CN111041278B - A γ'-phase-strengthened Co-Ni-Al-Ta-based superalloy - Google Patents
A γ'-phase-strengthened Co-Ni-Al-Ta-based superalloy Download PDFInfo
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 28
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 80
- 239000000956 alloy Substances 0.000 claims abstract description 80
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 19
- 239000000126 substance Substances 0.000 claims abstract description 16
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 16
- 238000005728 strengthening Methods 0.000 claims abstract description 11
- 238000001556 precipitation Methods 0.000 claims abstract description 7
- 239000011159 matrix material Substances 0.000 claims abstract description 3
- 239000000463 material Substances 0.000 claims description 48
- 238000003723 Smelting Methods 0.000 claims description 25
- 239000006104 solid solution Substances 0.000 claims description 20
- 239000012300 argon atmosphere Substances 0.000 claims description 14
- 230000032683 aging Effects 0.000 claims description 13
- 239000005457 ice water Substances 0.000 claims description 12
- 238000010791 quenching Methods 0.000 claims description 12
- 230000000171 quenching effect Effects 0.000 claims description 12
- 238000005266 casting Methods 0.000 claims description 11
- 238000001816 cooling Methods 0.000 claims description 11
- 238000005303 weighing Methods 0.000 claims description 11
- 238000002360 preparation method Methods 0.000 claims description 4
- 230000006698 induction Effects 0.000 claims description 3
- 229910052804 chromium Inorganic materials 0.000 abstract description 8
- 229910052721 tungsten Inorganic materials 0.000 abstract description 4
- 229910052720 vanadium Inorganic materials 0.000 abstract description 4
- 239000000203 mixture Substances 0.000 abstract description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 24
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 16
- 239000000243 solution Substances 0.000 description 16
- 229910052759 nickel Inorganic materials 0.000 description 12
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 10
- 229910052786 argon Inorganic materials 0.000 description 8
- 238000010891 electric arc Methods 0.000 description 7
- 229910017052 cobalt Inorganic materials 0.000 description 4
- 239000010941 cobalt Substances 0.000 description 4
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000001000 micrograph Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 108090000765 processed proteins & peptides Proteins 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 229910002058 ternary alloy Inorganic materials 0.000 description 1
- 238000004627 transmission electron microscopy Methods 0.000 description 1
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- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
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- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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Abstract
本发明公开了一种γ’相强化型Co‑Ni‑Al‑Ta基高温合金，不含W和V元素，其微观组织特征包括均匀分布的立方状有序的γ’相和基体γ相；其中，该γ’相的固溶温度为1100‑1280℃；且该合金的析出强化相为γ’‑Co3(Al，Ta)相；该合金的成分按原子百分数为：Ni为30‑50％，Al为8‑16％，Ta为2‑10％，Cr为0‑20％，Co为余量。本发明的化学成分、析出强化相均与现有技术完全不同，并具有较低的密度(8.1‑8.8g.cm‑3)、较高的γ’相体积分数(50‑80％)和较高的γ’相固溶温度(1100‑1280℃)。
The invention discloses a γ' phase-strengthened Co-Ni-Al-Ta-based superalloy, which does not contain W and V elements, and whose microstructure features include uniformly distributed cubic ordered γ' phases and matrix γ phases; Wherein, the solution temperature of the γ' phase is 1100-1280 ℃; and the precipitation strengthening phase of the alloy is γ'-Co 3 (Al, Ta) phase; the composition of the alloy is: Ni is 30-50 %, Al is 8‑16%, Ta is 2‑10%, Cr is 0‑20%, and Co is the balance. The chemical composition and precipitation strengthening phase of the present invention are completely different from those of the prior art, and have lower density (8.1-8.8g.cm -3 ), higher volume fraction of γ' phase (50-80%) and higher High γ' phase solution temperature (1100‑1280℃).
