitsubishi Heavy Industries, Ltd. Heat exchanger
US11414728B2 (en) 2019-03-07 2022-08-16 Mitsubishi Heavy Industries, Ltd. Cobalt based alloy product, method for manufacturing same, and cobalt based alloy article
US11306372B2 (en) 2019-03-07 2022-04-19 Mitsubishi Power, Ltd. Cobalt-based alloy powder, cobalt-based alloy sintered body, and method for producing cobalt-based alloy sintered body
US20220220583A1 (en) * 2020-03-02 2022-07-14 Mitsubishi Heavy Industries, Ltd. Co-based alloy structure and method for manufacturing same
CN113502427A (zh) * 2021-06-23 2021-10-15 沈阳航空航天大学 2.3GPa强度级别Co-Ni-Cr基合金及其制备方法
EP4159360A1 (de) * 2021-09-30 2023-04-05 Daido Steel Co., Ltd. Legierungsprodukt auf kobaltbasis und verfahren zur herstellung eines legierungsprodukts auf kobaltbasis

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