WO2015159166A1 - Superalliage à base de cobalt sans tungstène à renforcement des phases gamma/gamma prime - Google Patents

Superalliage à base de cobalt sans tungstène à renforcement des phases gamma/gamma prime Download PDF

Info

Publication number
WO2015159166A1
WO2015159166A1 PCT/IB2015/052076 IB2015052076W WO2015159166A1 WO 2015159166 A1 WO2015159166 A1 WO 2015159166A1 IB 2015052076 W IB2015052076 W IB 2015052076W WO 2015159166 A1 WO2015159166 A1 WO 2015159166A1
Authority
WO
WIPO (PCT)
Prior art keywords
less
alloy
cobalt
alloys
cobalt based
Prior art date
Application number
PCT/IB2015/052076
Other languages
English (en)
Inventor
Surendra Kumar MAKINENI
Nithin BALER
Kamanio CHATTOPADHYAY
Original Assignee
Indian Institute Of Science
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 Indian Institute Of Science filed Critical Indian Institute Of Science
Priority to US15/304,479 priority Critical patent/US20170037498A1/en
Publication of WO2015159166A1 publication Critical patent/WO2015159166A1/fr

Links

Classifications

    • 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
    • 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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • 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
    • 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

Definitions

  • the present disclosure generally relates to the field of materials science, and more specifically to a cobalt-base superalloy with a ⁇ / ⁇ ' microstructure.
  • Embodiments herein particularly relate to a composition of high temperature resistant, tungsten free cobalt based superalloy.
  • Superalloys are based on Group VIIIB elements of periodic table and usually consist of various combinations of Iron (Fe). Nickel (Ni). Cobalt (Co), and Chromium (Cr). as well as lesser amounts of Tungsten (W). Molybdenum (Mo). Tantalum (Ta). Niobium (Nb). Titanium (Ti). and Aluminum (Al).
  • Three major classes of superalloys based on their base alloying element include nickel (Ni). cobalt (Co), or nickel-iron.
  • Some of the well- known superalloys developed include Hastelloy. Inconel (e.g. IN 100. IN600. IN713). Waspaloy. Rene alloys (e.g. Rene 41. Rene 80. Rene 95. Rene N5). Haynes alloys. Incoloy. MP98T. disk alloys such as TMS alloys and cast equiaxed. directionalK- solidified and single crystal alloys such as CMSX (e.g. CMSX-4).
  • ⁇ is a face-centered-cubic (FCC) structure that usually contains a high percentage of solid-solution elements such as Co. Cr. Mo. and W.
  • ⁇ precipitates, cuboidal in shape, have structure which is coherent with the ⁇ - ⁇ matrix with a lattice mismatch less than 0.5° o at the interface making the interfacial energy very low and hence increasing microstructural stability for long time exposure at high temperature.
  • Co has a higher melting point metal than nickel
  • superalloys are also developed w ith Co as the matrix.
  • Nickel based alloys exist in FCC form throughout the temperature range of application, while Co transforms to hexagonal close pack (HCP) structure at room temperature.
  • Cobalt based superalloys. such as Vitallium (Co-Cr-Mo) and Co-Ti alloys are biocompatible, and hence are used for orthopaedic implants because of their extremeh- high corrosive wear resistance.
  • Alloys such as Co-Cr-W-C (Stellite. Hayness) are used where both high temperature strength and corrosion resistance is required such as valves for IC engines. In these alloys the strengthening comes from the solid solution and metal carbides.
  • Carbon added at levels of 0.05-0.2° o. combines w ith reactive and refractory elements such as titanium, tantalum, and hafnium to form carbides (e.g.. TiC. TaC. or HfC). During heat treatment, these begin to decompose and form lower carbides such as M23C& and M&C. which tend to form on grain boundaries.
  • carbides e.g. TiC. TaC. or HfC.
  • Al Aluminum
  • Tungsten (W) addition is crucial and essential in this class of alloys to stabilize the ⁇ " phase although it reduces specific strength due to its high density.
  • Prior inventions considered tungsten (W) as an essential element to stabilize ⁇ " in Co base alloys. Since, tungsten (W) is not desirable because of high density, very high melting point making homogenization difficult, therefore current invention demonstrates tungsten (W) free Co base superalloys.
  • Yet another object of the present disclosure is to provide a ⁇ - ⁇ " cobalt based superalloys having better specific strength, compressive as well as tensile, good ductility in combination w ith good creep strength and corrosion resistance at elevated temperatures.
  • Yet another object of the present disclosure is to provide exemplary heat treatment process for tungsten free ⁇ - ⁇ " cobalt based superalloys for achieving claimed mechanical properties.