Description
Technical Field
The invention belongs to the technical field of new materials, and particularly relates to a gamma' phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
Background
The high-temperature alloy is widely applied to hot end parts of aerospace, ships, gas turbines, nuclear reactor and the like. Among them, the nickel-base superalloy relies on a superalloy having L12Structural strengthening phase gamma' -Ni3(Al, Ti) to obtain excellent high-temperature mechanical properties, so that the alloy is widely applied to blades of aeroengines and industrial gas turbines. However, nickel-base superalloys have limited temperature capability, and their ultimate service temperature (about 1100 ℃) has approached the incipient melting temperature of the alloy. Compared with nickel-based high-temperature alloy, the traditional cobalt-based high-temperature alloy has higher melting point, excellent hot corrosion resistance and thermal fatigue resistance, so that the cobalt-based high-temperature alloy is widely applied to static parts such as turbine guide vanes of aircraft engines and gas turbines. However, conventional cobalt-based superalloys rely primarily on solid solution strengthening and carbide precipitation strengthening, and lack γ' -Ni similar to nickel-based superalloys3The (Al, Ti) ordered strengthening phase makes the temperature bearing capacity and the comprehensive performance far inferior to those of the nickel-based high-temperature alloy.
In 2006, Ishida et al found a peptide with L12Structural gamma' -Co3Strengthening the (Al, W) phase and preparing the Co-Al-W-based high-temperature alloy with a gamma/gamma' two-phase structure. The Co-Al-W-based high-temperature alloy has a higher melting point (about 1450 ℃) which is 50-150 ℃ higher than that of the Ni-based single-crystal high-temperature alloy, so that the alloy is expected to become a next-generation high-temperature structural material. However, the Co-Al-W based alloys still have problems of low γ' phase solution temperature, high alloy density, and the like. Therefore, how to design and prepare a Co-based superalloy with both a high γ' phase solution temperature and a low density is one of the important issues to be solved urgently in the field.
In recent years, Co-based superalloys have been disclosed as important high-temperature structural materials. CN101248198A (high temperature resistant cobalt-based high temperature alloy) discloses a Co-Al-W-based high temperature alloy, which has higher melting point. However, the density of the alloy is increased sharply (9.2-10 g.cm) due to the addition of a large amount of W element with large specific gravity-3) And the application of the alloy in an aircraft engine is not facilitated. CN104630569A (aGamma' phase strengthened Co-based high temperature alloy with high temperature stability and its preparation process) discloses a Co-V-Ta-based high temperature alloy with high strength. However, the gamma' solid solution temperature of the alloy is low, which is not beneficial to the service of the material at high temperature. CN109207799A (Co-Ni-V-Al based high temperature alloy strengthened by stable gamma 'phase) discloses a Co-Ni-Al-V based high temperature alloy which has higher gamma' phase solid solution temperature and lower density. However, such alloys add a large amount of V element for raising the γ' phase solution temperature of the alloy, so that the manufacturing cost of the alloy is significantly increased.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a gamma' phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The technical scheme of the invention is as follows:
gamma' phase reinforced Co-Ni-Al-Ta-based high-temperature alloy with density of 8.1-8.8g.cm-3The microstructure characteristics comprise uniformly distributed cuboidal ordered gamma' phase and matrix gamma phase; wherein the volume fraction of the gamma' -phase in the alloy is 50-80%, and the solid solution temperature is 1100-1280 ℃; and the precipitation strengthening phase of the alloy is gamma' -Co3A (Al, Ta) phase,
the alloy comprises the following components in atomic percentage: 30-50% of Ni, 8-16% of Al, 2-10% of Ta, 0-20% of Cr and the balance of Co.
In a preferred embodiment of the invention, the components are as follows in atomic percent: 30-50% of Ni, 8-14% of Al, 2-6% of Ta and the balance of Co.
In a preferred embodiment of the invention, the components are as follows in atomic percent: 30% of Ni, 10-12% of Al, 4-6% of Ta, 4-20% of Cr and the balance of Co.
In a preferred embodiment of the invention, the components are as follows in atomic percent: 40% of Ni, 12-14% of Al, 4-6% of Ta, 10-15% of Cr and the balance of Co.
In a preferred embodiment of the invention, the components are as follows in atomic percent: 40% of Ni, 10-12% of Al, 6-10% of Ta, 15-20% of Cr and the balance of Co.
In a preferred embodiment of the invention, the components are as follows in atomic percent: 50% of Ni, 10-14% of Al, 4-6% of Ta, 10-15% of Cr and the balance of Co.
