CN110241331B - Nickel-based powder superalloy and preparation method and application thereof - Google Patents
Nickel-based powder superalloy and preparation method and application thereof Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
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- 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%
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- 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%
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- 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
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Abstract
The invention relates to a nickel-based powder superalloy and a preparation method and application thereof. The nickel-based powder superalloy comprises the following components in percentage by mass: 0.02 to 0.10 percent of C, 14.0 to 22.0 percent of Co, 6.0 to 14.0 percent of Cr, 1.8 to 4.0 percent of Mo, 3.0 to 6.0 percent of W, 2.5 to 6.0 percent of Ta, 2.8 to 4.0 percent of Al, 2.6 to 4.4 percent of Ti, 1.2 to 3.2 percent of Nb, 0.1 to 0.5 percent of Hf, 0.01 to 0.08 percent of Zr, 0.01 to 0.08 percent of B, 0.3 to 6.0 percent of Os and/or 0.5 to 6.0 percent of Ru, and the balance of Ni. The nickel-based powder superalloy has excellent high-temperature tensile strength, yield strength, high-temperature durability and a higher maximum working temperature.
Description
Technical Field
The invention relates to the field of powder superalloy, in particular to nickel-based powder superalloy and a preparation method and application thereof.
Background
The turbine disk is one of the most important hot end parts in the aircraft engine, and in the service process, the hub bears the extremely high centrifugal force and needs high tensile strength, and the temperature of the wheel rim is higher than that of the hub, so that good high-temperature endurance performance and creep resistance are needed. The aeroengine turbine disc has strict requirements on materials, the turbine disc alloy is required to have high tensile strength, high damage tolerance, high creep property, high thermal fatigue property, excellent oxidation resistance, excellent corrosion resistance and the like, and the topological closely-spaced (TCP) phase precipitation tendency of the turbine disc alloy in the long-term service process is required to be very small, so that the alloy has good high-temperature structure stability, and the attenuation of the mechanical property of the alloy is reduced to the minimum.
With the development of aero-engines, the working temperature of a turbine disc is higher and higher, and the operating temperature of the turbine disc is required to reach 815 ℃ in the currently newly developed and developed aero-engine. The maximum service temperature of the existing nickel-based powder high-temperature alloys for the turbine disk, such as FGH4095, FGH4096, FGH4097, FGH4098 and the like, is limited to 650-750 ℃, and serious TCP phase appears when the temperature exceeds 750 ℃, and the alloys can not meet the requirement of maintaining lasting high performance at 815 ℃.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
A first object of the present invention is to provide a nickel-based powder superalloy having an excellent balance of composition and content that imparts excellent high temperature tensile strength, yield strength, and high temperature durability properties and a higher maximum operating temperature to the nickel-based powder superalloy.
The second purpose of the invention is to provide the preparation method of the nickel-based powder superalloy, which is efficient, easy and good in reproducibility, and the prepared nickel-based powder superalloy has high microstructure stability.
A third object of the present invention is to provide an aircraft device to which the above nickel-based powder superalloy is applied.
In order to achieve the above purpose of the present invention, the following technical solutions are adopted:
the nickel-based powder superalloy comprises the following components in percentage by mass:
0.02-0.10% of C, 14.0-22.0% of Co, 6.0-14.0% of Cr, 1.8-4.0% of Mo, 3.0-6.0% of W, 2.5-6.0% of Ta, 2.8-4.0% of Al, 2.6-4.4% of Ti, 1.2-3.2% of Nb, 0.1-0.5% of Hf, 0.01-0.08% of Zr, 0.01-0.08% of B, 0.3-6.0% of Os0.5-6.0% of Ru0 and the balance of Ni;
the total mass fraction of Al, Ti, Nb, Ta and Hf in the nickel-based powder superalloy is 12.5-15.5%.
Optionally, the nickel-based powder superalloy has a composition comprising, in mass fractions:
0.03 to 0.08 percent of C, 15.0 to 20.0 percent of Co, 7.0 to 13.0 percent of Cr, 2.6 to 3.8 percent of Mo, 3.2 to 5.5 percent of W, 2.6 to 3.8 percent of Ta, 3.0 to 4.0 percent of Al, 2.8 to 4.2 percent of Ti, 1.4 to 3.0 percent of Nb, 0.15 to 0.45 percent of Hf, 0.01 to 0.06 percent of Zr, 0.01 to 0.06 percent of B, 0.3 to 3.0 percent of Os and/or 0.5 to 3.0 percent of Rus, and the balance of Ni.