  • embodiments herein present the invention of a class of Tungsten (W) free Cobalt based ( ⁇ - ⁇ " ) superalloys with the basic chemical composition comprising in ° o by weight: 0.5 to 10 Aluminium (Al) and 1 to 15 Molybdenum (Mo) with atleast one or both of 0.5 to 12 Niobium (Nb) and 0.5 to 12 Tantalum (Ta). with the reminder being Cobalt (Co). Some part of the cobalt can be replaced by nickel (50° o or less).
  • Nickel added alloys can be added further w ith atleast one among the transition metals zirconium (5° o or less), hafnium (5° o or less), vanadium (5° o or less), titanium (5° o or less), and yttrium (5° o or less), boron (2° o or less), carbon (2° o or less), rhenium ( 10° o or less), ruthenium (5° o or less) for further fine tune the sohiis temperature, volume fraction of ⁇ " and creep properties.
  • the present disclosure provides a number of exemplan combinations of all or some of the above alloying elements to obtain superalloys exhibiting different capabilities.
  • Achievable superalloys are not limited to these exemplan- ones and it is possible for one conversant in the art to work out mam- other combinations to achieve claimed properties in accordance w ith the present disclosure.
  • Figure 1 illustrates an exemplan method for heat treatment of disclosed superalloys in accordance with an embodiment of the present invention.
  • Figure 2 illustrates an exemplan Transmission Electron Microscopy (TEM) diffraction pattern in [001] zone axis showing Ll 2 super-lattice reflections along with matrix reflections for Co-4.6Al-8.2Mo-3.2Nb alloy (alloy 1 ) after final aging heat treatment.
  • TEM Transmission Electron Microscopy
  • Figure 3 illustrates an exemplan Transmission Electron Microscopy (TEM) darkfield image taken from 010 super lattice Ll 2 spot in [001] zone axis for Co-4.6Al-8.2Mo- 3.2Nb alloy (alloy 1 ) after final aging heat treatment.
  • TEM Transmission Electron Microscopy
  • Figure 4 illustrates an exemplan comparison of densities of present invented alloys with other available cobalt based superalloys.
  • Figure 5 illustrates an exemplan comparison of DSC curves of present invented alloys (Alloy 1. Alloy 5. Alloy 6. and Alloy 8) with Co-3.6Al-24W alloy.
  • Figure 6 illustrates exemplan- comparison of 0.2°o compressive proof stress of present invented alloys with known Co-3.6Al-24.7W alloy at room temperature.
  • Figure 7 illustrates exemplan- comparison of specific 0.2°o compressive proof stress of present invented alloys with known Co-3.6Al-24.7W alloy at room temperature.
  • Figure 8 illustrates exemplan- comparison of 0.2°o compressive proof stress of present invented alloys with known Co-3.6Al-24.7W alloy at 87 () °C temperature.
  • Figure 9 illustrates exemplan- comparison of specific 0.2°o compressive proof stress of present invented alloys with known Co-3.6Al-24.7W alloy at 87 () °C temperature.
  • Figure 10 illustrates exemplan comparison of tensile test cun es of Alloy 1 as an example and Co-3.6Al-24.7W alloy.
  • Figure 1 1 illustrates exemplary comparison of 0.2°o tensile proof stress of Alloy 1.
  • Figure 12 illustrates exemplary comparison of specific 0.2°o tensile proof stress of Alloy 1. Alloy 4. Alloy 5 and Alloy 7 w ith known Co-3.6Al-24.7W and other commercially available cobalt superalloys.
  • Embodiments described herein generally relate to the field of materials science, and to a cobalt-base superalloy w ith a ⁇ / ⁇ ' microstmcture.
  • the described embodiments herein more particularly relate to compositions of high temperature resistant tungsten free cobalt based superalloys.
  • Embodiments herein describe Tungsten (W) free Cobalt based superalloy with base chemical compositions comprising in °o by weight: 0.5 to 10 Aluminium (Al). 1 to 15 Molybdenum (Mo), and one or both of 0.5 to 12 Niobium (Nb) and 0.5 to 12 Tantalum (Ta). w ith the remainder being Cobalt (Co).
  • Cobalt can be replaced by nickel (50° o or less) in the base alloy mentioned above.
  • transition metals such as chromium, platinum. palladium, iridium, titanium, vanadium, zirconium, hafnium, platinum, palladium, chromium. iron, iridium, ruthenium, rhenium, carbon and boron, atleast one among these can be a part of the Nickel added composition with respective purposes.
  • Table 1 show s eight different exemplan compositions of Co based superalloys in accordance w ith exemplan- embodiments of the present invention. It should be appreciated that the below compositions are purely exemplan- in nature and any other suitable composition w ithin the above mentioned range is completely w ithin the scope of the present disclosure. Each superalloy composition is designated w ith a number and referred as alloy 1. allov 2. allov 3. allov 4. allov 5. allov 6. allov 7 and allov 8.
  • Table 1 Composition of alloys weight % (atom
  • Figure 1 show s an exemplan- process flow chart ( 100) for producing above mentioned exemplan- tungsten (W) free cobalt based superalloys.
  • the process ( 100) can include heat treatment required to be perfomied on superalloys to achieve desired physical propertied of materials.