The preparation method of the gamma' phase reinforced Co-Ni-Al-Ta-based high-temperature alloy comprises the following steps:
(1) weighing high-purity simple substance materials according to the atomic percentage;
(2) placing the simple substance material in a vacuum arc furnace or a vacuum induction furnace, vacuumizing and smelting in an argon atmosphere to obtain a uniformly smelted cast material;
(3) and (2) placing the casting material in an argon atmosphere, carrying out solid solution treatment for 4-24h at 1200-1300 ℃, then carrying out aging treatment for 24-120h at 700-900 ℃, and then carrying out ice water quenching or air cooling to obtain the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The invention has the beneficial effects that:
1. the chemical components of the invention are completely different from the prior art: the alloy does not contain W and V elements, and is quite different from the technical schemes disclosed in CN101248198A, CN104630569A and CN109207799A in the alloy composition.
2. The precipitation strengthening phase of the invention is completely different from the prior art: the precipitation strengthening phase of the invention is gamma' -Co3(Al, Ta) phase (shown in FIG. 1 as alloy γ' -Co)3(transmission electron microscopy image of Al, Ta) precipitate phase), different from the γ' -Co disclosed in CN101248198A3(Al, W) phase, gamma' -Co disclosed in CN104630569A3(V, Ta) phase and gamma' -Co disclosed in CN109207799A3(Al, V) phase.
3. The invention has lower density: the invention does not contain large specific gravity W element (the density is about 19.3 g.cm)-3) And a large amount of low specific gravity Al (density of about 2.7 g.cm) is added-3) And Cr element (density about 7.2 g.cm)-3) And the lightweight design of the alloy is realized. Therefore, the present invention has a lower density (8.1-8.8 g.cm) compared to the Co-Al-W group disclosed in CN101248198A-3) (ii) a As shown in fig. 2, the density of the present inventionIs basically equivalent to Co-Al-V base (CN109207799A) alloy without W element and is obviously superior to the Co-Al-W base alloy disclosed in CN101248198A and the traditional Co base commercial high-temperature alloy Mar-M-302.
4. The invention has higher gamma' phase solid solution temperature: as a large amount of Ni and Ta elements are added, the gamma 'phase solid solution temperature in the alloy is rapidly increased, as shown in figure 3, the gamma' phase solid solution temperature of the invention is 1100-1280 ℃, which is obviously superior to the Co-Al-W-based alloy disclosed by CN101248198A and also obviously superior to the Co-V-Ta-based alloy disclosed by CN104630569A, and the alloy is expected to be applied at higher temperature.
Drawings
FIG. 1 is a transmission electron microscope image of a Co-10Al-10Ta ternary alloy aged for 48h at 800 ℃.
FIG. 2 is a graph comparing the density of the alloy with other Co-based superalloys.
FIG. 3 is a gamma prime solution temperature comparison of the alloy with other Co-based superalloys.
FIG. 4 is a microstructure image of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloy prepared in example 2, which was subjected to solution treatment at 1280 ℃ for 12 hours and then aged at 700 ℃ for 96 hours.
FIG. 5 is a microstructure image of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloy prepared in example 3, which was subjected to a solution treatment at 1250 ℃ for 12 hours and then aged at 800 ℃ for 48 hours.
Detailed Description
The technical solution of the present invention will be further illustrated and described below with reference to the accompanying drawings by means of specific embodiments.
The following table 1 shows the specific atomic percentages of the gamma prime strengthened Co-Ni-Al-Ta based superalloys of the examples:
TABLE 1 atomic percentage table of various gamma' -phase strengthened Co-Ni-Al-Ta-based superalloy prepared in the examples of the present invention
The preparation process of the following examples is as follows:
(1) weighing high-purity simple substance materials according to the atomic percentage;
(2) placing the simple substance material in a vacuum arc furnace or a vacuum induction furnace, vacuumizing and smelting in an argon atmosphere to obtain a uniformly smelted cast material;
(3) and (2) placing the casting material in an argon atmosphere, carrying out solid solution treatment for 4-24h at 1200-1300 ℃, then carrying out aging treatment for 24-120h at 700-900 ℃, and then carrying out ice water quenching or air cooling to obtain the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
Example 1
Weighing high-purity Co, Ni, Al and Ta elementary substance materials according to the atomic percentage shown in alloy 1 in the table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted in a smelting furnace for more than 4 times to obtain a uniformly smelted cast material. Then, in argon atmosphere, the casting material is placed at 1300 ℃ for solution treatment for 12-24h, then ice water quenching is carried out, aging is carried out for 96h at 700 ℃, ice water quenching and cooling are carried out, and the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy with the density of 8.53g.cm is obtained-3The solid solution temperature of the gamma 'phase is 1102 ℃ and the volume fraction of the gamma' phase is 54%.