Optionally, the nickel-based powder superalloy has a composition comprising, in mass fractions:
0.04 to 0.07 percent of C, 16.0 to 19.0 percent of Co, 8.0 to 12.0 percent of Cr, 2.7 to 3.6 percent of Mo, 3.4 to 5.0 percent of W, 2.8 to 3.6 percent of Ta, 3.1 to 4.0 percent of Al, 3.0 to 4.0 percent of Ti, 1.6 to 2.8 percent of Nb, 0.2 to 0.4 percent of Hf, 0.01 to 0.06 percent of Zr, 0.01 to 0.06 percent of B, 0.3 to 3.0 percent of Os and/or 0.5 to 3.0 percent of Rus, and the balance of Ni.
The main technical scheme of the invention is that the precipitation tendency of a topological close-packed (TCP) phase is reduced by controlling the contents of Cr, Mo, W and Ru, and simultaneously high-temperature tensile strength and yield strength and excellent high-temperature endurance strength of the alloy are realized by adding solid solution strengthening elements (Co, Cr, Mo, W and Ru), gamma' phase forming elements (Al, Ti, Nb, Ta and Hf) and grain boundary strengthening elements (Zr and B), so that the component range with good comprehensive performance is obtained. The micron-sized pre-alloyed powder of the powder high-temperature alloy is formed by cooling at a high cooling speed, so that the alloy has uniform components, uniform microstructure and dispersed precipitated phases, macrosegregation is eliminated, the hot-working performance is improved, the alloying degree can be further improved, and the alloy has good tensile core-stem, high-temperature durability and creep resistance. By coordinately controlling the contents of Co, Cr, Mo, W, Ta and other elements, the tendency of TCP phase precipitation is reduced, and the high-temperature structure stability of the alloy is improved.
Optionally, the total mass fraction of Co, Cr, Mo, W in the nickel-based powder superalloy is 30% to 38%.
Optionally, the total mass fraction of Co, Cr, Mo, and W in the nickel-based powder superalloy is 32% to 36%.
Optionally, the total mass fraction of W, Ta, and Ru in the nickel-based powder superalloy is 8.5% to 14.0%.
Optionally, the total mass fraction of W, Ta, and Ru in the nickel-based powder superalloy is 9.0% to 12.0%.
Optionally, the major precipitated phases of the nickel-based powder superalloy include a gamma-matrix, a gamma' -phase, MC, and M3B2And (4) phase(s).
The microstructure of the alloy of the invention is mainly composed of gamma, gamma', MC and M3B2Phase composition, gamma' phase composition (Ni, Co)3The composition of the (Al, Ti, Ta, Nb, Hf) type and MC type carbides is (Ti, Ta, Nb, Hf) C type.
Optionally, the content of the gamma 'phase in the nickel-based powder superalloy is 55-65% by mass, and the complete dissolution temperature of the gamma' phase is 1180-1220 ℃.
Optionally, the content of the γ 'phase in the nickel-based powder superalloy is 60%, and the complete dissolution temperature of the γ' phase is 1200 ℃ to 1220 ℃.
Optionally, when the nickel-based powder superalloy contains Ru, the mass fraction of Ru in a gamma matrix of the nickel-based powder superalloy is 0.30% -1.65%; and/or
When the nickel-based powder superalloy contains Os, the mass fraction of Os in a gamma matrix of the nickel-based powder superalloy is 0.24-2.1%.
Ru reduces the supersaturation degree of refractory elements in a gamma phase, can inhibit the precipitation of harmful phases such as TCP and the like, and improves the stability of an alloy microstructure. Meanwhile, Ru as an effective solid solution strengthening element plays a significant role in strengthening the gamma phase and the gamma' phase, and the creep resistance and the durability of the alloy are improved. Therefore, the addition of the element Ru with proper content in the powder superalloy can improve the structural stability of the alloy and simultaneously improve the high-temperature mechanical property of the alloy.