  • constituent elements required to make above mentioned compositions (table 1 ). can be melted, for example but not limited to. in an electric arc furnace. In an implementation. 30 grams of these constituent elements were melted in a laboraton- scale electric arc furnace having a w ater- cooled copper hearth. During this step, constituents were melted a number of times to ensure homogeneity. In an embodiment of laboratory scale process, this w as done 12 to 15 times to ensure homogeneity. However, such melting is not limited to any specific number of steps any change in the process or steps involved there in are w ithin the scope of the present invention.
  • molten material can be cast/molded in a mold, such as a copper mold, into desired shapes.
  • Casting is a process of manufacturing, wherein liquid metal or pliable raw material is given a required shape using a rigid frame called a mold. In a laboraton- scale embodiment, this can. for example, be done using water cooled copper mold, wherein the cast shape can be say a cylindrical rod.
  • cast alloy can be subjected to solution heat treatment (solutionized).
  • Solution heat treatment can be typically done on age or precipitation hardenable alloys, w hich gain strength due to presence of fine second phases fomied during precipitation hardening. SHT can be earned out before final ageing or precipitation heat treatment to reintroduce solute into a matrix so that it can be utilized to form a fine dispersion of phases on subsequent processing.
  • the solutionising temperature can be between 1 100 to 1400°C for time between 1 to 20 hours.
  • cylindrical rods were solutionised at 1300°C temperature for 15 his in a vacuum furnace.
  • SHT can be followed by water quenching, wherein quenching involves rapid cooling of an alloy to obtain supersaturated solid solution (SS) at room temperature. It prevents low -temperature processes. such as phase transformations, from occurring by providing only a narrow window of time in which reaction is both themiodynamically favorable and kinetically accessible.
  • Important parameters of quenching process include solutionising temperature from which alloy is quenched, and medium of quenching. In an embodiment, solutionising temperature depends on the alloy being processed and the medium determines the rate of cooling, which also depends on the alloy. In an embodiment, quenching of disclosed superalloys can be earned out from 13 ()() "C. w ith water being used as the cooling medium.
  • solutionised and quenched alloys can be subjected to process of aging, otherw ise known as precipitate hardening.
  • precipitate hardening Upon rapid cooling from high temperatures for example after quenching, alloys retain solute in the matrix at low temperatures. Aging of these alloys at intermediate temperatures decomposes supersaturated solid solution. Aging or precipitation hardening relies on this change in solid solubility with temperature to produce secondary phase - gamma prime ( ⁇ ' ) in the subject matter and hardens the material. Alloys must be kept at intermediate temperature for hours to allow precipitation or aging to take place.
  • the intermediate aging temperature can be between 5 ()() °C to 1 100°C for the present invented alloys.
  • all alloys (w ith reference to table 1 ) were vacuum sealed in quartz tube and aged at 800°C upto to the time when peak hardness was achieved. The time varies according to the alloy composition and is shown in table 2.
  • aged alloys can be cooled through furnace cooling, air cooling or quenching in water from the temperature at which aging was done. In the present embodiment all alloys were furnace cooled. For Ni added alloys (alloy 5. alloy 6. alloy 7 and alloy 8). cooling can be done by both air cooling or quenching in water. Air cooling and quenching in water was not done for alloy 1. alloy 2. alloy 3 and alloy 4 to avoid the transformation of FCC matrix (a-Co) to HCP ( ⁇ -Co).
  • the densities of the alloys were measured in accordance w ith ASTM standard B31 1-08 at room temperature.
  • Transmission Electrom Microscopy (TEM) FEI F30 is used for microstnictural studies and Differential Scanning Calorimetry (DSC) NETZSCH STA 449 F3 Jupiter is used for determination of melting and sohns temperature of the alloys. Peak age time for all the alloys was determined by measuring Vickers hardness (Hv) using 0.5 Kg load.
  • Figure 2 show s an exemplary TEM diffraction pattern for Alloy 1 after final aging heat treatment, along [001] zone axis showing L l 2 ⁇ " super lattice reflections along w ith ⁇ matrix reflections, in accordance w ith an embodiment of the present invention.
