Nickel-based superalloy, method for preparing same, and structural member

Abstract

The present disclosure relates to the technical field of nickel-based high temperature alloys, in particular to nickel-based high temperature alloys, their preparation methods and structural members. The alloy has a composition containing, by mass fraction, Co: 17%-22%, Cr: 9%-13%, Ta: 2.95%-3.95%, Al: 2.5%-3.5%, Ti: 2.5%-3.5%, W: 2.1%-3.5%, Mo: 2.1%-3.5%, Nb: 1.65%-1.95%, Hf: 0.2%-0.7%, C: 0.03%-0.08%, B: 0.01%-0.06%, Zr: 0.03%-0.07%, and the balance: Ni. The nickel-based high temperature alloy according to the present disclosure improves creep resistance by generating a specific Suzuki atmosphere at a specific position during creep at 780°C and pinning dislocations. Therefore, the operating temperature can be increased to above 780°C, satisfying the requirements for materials in advanced aeroengines.

Description

Technical Field

[0001] The present disclosure relates to the technical field of nickel-based superalloys, and particularly to nickel-based superalloys, their preparation methods, and structural members.

[0002] (Cross-reference to Related Applications) The present disclosure claims priority based on a Chinese application with an application number of 202211701504.7 and a title of "Nickel-based Superalloy, Its Preparation Method, and Structural Member" filed with the Chinese Patent Office on December 29, 2022, and all of its contents are incorporated herein by reference.

Background Art

[0003] Superalloys are widely used in important components of the hot end in aircraft, engines for spacecraft, ships, and industrial gas turbines because of their excellent performance in high-temperature environments. In current aircraft engines, their usage accounts for 40% - 60% of the engine mass. The pre-turbine temperature refers to the temperature of the high-temperature and high-pressure gas after combustion before it enters the turbine, and it is an important indicator indicating the performance of the engine. The larger this temperature value is, the higher the internal energy of the gas before the turbine is, and the greater the work done by the gas passing through the turbine at the same flow rate, which means it is an engine with good performance. Increasing the pre-turbine temperature is an important technical means to improve the thrust of the engine, but it poses strict requirements on the performance of the material. Under high temperature and high stress, the movement of dislocations in the alloy becomes easy, and failure forms such as deformation and cracking of the alloy occur. The superalloys in related technologies have insufficient use temperatures and cannot meet the requirements for materials in advanced aircraft engines (above 780°C). In view of the above circumstances, the present disclosure is submitted.

Summary of the Invention

Problems to be Solved by the Invention

[0004] The present disclosure provides a nickel-based superalloy that solves the technical problems in the related art where at least the service temperature of the alloy cannot meet the requirements of advanced aeroengines. The present disclosure also provides a method for preparing a nickel-based superalloy. The present disclosure further provides a structural member prepared using the nickel-based superalloy.

Means for Solving the Problems

[0005] An embodiment of the present disclosure provides a nickel-based superalloy having a composition containing, by mass fraction, Co: 17% - 22%, Cr: 9% - 13%, Ta: 2.95% - 3.95%, Al: 2.5% - 3.5%, Ti: 2.5% - 3.5%, W: 2.1% - 3.5%, Mo: 2.1% - 3.5%, Nb: 1.65% - 1.95%, Hf: 0.2% - 0.7%, C: 0.03% - 0.08%, B: 0.01% - 0.06%, Zr: 0.03% - 0.07%, and the balance: Ni, and the total mass fraction of Nb and W being 3.75% - 5.2%. In any embodiment of the present disclosure, the nickel-based superalloy may have a total mass fraction of Nb and W of 4.1% - 5.1%. In any embodiment of the present disclosure, the nickel-based superalloy may have a total mass fraction of Ti, Nb, and Ta of 7.8% - 9.3%. In any embodiment of the present disclosure, the nickel-based superalloy may satisfy (Ti + Al) / (Nb + Ta) = 1.1 - 1.3 for the mass fractions of Ti, Al, Nb, and Ta. In any embodiment of the present disclosure, the nickel-based superalloy may satisfy Cr / (Co + Ni) = 0.14 - 0.18 for the mass fractions of Cr, Co, and Ni. In any embodiment of the present disclosure, the nickel-based superalloy may further contain Mg and / or Ce. Furthermore, the content of Mg may be greater than 0 and not more than 0.01%, and the content of Ce may be greater than 0 and not more than 0.01%. In any embodiment of the present disclosure, the nickel-based superalloy may have a Suzuki atmosphere containing Cr and Co in the fine twins due to creep deformation and a Suzuki atmosphere containing Ta, Nb, W, and Ti in the superlattice stacking faults due to creep deformation during the creep process at 780 °C.