Os and Ru are both group VIII elements and are adjacent to group VIIB Re elements. The melting point and the atomic radius of the Os element are between Re and Ru, and the crystal structure of the Os element is the same as that of Re and Ru and is an HCP structure. Therefore, the strengthening effect of Os in the nickel-based superalloy is similar to that of Re and Ru. Meanwhile, the calculation of the first principle shows that the element Os has high strengthening effect. In the alloy as-cast structure, the segregation coefficient ks of the element is calculated by using the composition of dendrites and dendrite trunks as C dendrite interdendrites/C dendrite trunks, and as a result, Os segregates (positive segregation) between dendrites, and the segregation of Al, Ti, Nb, Ta, and Hf is greatly affected by Os, so that Al is transformed from segregation to dendrite trunks, and Ta is transformed from segregation to dendrite trunks, thereby aggravating the segregation of Ti and Nb to dendrites and weakening the segregation of Hf to dendrites.
In the alloy as-heat treated structure, Os exists mainly in the γ matrix and secondarily in the γ' phase, and Os does not exist in the MC type carbide; the Os increases the proportion of Co, Cr, Mo and W elements in the gamma matrix, reduces Nb elements and has little change of the proportion of other alloy elements. From this, it is understood that Os mainly plays a solid solution strengthening role.
Optionally, the nickel-based powder superalloy has a maximum operating temperature above 815 ℃.
According to another object of the present invention, there is provided a method for preparing any of the above nickel-based powder superalloys, the method comprising the steps of:
a) mixing and smelting the components according to the mass fraction ratio to obtain an alloy precursor;
b) carrying out powder preparation, screening and electrostatic treatment on the alloy precursor obtained in the step a) to obtain alloy powder;
c) carrying out vacuum degassing and sealing welding on the alloy powder obtained in the step b), and then carrying out hot isostatic pressing forming to obtain an ingot blank;
d) heat treating the ingot blank obtained in step c) to obtain the nickel-based powder superalloy.
Optionally, in the step a), the alloy precursor is obtained by a vacuum induction melting process.
Optionally, in the step b), the milling is performed by a plasma rotating electrode method; the grain size of the alloy powder is 50-150 mu m.
Optionally, in the step c), the hot isostatic pressing conditions are: the temperature is 1170-1230 ℃, the pressure is 120-140 MPa, and the heat preservation time is 2-4 h.
Optionally, in step d), the heat treatment comprises solution heat treatment and aging heat treatment.
Optionally, the conditions of the solution heat treatment are: 1190-1230 deg.c/2-10 hr/air cooling.
Optionally, the aging heat treatment comprises a multi-stage aging heat treatment, preferably a two-stage aging heat treatment; the aging heat treatment conditions are as follows: 860-940 ℃/2 h-6 h/air cooling + 740-780 ℃/12 h-22 h/air cooling.
As an embodiment, a method of making a nickel-based powder superalloy, the method comprising the steps of:
s1, preparing raw materials according to chemical components and mass fractions of powder high-temperature alloy, and preparing an alloy bar by adopting a vacuum induction melting process;
s2, preparing high-temperature alloy powder from the alloy bar by adopting a plasma rotating electrode method, and screening and carrying out electrostatic treatment on the alloy powder to obtain finished powder with the granularity of 50-150 mu m;
s3, filling the alloy powder into a low-carbon steel sheath, and performing vacuum degassing and seal welding;
s4, carrying out hot isostatic pressing forming on the sealed and welded alloy powder to obtain an ingot blank; specifically, the hot isostatic pressing conditions were: 1170-1230 ℃, the pressure of 120-140 MPa and the heat preservation time of 2-4 h;
and S5, carrying out heat treatment on the formed ingot blank to obtain a powder high-temperature alloy workpiece. The heat treatment comprises solution heat treatment and aging heat treatment; specifically, the solution heat treatment conditions were: 1190 ℃ to 1230 ℃/2h to 10 h/air cooling, the aging heat treatment comprises two-stage aging heat treatment, the aging heat treatment system is as follows: 860-940 ℃/2 h-6 h/air cooling + 740-780 ℃/12 h-22 h/air cooling.