Example 2
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentage shown in alloy 2 in table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and quenching and cooling are carried out by ice water, thus obtaining the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy with the density of 8.61g.cm-3The solid solution temperature of the gamma 'phase is 1122 ℃ and the volume fraction of the gamma' phaseThe content was found to be 58%.
FIG. 4 is a microstructure image of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloy prepared in this example after solution treatment at 1280 ℃ for 12 hours and aging at 700 ℃ for 96 hours. As can be seen from FIG. 4, the γ ' phase strengthened Co-Ni-Al-Ta-based superalloy prepared in the embodiment can maintain the morphology of a γ/γ ' two-phase microstructure after heat treatment, and the volume fraction of the γ ' phase is more than 50%.
Example 3
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentage shown in alloy 3 in table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted in a smelting furnace for more than 8 times to obtain a uniformly smelted cast material. Then, in argon atmosphere, the casting material is placed at 1260 ℃ for solid solution treatment for 4h, after ice water quenching, aging treatment is carried out for 48h at 800 ℃, and air cooling is carried out to obtain the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy with the density of 8.62g.cm-3The solid solution temperature of the gamma 'phase is 1183 ℃, and the volume fraction of the gamma' phase is 62%.
FIG. 5 is a microstructure image of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloy prepared in this example after solution treatment at 1250 ℃ for 12 hours and aging at 800 ℃ for 48 hours. As can be seen from FIG. 5, the γ ' phase strengthened Co-Ni-Al-Ta-based superalloy prepared in the embodiment can maintain the microstructure morphology of γ/γ ' two phases after heat treatment, and the volume fraction of the γ ' phase is more than 50%.
Example 4
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentage shown in alloy 4 in the table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and ice water quenching cooling is carried out to obtain the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy with the density of 8.55g.cm-3The solid solution temperature of the gamma 'phase is 1145 ℃ and gamma'The phase volume fraction was 73%.
Example 5
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentages shown by alloys 5, 6, 7 and 8 in the table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and quenching and cooling are carried out by ice water, thus obtaining the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The densities of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloys corresponding to alloys 5, 6, 7 and 8 in Table 1 were 8.44g.cm, respectively-3、8.48g.cm-3、8.56g.cm-3And 8.25g.cm-3The solid solution temperature of the gamma 'phase is 1125 ℃, 1140 ℃, 1156 ℃ and 1160 ℃ respectively, and the volume fraction of the gamma' phase is 65%, 58%, 79% and 73% respectively.
Example 6
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentages shown in alloys 9, 10 and 11 in the table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and quenching and cooling are carried out by ice water, thus obtaining the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The densities of the gamma prime strengthened Co-Ni-Al-Ta based superalloys corresponding to alloys 9, 10 and 11 in Table 1 were 8.66g.cm, respectively-3、8.74g.cm-3And 8.7g.cm-3The solid solution temperature of the gamma 'phase is 1158 ℃, 1162 ℃ and 1135 ℃, and the volume fraction of the gamma' phase is 51%, 66% and 78% respectively.
Example 7
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentages shown by alloys 12, 13, 14 and 15 in the table 1; putting the proportioned material intoVacuum-pumping to 6.6 × 10 in a vacuum arc furnace-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and quenching and cooling are carried out by ice water, thus obtaining the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The densities of the γ' -phase strengthened Co-Ni-Al-Ta-based superalloys corresponding to alloys 12, 13, 14 and 15 in Table 1 were 8.47g.cm, respectively-3、8.55g.cm-3、8.72g.cm-3And 8.6g.cm-3The solid solution temperature of the gamma 'phase is 1109 ℃, 1184 ℃, 1192 ℃ and 1120 ℃ respectively, and the volume fraction of the gamma' phase is 59%, 66%, 75% and 53% respectively.