[0006] Embodiments of the present disclosure further provide a preparation method for preparing any of the above nickel-based superalloys. This preparation method includes the steps of preparing a bar by a vacuum induction melting method, producing alloy powder from the bar by a vacuum inert gas atomization method, performing a hot isostatic pressing treatment on the alloy powder to obtain a blank, and performing hot extrusion, forging, and heat treatment on the blank. In any embodiment of the present disclosure, the hot isostatic pressing treatment is performed at a temperature of 1120 - 1130 °C, a pressure of 140 - 150 MPa, and a time of 4 - 10 hours. In any embodiment of the present disclosure, the hot extrusion is performed at a temperature of 1120 - 1130 °C, an extrusion ratio of (5.5 - 6.5):1, and an extrusion speed of 18 - 22 mm / s. In any embodiment of the present disclosure, the forging is isothermal forging, and the isothermal forging is performed at a temperature of 1120 - 1130 °C and a reduction rate of 0.8 - 1.2 mm / s.

[0007] Embodiments of the present disclosure further provide a structural member, which is mainly manufactured from any of the above nickel-based superalloys. In any embodiment of the present disclosure, the structural member includes a turbine disk.

Advantages of the Invention

[0008] Compared with the related art, the present disclosure has at least the following beneficial effects. (1) In the nickel-based superalloy according to the present disclosure, Nb, W, Ti, and Ta are used to synergistically strengthen the γ' phase, generate a Suzuki atmosphere of specific elements in the fine twins and superlattice stacking faults, and pin the dislocations to improve the creep resistance. (2) The service temperature of the nickel-based superalloy according to the present disclosure can be increased to 780 - 830 °C, which can meet the requirements for materials of advanced aero-engines.

[0009] To more clearly explain the specific embodiments or technical solutions of the related art in the present disclosure, the following briefly describes the drawings necessary for the description of the specific embodiments or related art. The drawings to be described are only part of the embodiments of the present disclosure. Those skilled in the art can obtain other drawings based on these drawings without using inventive capabilities.

Brief Description of the Drawings

[0010]

Figure 1

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Modes for Carrying Out the Invention

[0011] The technical solution of the present disclosure will be clearly and completely described below with reference to the drawings and specific embodiments. The embodiments described below are only some of the embodiments for explaining the present disclosure, not all of them, and should not be regarded as limiting the scope of the present disclosure. Based on the embodiments of the present disclosure, all other embodiments obtained by those skilled in the art without using inventive ability also belong to the protection scope of the present disclosure. In the embodiments, for the conditions not specified specifically, it is possible to carry out under conventional conditions or the conditions recommended by the manufacturer. For reagents or instruments not specified by the manufacturer, commercially available conventional products can be used.

[0012] The nickel-based superalloy according to the embodiment of the present disclosure has a composition containing, by mass fraction, Co: 17% - 22%, Cr: 9% - 13%, Ta: 2.95% - 3.95%, Al: 2.5% - 3.5%, Ti: 2.5% - 3.5%, W: 2.1% - 3.5%, Mo: 2.1% - 3.5%, Nb: 1.65% - 1.95%, Hf: 0.2% - 0.7%, C: 0.03% - 0.08%, B: 0.01% - 0.06%, Zr: 0.03% - 0.07%, and the balance: Ni, and the total mass fraction of Nb and W is 3.75% - 5.25%.