According to a further object of the present invention, there is provided an aircraft device using any of the above nickel-based powder superalloys.
Optionally, the aerial device is an aircraft engine.
Optionally, the aerospace device is an aero-engine turbine disc.
Compared with the prior art, the invention has the beneficial effects that:
(1) the nickel-based powder superalloy provided by the invention has excellent comprehensive performance component composition and content, and the nickel-based powder superalloy is endowed with excellent high-temperature tensile strength, yield strength and high-temperature endurance and higher maximum working temperature.
(2) The nickel-based powder superalloy provided by the invention reduces the precipitation tendency of a Topologically Close Packed (TCP) phase by controlling the contents of Cr, Mo, W and Ru, realizes high-temperature tensile strength and yield strength and excellent high-temperature endurance strength of the alloy by adding solid solution strengthening elements (Co, Cr, Mo, W and Ru), gamma' phase forming elements (Al, Ti, Nb, Ta and Hf) and grain boundary strengthening elements (Zr and B), reduces the precipitation tendency of the TCP phase by coordinately controlling the contents of Co, Cr, Mo, W and Ta and the like, and improves the high-temperature structure stability of the alloy.
(3) The maximum working temperature of the nickel-based powder high-temperature alloy provided by the invention can reach over 815 ℃, can meet the rigorous requirement of an aeroengine on the material performance at high temperature, and can be used as an aeronautical high-temperature material in a temperature scene of over 815 ℃.
(4) The preparation method of the nickel-based powder superalloy provided by the invention is efficient and easy to implement, the reproducibility is good, and the microstructure of the prepared nickel-based powder superalloy is high in stability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a metallographic structure representation of the as-heat-treated microstructure of a nickel-based powder superalloy in accordance with an embodiment of the present invention;
FIG. 2 is a metallographic structure representation result of the nickel-based powder superalloy after being subjected to aging heat treatment at 815 ℃/3000h in one embodiment of the invention;
FIG. 3 is a metallographic structure representation result of a nickel-based powder superalloy after aging heat treatment at 850 ℃/500h in one embodiment of the invention.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but it will be understood by those skilled in the art that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products commercially available.
EXAMPLE 1 preparation of a Nickel-based powder superalloy
Preparation of 1 from the ingredients and their contents listed in Table 1#～5#Nickel-based powder superalloys.
TABLE 1 composition and preparation conditions of nickel-based powder superalloy samples
The preparation method specifically comprises the following steps:
s1, preparing raw materials according to chemical components and mass fractions of powder high-temperature alloy, and preparing an alloy bar by adopting a 25kg vacuum induction melting process;
s2, preparing high-temperature alloy powder from the alloy bar by adopting a plasma rotating electrode method, and screening and carrying out electrostatic treatment on the alloy powder to obtain finished powder with the granularity of 50-150 mu m;
s3, filling the alloy powder into a low-carbon steel sheath, and performing vacuum degassing and seal welding;
s4, carrying out hot isostatic pressing forming on the sealed and welded alloy powder to obtain an ingot blank;
s5, carrying out heat treatment on the formed ingot blank to obtain a powder high-temperature alloy workpiece; the heat treatment includes solution heat treatment and aging heat treatment.
Experimental example 1 metallographic structure characterization of nickel-based powder superalloy
The microstructure of the alloy obtained in example 1 was characterized by observing the microstructure of the alloy in the heat-treated state and after long-term ageing using an Olympus GM-7 metallographic microscope#～5#The metallographic structure of the nickel-based powder superalloy.
By 4#The nickel-based powder superalloy is typical, and the metallographic structure of the nickel-based powder superalloy in a heat treatment state is shown in a figure 1; 4#The metallographic structure of the nickel-based powder superalloy after 815 ℃/3000h aging and 850 ℃/500h aging is respectively shown in fig. 2 and fig. 3.
The microstructure of the nickel-based powder superalloy provided by the invention mainly comprises gamma, gamma ', MC and M3B2 phases, wherein the gamma' phase comprises (Ni, Co)3The composition of the (Al, Ti, Ta, Nb, Hf) type and MC type carbides is (Ti, Ta, Nb, Hf) C type.