  • Figure 3 show s an exemplary TEM darkfield micrograph of alloy 1 taken from 010 super lattice spot which corresponds to ⁇ " . in [001] zone axis in accordance w ith an embodiment of the present invention. It is clear from darkfield micrograph that microstnicture contains L l 2 ordered cuboidal ⁇ " precipitates throughout the ⁇ matrix. Their size ranges from 25 to 50 11111 ,
  • Figure 4 show s an exemplary comparison of densities of the present invented alloys (table 1 ) w ith other commercially available cobalt superalloys and tungsten (W) containing cobalt superalloy (Co-3.6Al-24.7W) in accordance w ith the embodiment herein.
  • the present invented alloys have much lower densities compared to Co-3.6Al-24.7W and other cobalt superalloys (L-605. Hayness 188. Stellite).
  • Density of the alloys described in embodiments herein i.e. alloy 1. alloy 2. alloy 3. alloy 4. alloy 5. alloy 6. alloy 7 and alloy 8 are 8.36. 8.42. 8.46. 8.61. 8.38. 8.29.
  • Figure 5 shows exemplary comparison DSC heating curves of alloy 1. alloy 5. alloy 6 and alloy 8 w ith Co-3.6Al-24.7W alloy in accordance w ith the embodiment herein. As illustrated in the heating curve, the melting points for alloy 1 and alloy 5 are found to be 1315°C and 1355°C respectively, which are in the range of incipient melting points of nickel based superalloys. The solvus temperatures for Alloy 1 and Alloy 5 are 866°C and 976°C which are lower compared to Co-3.6Al-24.7W alloy (986°C). But. the Alloy 6 and Alloy 8 have values of 1026°C and 1068°C winch higher than the Co-3.6Al-24.7W alloy and commercially used nickel based superalloy (waspalloy).
  • Table 2 below show s exemplary peak hardness values for all the alloys (with reference to table 1 ) and Co-3.7Al-24.7W alloy (heat treatment schedule was given according to the reference [ 1]) in accordance w ith an embodiment of the present invention.
  • Alloy 1 attains peak hardness after aging of 2 hours, alloy 2.
  • alloy 6 and alloy 8 get peak hardness after aging of 10 hours while for Alloy 5 and Alloy 7. Peak hardness is attained in 5 hours.
  • Figure 6 shows exemplary results of compression tests performed at room temperature on all the alloys after subjecting them to heat treatment as disclosed above and compared with Co-3.6Al-24.7W alloy (heat treated according to the reference [ 1] ). As illustrated, compressive strength values for all present disclosed alloys are above the Co- 3.6A1-24.7W alloy except alloy 1. Alloy 7 showed 0.2° o compressive proof stress value of about 890 MPa which is higher than 780 MPa of Co-3.6Al-24.7W alloy.
  • Figure 7 shows specific 0.2° o compressive proof stress for all the alloys and it is clear that all present invented alloys have much higher values compared to Co-3.6Al-24.7W alloy. Among these. Alloy 7 has a higher value of 103 MPa/gm.cm "1 compared to 79.4 MPa/gm.cm "3 for Co-3.6Al-24.7W alloy.
  • Figure 8 show s exemplary results of compression tests performed at elevated temperature (at 870°C) on all the alloys after subjecting them to heat treatment as disclosed above and compared w ith Co-3.6Al-24.7W alloy.
  • Alloy 5 (535 MPa).
  • Alloy 6 (520 MPa) and Alloy 7 (530 MPa) showed higher 0.2° o compressive proof stress values than Co-3.6Al-24.7W (485 MPa) alloy and Alloy 4 (480 MPa) and Alloy 8 (490 MPa) show similar values as Co-3.6Al-24.7W alloy.
  • Figure 9 show s specific 0.2° o compressive stress values at 870°C for all the alloys. It is clear that present disclosed alloys (except alloy 1 and alloy 2) have much higher values (highest among these. Alloy 5 w ith 63.8 MPa/gm.cm " ) than the Co-3.6Al-24.7W having 49.4 MPa/gm.cm "'1 .
  • Table 3 show s comparison of density, peak hardness (Hv) and compression test results among all the present disclosure alloys and Co-3.6Al-24.7W alloy.
  • Figure 10 shows exemplan- tensile test cun e as an example for peak aged alloy 1 and for Co-3.6Al-24.7W alloy at room temperature. Comparison of 0.2° o tensile proof stress for alloy 1. alloy 4. alloy 5 and alloy 7 w ith Co-3.6Al-24.7W and other cobalt based superalloys (L605. Hayness 188. Stellite) were shown in figure 12. We see that for Co-3.6Al- 24.7W (made by us under identical condition) show s 0.2° o tensile proof stress of about 760 MPa but fracture immediateh (from the cun e) w ithout any elongation. But. alloy 1. alloy 4.
  • alloy 5 and alloy 7 show s ultimate tensile strength of about 835 MPa w ith 19° o elongation. 925 MPa w ith 16° o elongation. 950 MPa with 16 ° o elongation and 1000 MPa w ith 16° o elongation respectively (table 4).
  • Alloy 1. alloy 4. alloy 5 and alloy 7 have much higher values than L-605 (460 MPa). Hayness 188 (485 MPa). Stellite (635 MPa) and comparable to Co-3.6Al-24.7W alloy.
  • Figure 12 show s comparison of specific 0.2° o tensile proof stress for all above mentioned alloys and it is clear that Alloy 1. alloy 4. Alloy 5 and alloy 7 have much higher values than other cobalt based superalloys. Table 4 show s comparison of all tensile results among these superalloys. Table 4: Yield Strength and Specific Yield Strength at room temperature and 900 C