[0013] Since the creep of the superalloy is mainly caused by fine twins and dislocation climb, suppressing twins and sliding dislocations are the basic mechanisms of the present disclosure. The nickel-based superalloy according to the present disclosure has excellent creep resistance characteristics, and the service temperature is 780 °C or higher. Nb, W, Ti, and Ta can synergistically strengthen the γ' phase. As the main strengthening method, specific Nb, W, Ti, Ta, Cr, and Co are used to generate the Suzuki atmosphere of specific elements in fine twins and superlattice stacking faults, and the creep resistance characteristics are improved by pinning dislocations.

[0014] Here, since W has a high diffusion coefficient, it is very stable at high temperatures when it is unevenly distributed in stacking faults. Nb can promote the uneven distribution of W in the hexagonal stacking faults. The total mass fraction of Nb and W is adjusted to be 3.75% - 5.25% to ensure the stability of the Suzuki uneven distribution in the superlattice stacking faults.

[0015] In addition, the total mass fraction of Ti, Nb, and Ta is adjusted to be 7.8% to 9.3% so that the Al sublattice and Ti sublattice of the γ' phase are replaced by Ta and Nb. The alloys obtained within the composition range of the nickel-based superalloy according to the present disclosure generate a Suzuki atmosphere in which different elements are unevenly distributed at different positions. During the creep process at 780 °C or higher, a fine twin and a stable Cr, Co-rich Suzuki atmosphere are obtained, and a stable Ta, Nb, W, Ti-rich Suzuki atmosphere is obtained at the superlattice stacking fault. The alloy composition within the above content range is required for the strengthening method of pinning dislocations by the Suzuki effect. If the total mass fraction of Nb and W exceeds a predetermined range, a massive μ phase precipitates in the matrix, and if it is below the predetermined range, W cannot be effectively dragged to the stacking fault. If the total mass fraction of Ti, Nb, and Ta is below a predetermined range, a stable Suzuki effect cannot be obtained during the creep process at 780 °C or higher, and if it exceeds the predetermined range, a massive η phase precipitates in the matrix.

[0016] For example, in different embodiments, the content of each element in the nickel-based superalloy can be as follows in terms of mass fraction. The content of Co can be 17%, 17.5%, 18%, 18.5%, 19%, 19.5%, 20%, 20.5%, 21%, 21.5%, 22%, etc. The content of Cr can be 9%, 9.5%, 10%, 10.5%, 11%, 11.5%, 12%, 12.5%, 13%, etc. The content of Ta can be 2.95%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, 3.6%, 3.7%, 3.8%, 3.9%, 3.95%, etc. The content of Al can be 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc. The content of Ti can be 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc. The content of W can be 2.1%, 2.2%, 2.3%, 2.4%, 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc. The content of Mo can be 2.1%, 2.2%, 2.3%, 2.4%, 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc. The content of Nb can be 1.65%, 1.7%, 1.75%, 1.8%, 1.85%, 1.9%, 1.95%, etc. The content of Hf can be 0.2%, 0.3%, 0.4%, 0.5%, 0.6%, 0.7%, etc. The content of C can be 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, etc. The content of B can be 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, etc. The content of Zr can be 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, etc.

[0017] The content of each of the above elements is merely illustrative and not limited thereto, and the content within other predetermined ranges can also be used. In any embodiment of the present disclosure, the nickel-based superalloy may have a total mass fraction of Nb and W of 4.1% to 5.1%. For example, in different embodiments, the nickel-based superalloy may have a total mass fraction of Nb and W of 4.1%, 4.2%, 4.3%, 4.4%, 4.5%, 4.6%, 4.7%, 4.8%, 4.9%, 5%, 5.1%, etc. By limiting the total mass fraction of Nb and W within the above range, it is possible to avoid the precipitation of massive μ-phase in the matrix while effectively dragging W to the stacking defects. As a result, in combination with other components, a Ta, Nb, W, Ti-rich Suzuki atmosphere stabilized by superlattice stacking defects can be obtained under high-temperature conditions.