1#The gamma 'phase content of the nickel-based powder superalloy is 60% (mass fraction), the complete dissolution temperature of the gamma' phase is 1200-1220 ℃, about 80% of Os enters a gamma matrix, and the mass fraction of Os in the gamma matrix is 0.32%.
2#The gamma 'phase content of the nickel-based powder superalloy is 60% (mass fraction), the complete dissolution temperature of the gamma' phase is 1200-1220 ℃, and about 78% of Os enters a gamma matrix, namely the mass fraction of Os in the gamma matrix is 1.4%.
3#The gamma 'phase content of the nickel-based powder superalloy is 60 percent (mass fraction), the complete dissolution temperature of the gamma' phase is 1180-1200 ℃, about 58 percent of Ru enters a gamma matrix, and the mass fraction of the Ru in the gamma matrix is 0.35 percent.
4#The gamma 'phase content of the nickel-based powder superalloy is 60% (mass fraction), the complete dissolution temperature of the gamma' phase is 1180-1200 ℃, about 55% of Ru enters a gamma matrix, and the mass fraction of the Ru in the gamma matrix is 1.24%.
As can be seen from FIGS. 2 and 3, the nickel-based powder superalloy has no TCP phase precipitation after being subjected to aging heat treatment at 815 ℃/3000h and 850 ℃/500h, and has excellent high-temperature structure stability at 815 ℃.
Experimental example 2 Performance characterization of Nickel-based powder superalloy
Test of 1 prepared in example 1 Using NCS GNT100 electronic tensile tester, GNCJ-30 mechanical high temperature creep rupture tester#～5#Mechanical properties of the nickel-based powder superalloy.
Wherein 1 is#～5#The room temperature tensile property, 760 ℃ tensile property, 815 ℃ tensile property and 815 ℃/450MPa durability of the nickel-based powder superalloy are shown in tables 2, 3, 4 and 5, respectively.
TABLE 2 room temperature tensile properties of nickel-based powder superalloys
| Alloy number | σb/MPa | σ0.2/MPa | δ/％ | ψ/％ |
| 1# | 1570 | 1210 | 11.0 | 12.5 |
| 2# | 1605 | 1240 | 10.0 | 11.5 |
| 3# | 1565 | 1205 | 11.5 | 12.5 |
| 4# | 1583 | 1225 | 11.0 | 12.0 |
| 5# | 1620 | 1260 | 9.0 | 10.5 |
TABLE 3 tensile properties at 760 ℃ of nickel-based powder superalloys
| Alloy number | σb/MPa | σ0.2/MPa | δ/％ | ψ/％ |
| 1# | 1345 | 1145 | 8.0 | 9.5 |
| 2# | 1390 | 1190 | 7.0 | 8.5 |
| 3# | 1335 | 1135 | 8.0 | 8.5 |
| 4# | 1370 | 1180 | 7.5 | 8.0 |
| 5# | 1420 | 1220 | 6.5 | 8.0 |
TABLE 4 tensile properties at 815 ℃ of nickel-based powder superalloys
| Alloy number | σb/MPa | σ0.2/MPa | δ/％ | ψ/％ |
| 1# | 1125 | 960 | 6.5 | 8.5 |
| 2# | 1170 | 1020 | 6.0 | 7.5 |
| 3# | 1120 | 950 | 6.5 | 9.0 |
| 4# | 1150 | 995 | 6.5 | 8.5 |
| 5# | 1190 | 1040 | 5.5 | 7.0 |
TABLE 5 815 ℃/450MPa permanence of nickel-based powder superalloys
| Alloy number | Permanent life tau/h | Permanent plasticity δ/%) |
| 1# | 550 | 6.1 |
| 2# | 720 | 5.0 |
| 3# | 540 | 6.2 |
| 4# | 685 | 5.9 |
| 5# | 850 | 5.5 |
The existing powder superalloy ME501[ A.Powell, K.Bain, A.Wessman, et al.Advance dsupersolvus nickel powder alloy DOE: chemistry, properties, phaseformations and thermal stability [ C ]. Superalloy 2016: 189-; D.P. Mourer, K.R. Bain.Nickel-based alloy, processing theror and components for the purpose of their of US 8613810[ P ].2013-12-24], wherein the tensile strength and yield strength at 760 ℃ are 1186MPa and 1041MPa respectively, the tensile strength and yield strength at 815 ℃ are 993MPa and 903MPa respectively, and the endurance life at 815 ℃/345MPa is 532 h.