Landscapes

  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Les modes de réalisation de la présente invention concernent une classe de superalliages (γ – γ') à base de cobalt sans tungstène (W) dont la composition chimique de base comprend, en % massique : de 0,5 à 10 d'Aluminium (Al) et de 1 à 15 de Molybdène (Mo), ainsi que 0,5 à 12 de Niobium (Nb) et/ou 0,5 à 12 de Tantale (Ta), le reste étant du Cobalt (Co). Une partie du cobalt peut être remplacée par du nickel (en une proportion inférieure ou égale à 50 %). Dans les alliages à adjonction de nickel, une partie du cobalt ou du nickel peut être remplacée par au moins un des métaux de transition choisi dans le groupe constitué par : l'Iridium en une proportion inférieure ou égale à 10 %, le Platine en une proportion inférieure ou égale à 10 %, le Palladium en une proportion inférieure ou égale à 10 % ou le Chrome en une proportion inférieure ou égale à 15 %, ou une combinaison de ceux-ci. Toujours dans les alliages à adjonction de nickel, il est possible d'ajouter en outre au moins un des métaux de transition suivants : du zirconium (en une proportion inférieure ou égale à 5 %), de l'hafnium (en une proportion inférieure ou égale à 5 %), du vanadium (en une proportion inférieure ou égale à 5 %), du titane (en une proportion inférieure ou égale à 5 %), et de l'yttrium (en une proportion inférieure ou égale à 5 %), du bore (en une proportion inférieure ou égale à 2 %), du carbone (en une proportion inférieure ou égale à 2 %), du rhénium (en une proportion inférieure ou égale à 10 %), du ruthénium (en une proportion inférieure ou égale à 5 %) pour assurer une régulation plus précise de la température de solubilité, de la fraction volumique et des propriétés de fluage de la phase γ'.
PCT/IB2015/052076 2014-04-16 2015-03-21 Superalliage à base de cobalt sans tungstène à renforcement des phases gamma/gamma prime WO2015159166A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US15/304,479 US20170037498A1 (en) 2014-04-16 2015-03-21 Gamma - gamma prime strengthened tungsten free cobalt-based superalloy