[0018] In any embodiment of the present disclosure, the nickel-based superalloy may have a total mass fraction of Ti, Nb, and Ta of 7.8% to 9.3%, preferably 7.9% to 9%. For example, in different embodiments, the nickel-based superalloy may have a total mass fraction of Ti, Nb, and Ta of 7.8%, 7.9%, 8%, 8.1%, 8.2%, 8.3%, 8.4%, 8.5%, 8.6%, 8.7%, 8.8%, 8.9%, 9%, 9.1%, 9.2%, 9.3%, etc. By limiting the total mass fraction of Ti, Nb, and Ta within the above range, while avoiding the precipitation of massive η-phase in the matrix, the Al sublattice and Ti sublattice in the γ'-phase can be substituted with Ta and Nb in a good ratio. As a result, when combined with other components, a Ta, Nb, W, Ti-rich Suzuki atmosphere stable with superlattice stacking faults can be obtained under high-temperature conditions.

[0019] In any embodiment of the present disclosure, the nickel-based superalloy may have a mass fraction of Ti, Al, Nb, and Ta such that (Ti + Al) / (Nb + Ta) = 1.1 to 1.3. For example, in different embodiments, the nickel-based superalloy may have (Ti + Al) / (Nb + Ta) of 1.1, 1.12, 1.15, 1.18, 1.2, 1.22, 1.25, 1.28, 1.3, etc. By adjusting the mass fraction of Ti, Al, Nb, and Ta within the above range, the Al sublattice and Ti sublattice in the γ'-phase are substituted with Ta and Nb in an optimal ratio, ensuring the stability of the formed Suzuki atmosphere.

[0020] In any embodiment of the present disclosure, the nickel-based superalloy may have a mass fraction of Cr, Co, and Ni such that Cr / (Co + Ni) = 0.14 to 0.18. For example, in different embodiments, the nickel-based superalloy may have Cr / (Co + Ni) of 0.14, 0.145, 0.15, 0.155, 0.16, 0.165, 0.17, 0.175, 0.18, etc. By adjusting the mass fractions of Cr, Co, and Ni within the above ranges, Cr and Co are unevenly distributed in the twin crystals.

[0021] In any embodiment of the present disclosure, the nickel-based superalloy may further contain Mg and / or Ce. Further, the content of Mg is greater than 0 and not more than 0.01%, and the content of Ce may be greater than 0 and not more than 0.01%. For example, the content of Mg may be 0.0005% - 0.01%, and the content of Ce may be 0.0005% - 0.01%.

[0022] In any embodiment of the present disclosure, the nickel-based superalloy may have a composition containing, by mass fraction, Co: 17% - 22%, Cr: 9% - 13%, Ta: 2.95% - 3.95%, Al: 2.5% - 3.5%, Ti: 2.5% - 3.5%, W: 2.1% - 3.5%, Mo: 2.1% - 3.5%, Nb: 1.65% - 1.95%, Hf: 0.2% - 0.7%, C: 0.03% - 0.08%, B: 0.01% - 0.06%, Zr: 0.03% - 0.07%, Mg: 0 - 0.01%, Ce: 0 - 0.01%, and the balance: Ni. In any embodiment of the present disclosure, the nickel-based superalloy may have a composition containing, by mass fraction, Co: 18% - 21%, Cr: 9% - 13%, Ta: 2.95% - 3.9%, Al: 2.8% - 3.5%, Ti: 3.0% - 3.5%, W: 2.1% - 3.5%, Mo: 2.1% - 3.5%, Nb: 1.65% - 1.85%, Hf: 0.2% - 0.5%, C: 0.03% - 0.08%, B: 0.01% - 0.06%, Zr: 0.03% - 0.07%, Mg: 0 - 0.01%, Ce: 0 - 0.01%, and the balance: Ni.

[0023] In any embodiment of the present disclosure, the nickel-based superalloy has a Suzuki atmosphere containing Cr and Co in the fine twins due to creep deformation and a Suzuki atmosphere containing Ta, Nb, W, and Ti in the superlattice stacking faults due to creep deformation during the creep process at 780°C. In any embodiment of the present disclosure, in the creep process at 780 °C, the deformed laminated defects in the structure are mainly inside the strengthening phase.

[0024] The present disclosure further provides a preparation method for any of the above nickel-based superalloys. This preparation method includes the steps of preparing a bar by a vacuum induction melting method, producing alloy powder from the bar by a vacuum inert gas atomization method, performing a hot isostatic pressing treatment on the alloy powder to obtain a blank, and performing hot extrusion, forging, and heat treatment on the blank.