As can be seen from the data in tables 3 and 4, compared with the conventional powder superalloy ME501, the tensile strength and yield strength of the nickel-based powder superalloy provided by the invention are greatly improved at 760 ℃ and 810 ℃; as can be seen from the data in Table 5, the present invention provides 1#、2#The lasting strength of the nickel-based powder superalloy at 815 ℃ is more than 1.35 times that of the ME501 alloy, and 3#、4#、5#The endurance strength of the nickel-based powder superalloy at 815 ℃ is more than 1.29 times that of the ME501 alloy. Therefore, the nickel-based powder superalloy provided by the invention has excellent mechanical properties.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (7)
1. Nickel-base powder superalloy characterized in that its composition comprises, in mass fractions:
0.058% of C, 16.1% of Co, 9.8% of Cr, 2.58% of Mo, 5.11% of W, 5.05% of Ta, 3.21% of Al, 3.04% of Ti3, 2.02% of Nb0.31% of Hf0.028% of B, 0.03% of Os1.1% of Ru, and the balance of Ni;
the preparation method of the nickel-based powder superalloy comprises the following steps:
a) mixing and smelting the components according to the mass fraction ratio to obtain an alloy precursor;
b) carrying out powder preparation, screening and electrostatic treatment on the alloy precursor obtained in the step a) to obtain alloy powder;
c) carrying out vacuum degassing and sealing welding on the alloy powder obtained in the step b), and then carrying out hot isostatic pressing forming to obtain an ingot blank;
d) heat-treating the ingot blank obtained in step c) to obtain the nickel-based powder superalloy;
in step c), the hot isostatic pressing conditions are: the temperature is 1210-1230 ℃, the pressure is 120-140 MPa, and the heat preservation time is 2-4 h;
in said step d), said heat treatment comprises solution heat treatment and aging heat treatment;
the conditions of the solution heat treatment are as follows: air cooling at 1210-1230 ℃/5-10 h;
the aging heat treatment is two-stage aging heat treatment; the aging heat treatment conditions are as follows: 860-940 ℃/2 h-6 h/air cooling + 740-780 ℃/12 h-22 h/air cooling.
2. The nickel-base powder superalloy according to claim 1, wherein the major precipitation phases of the nickel-base powder superalloy comprise gamma-matrix, gamma' -phase, MC, and M3B2Phase (1);
according to the mass fraction, the content of the gamma 'phase in the nickel-based powder superalloy is 55-65%, and the complete dissolution temperature of the gamma' phase is 1180-1220 ℃.
3. The nickel-base powder superalloy according to claim 2, wherein the content of the gamma prime phase in the nickel-base powder superalloy is 60%, and the complete dissolution temperature of the gamma prime phase is 1200 ℃ to 1220 ℃.
4. The nickel-base powder superalloy according to claim 1, wherein the maximum operating temperature of the nickel-base powder superalloy is 815 ℃ or higher.
5. The nickel-base powder superalloy according to claim 1, wherein in step a), the alloy precursor is obtained using a vacuum induction melting process;
in the step b), the powder preparation is carried out by adopting a plasma rotating electrode method; the grain size of the alloy powder is 50-150 mu m.
6. Aerospace apparatus using the nickel-based powder superalloy according to any of claims 1 to 5.
7. The aerial device of claim 6, wherein the aerial device is an aircraft engine.
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| CN115927917A (en) * | 2022-12-21 | 2023-04-07 | 东方电气集团东方汽轮机有限公司 | high-W, mo-content nickel-based superalloy powder and application thereof, repairing agent and preparation thereof, and alloy repairing method |
| CN115679157B (en) * | 2022-12-29 | 2023-03-28 | 北京钢研高纳科技股份有限公司 | Nickel-based high-temperature alloy, preparation method thereof and structural member |
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