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN1981CH2014 2014-04-16
IN1981/CHE/2014 2014-04-16

Publications (1)

Publication Number Publication Date
WO2015159166A1 true WO2015159166A1 (fr) 2015-10-22

Family

ID=53016621

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2015/052076 WO2015159166A1 (fr) 2014-04-16 2015-03-21 Superalliage à base de cobalt sans tungstène à renforcement des phases gamma/gamma prime

Country Status (2)

Country Link
US (1) US20170037498A1 (fr)
WO (1) WO2015159166A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109576534A (zh) * 2019-01-25 2019-04-05 北京科技大学 一种低钨含量γ`相强化钴基高温合金及其制备工艺
CN109811199A (zh) * 2019-02-21 2019-05-28 宁国市华成金研科技有限公司 一种定向凝固钴基高温合金的制备方法
CN114953633A (zh) * 2022-06-16 2022-08-30 王晓凤 一种耐高温高压防腐延展性强的2132ah航天材料及制备方法
CN115786778A (zh) * 2022-06-22 2023-03-14 得利钟表制品厂有限公司 钴基合金、可佩戴物品和金属制品的制备方法

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109837424A (zh) * 2017-11-29 2019-06-04 中国科学院金属研究所 一种稳定γ′相强化的Co-Ni基高温合金及制备方法
WO2019226731A1 (fr) * 2018-05-22 2019-11-28 Northwestern University Superalliages à base de cobalt à précipités gamma-prime stables, leur procédé de production
CN111004945B (zh) * 2019-12-31 2020-11-24 东北大学秦皇岛分校 一种含钼钴基高温合金及其用途
CN113897517B (zh) * 2020-06-22 2023-03-28 首尔国立大学校产学协力财团 具有自我修复特性的钴基合金及其制造方法
CN113684397B (zh) * 2021-08-26 2022-05-13 大连理工大学 一种具有立方形γ′共格强化的低成本轻质Co基高温合金及制备方法
CN113684398B (zh) * 2021-08-26 2022-05-13 大连理工大学 900℃组织稳定的立方形γ′纳米粒子共格析出强化的高温合金及制备方法
CN113684396B (zh) * 2021-08-26 2022-05-13 大连理工大学 一种高含量方形纳米粒子析出强化的γ′-Ni3Al基低成本高温合金及制备方法
CN114032433B (zh) * 2021-10-13 2022-08-26 中南大学深圳研究院 钴基高温合金及其制备方法和热端部件
CN115874085B (zh) * 2022-09-29 2024-02-20 浙江大学 一种纳米相增强的无钨钴镍基高温合金及其制备方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4908069A (en) * 1987-10-19 1990-03-13 Sps Technologies, Inc. Alloys containing gamma prime phase and process for forming same
JP2000219911A (ja) * 1999-01-29 2000-08-08 Dai Ichi High Frequency Co Ltd 高温ハースローラー
US20080185078A1 (en) 2005-09-15 2008-08-07 Japan Science And Technology Agency Cobalt-base alloy with high heat resistance and high strength and process for producing the same
CN101654754A (zh) * 2009-08-27 2010-02-24 北京航空航天大学 一种Co-M-C合金及其采用液态金属冷却法制备Co-M-C合金的方法
US20100061883A1 (en) 2008-09-08 2010-03-11 Alstom Technology Ltd High-temperature-resistant cobalt-base superalloy
US20120312434A1 (en) 2011-06-09 2012-12-13 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
CN103045910A (zh) 2013-01-16 2013-04-17 北京科技大学 一种高温稳定γ’相强化的钴基高温合金及其制备方法