Example 8
Weighing high-purity Co, Ni, Al, Ta and Cr elementary substance materials according to the atomic percentages shown in alloys 16, 17, 18 and 19 in the table 1; putting the proportioned material into a vacuum electric arc furnace, and vacuumizing to 6.6 multiplied by 10-3And introducing argon for smelting protection after Pa is lower than Pa. The alloy is repeatedly smelted for more than 6 times in a smelting furnace to obtain a cast material with uniform smelting. Then, in argon atmosphere, the casting material is placed at 1250 ℃ for solution treatment for 12h, then aging is carried out for 48h at 800 ℃, and quenching and cooling are carried out by ice water, thus obtaining the gamma' -phase reinforced Co-Ni-Al-Ta-based high-temperature alloy.
The densities of the gamma' -phase strengthened Co-Ni-Al-Ta-based superalloys corresponding to 16, 17, 18 and 19 in Table 1 were 8.47g.cm, respectively-3、8.66g.cm-3、8.14g.cm-3And 8.4g.cm-3The solid solution temperature of the gamma 'phase is 1149 ℃, 1273 ℃, 1152 ℃ and 1150 ℃, and the volume fraction of the gamma' phase is 59%, 78%, 68% and 72% respectively.
The above description is only a preferred embodiment of the present invention, and therefore should not be taken as limiting the scope of the invention, which is defined by the appended claims.
Claims (7)
1. Gamma' phase reinforced Co-Ni-Al-Ta based superalloyIs characterized in that: the density is 8.1-8.8g.cm-3The microstructure characteristics comprise uniformly distributed cuboidal ordered gamma' phase and matrix gamma phase; wherein the volume fraction of the gamma' -phase in the alloy is 50-80%, and the solid solution temperature is 1100-1280 ℃; and the precipitation strengthening phase of the alloy is gamma' -Co3(Al, Ta) phase, the alloy comprising, in atomic percent: 30-50% of Ni, 8-16% of Al, 2-10% of Ta, 0-20% of Cr and the balance of Co.
2. A gamma prime strengthened Co-Ni-Al-Ta based superalloy as in claim 1, wherein: the components by atomic percentage are as follows: 30-50% of Ni, 8-14% of A1, 2-6% of Ta and the balance of Co.
3. A gamma prime strengthened Co-Ni-a1-Ta based superalloy as in claim 1, wherein: the components by atomic percentage are as follows: 30% of Ni, 10-12% of Al, 4-6% of Ta, 4-20% of Cr and the balance of Co.
4. A gamma prime strengthened Co-Ni-Al-Ta based superalloy as in claim 1, wherein: the components by atomic percentage are as follows: 40% of Ni, 12-14% of Al, 4-6% of Ta, 10-15% of Cr and the balance of Co.
5. A gamma prime strengthened Co-Ni-a1-Ta based superalloy as in claim 1, wherein: the components by atomic percentage are as follows: 40% of Ni, 10-12% of Al, 6-10% of Ta, 15-20% of Cr and the balance of Co.
6. A gamma prime strengthened Co-Ni-a1-Ta based superalloy as in claim 1, wherein: the components by atomic percentage are as follows: 50% of Ni, 10-14% of Al, 4-6% of Ta, 10-15% of Cr and the balance of Co.
7. The γ' phase strengthened Co-Ni-a1-Ta based superalloy as in any of claims 1-6, wherein: the preparation method comprises the following steps:
(1) weighing high-purity simple substance materials according to the atomic percentage;
(2) placing the simple substance material in a vacuum arc furnace or a vacuum induction furnace, vacuumizing and smelting in an argon atmosphere to obtain a uniformly smelted cast material;
(3) and (2) placing the casting material in an argon atmosphere, carrying out solid solution treatment for 4-24h at 1200-1300 ℃, then carrying out aging treatment for 24-120h at 700-900 ℃, and then carrying out ice water quenching or air cooling to obtain the gamma' -phase reinforced Co-Ni-A1-Ta-based high-temperature alloy.
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| CN102234732A (en) * | 2010-04-29 | 2011-11-09 | 通用电气公司 | Cobalt-nickel superalloys, and related articles |
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