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4908069A (en) * 1987-10-19 1990-03-13 Sps Technologies, Inc. Alloys containing gamma prime phase and process for forming same
JP2000219911A (ja) * 1999-01-29 2000-08-08 Dai Ichi High Frequency Co Ltd 高温ハースローラー
US20080185078A1 (en) 2005-09-15 2008-08-07 Japan Science And Technology Agency Cobalt-base alloy with high heat resistance and high strength and process for producing the same
US20100061883A1 (en) 2008-09-08 2010-03-11 Alstom Technology Ltd High-temperature-resistant cobalt-base superalloy
CN101654754A (zh) * 2009-08-27 2010-02-24 北京航空航天大学 一种Co-M-C合金及其采用液态金属冷却法制备Co-M-C合金的方法
US20120312434A1 (en) 2011-06-09 2012-12-13 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
CN103045910A (zh) 2013-01-16 2013-04-17 北京科技大学 一种高温稳定γ’相强化的钴基高温合金及其制备方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
P. MOULIN ET AL: "Water resistance of resin-bonded joints with time related to alloy surface treatment", JOURNAL OF DENTISTRY, vol. 27, no. 1, 1 January 1999 (1999-01-01), pages 79 - 87, XP055197195, ISSN: 0300-5712, DOI: 10.1016/S0300-5712(98)00033-5 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109576534A (zh) * 2019-01-25 2019-04-05 北京科技大学 一种低钨含量γ`相强化钴基高温合金及其制备工艺
CN109811199A (zh) * 2019-02-21 2019-05-28 宁国市华成金研科技有限公司 一种定向凝固钴基高温合金的制备方法
CN114953633A (zh) * 2022-06-16 2022-08-30 王晓凤 一种耐高温高压防腐延展性强的2132ah航天材料及制备方法
CN115786778A (zh) * 2022-06-22 2023-03-14 得利钟表制品厂有限公司 钴基合金、可佩戴物品和金属制品的制备方法
CN115786778B (zh) * 2022-06-22 2024-03-01 得利钟表制品厂有限公司 钴基合金、可佩戴物品和金属制品的制备方法

Also Published As

Publication number Publication date
US20170037498A1 (en) 2017-02-09

Similar Documents

Publication Publication Date Title
US20170037498A1 (en) Gamma - gamma prime strengthened tungsten free cobalt-based superalloy
JP6793689B2 (ja) Ｎｉ基合金部材の製造方法
EP2503013B1 (fr) Superalliage réfractaire
JP7012468B2 (ja) 超合金物品及び関連物品の製造方法
JP6965364B2 (ja) 析出硬化型コバルト−ニッケル基超合金およびそれから製造された物品
CN113106299B (zh) Ni基锻造合金材料的制造方法
US20200048743A1 (en) Highly processable single crystal nickel alloys
JP6826235B2 (ja) Ｎｉ基合金軟化粉末および該軟化粉末の製造方法
WO1994000611A9 (fr) Superalliage monocristallin a base de nickel
WO1994000611A1 (fr) Superalliage monocristallin a base de nickel
JPS6339651B2 (fr)
JP7138689B2 (ja) 高温耐性、耐傷性を有する超合金、その合金から作られた製品、及びその合金の製造方法
JP7073051B2 (ja) 超合金物品及び関連物品の製造方法
JP2017514998A (ja) 析出硬化ニッケル合金、前記合金でできた部品、及びその製造方法
US20230025204A1 (en) Nickel-base alloys
US5358584A (en) High intermetallic Ti-Al-V-Cr alloys combining high temperature strength with excellent room temperature ductility
JP2012107269A (ja) ニッケル基耐熱超合金と耐熱超合金部材
Karthikeyan et al. PROCESSING AND CHARACTERIZATION OF INCONEL 718 AND ICNI-5510-718 SUPER ALLOYS FOR SPACE APPLICATIONS

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 15719510

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 15304479

Country of ref document: US

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 15719510

Country of ref document: EP

Kind code of ref document: A1