[0025] In any embodiment of the present disclosure, the hot isostatic pressing treatment is carried out at a temperature of 1120 - 1130 °C, a pressure of 140 - 150 MPa, and a time of 4 - 10 hours. In any embodiment of the present disclosure, the hot extrusion is carried out at a temperature of 1120 - 1130 °C, an extrusion ratio of (5.5 - 6.5):1, and an extrusion speed of 18 - 22 mm / s. In any embodiment of the present disclosure, the forging is isothermal forging, and the isothermal forging is carried out at a temperature of 1120 - 1130 °C and a reduction rate of 0.8 - 1.2 mm / s. In actual operation, the heat treatment includes solution treatment and aging treatment. Further, the solution treatment is carried out by heating at 1180 °C for 3 hours and then oil quenching at an oil temperature of 150 °C. The aging treatment is carried out by heating at 760 °C for 16 hours. For the heat treatment of the duplex structure (a structure having two grain sizes), the heat treatment of the normal duplex structure is used so that the grain size of the rim is 5 - 6 grades and the grain size of the hub is 10 - 12 grades.

[0026] The present disclosure further provides a structural member, which is mainly manufactured by any of the above nickel-based superalloys. In any embodiment of the present disclosure, the structural member includes a turbine disk. The use temperature of the nickel-based superalloy according to the present disclosure can be increased to 780 - 830 °C, and the requirements for materials of advanced aero-engines can be satisfied.

[0027] Examples 1 - 10 In Examples 1 - 10, Nos. 1# - 10# of nickel - based superalloys and their preparation methods were provided respectively. The measured component values of the nickel - based superalloys are shown in Table 1.

[0028] The preparation method of the nickel - based superalloy includes the following steps. (1) Prepare a φ70mm bar by vacuum induction melting method, and prepare superalloy powder from the φ70mm bar prepared by vacuum induction melting method by vacuum inert gas atomization method (VIGA). (2) Screen powders with a particle size of 53μm or less, put them into a stainless - steel sheath. Degas and seal the sheath. Perform hot isostatic pressing (HIP) on the sealed sheath. The hot isostatic pressing process has a temperature of 1120°C, a pressure of 140 MPa, and a time of 4 hours. (3) Perform hot extrusion on the material after hot isostatic pressing in a heating furnace. The hot extrusion has a temperature of 1120°C, an extrusion ratio of 6:1, and an extrusion speed of 20 mm / s. (4) Cut the bar formed by hot extrusion to obtain a bar with a length of 400 mm, and further create a disk with a diameter of 600 mm by isothermal forging. The forging temperature is 1120°C and the reduction rate is 1 mm / s. (5) Perform solution treatment, oil quenching and aging treatment on the disk material. After solution treatment at 1180°C for 3 hours, oil quenching is carried out at an oil temperature of 150°C. Aging treatment is carried out at 760°C for 16 hours.

[0029] [Table 1]

[0030] Comparative Examples 1 - 5 In Comparative Examples 1 - 5, Comparative Examples 1# - 5# of nickel - based superalloys were provided respectively. Their preparation methods are the same as those of Example 1 except for the composition of the nickel - based superalloy. The measured component values of the nickel - based superalloys in Comparative Examples 1 - 5 are shown in Table 2.

[0031] [Table 2]

[0032] Comparative Examples 6 - 10 Comparative Examples 6 - 10 are the conventional alloys Rene95, EP741NP, Rene88DT, ME3, and ME501, respectively.

[0033] Experimental Example 1 To compare the differences between the nickel - based superalloys of the examples and comparative examples, the microstructures of the nickel - based superalloys according to the examples and comparative examples are shown. Figure 1 is a micrograph of the structure of nickel - based superalloy 1# after long - term rupture according to Example 1 of the present disclosure. Figure 2 is a micrograph of the structure of nickel - based superalloy Comparative Example 1# after long - term rupture according to Comparative Example 1. Taking Example 1 as an example, the deformed stacking defects in the structure are mainly inside the strengthening phase, while the deformed stacking defects in Comparative Example 1 penetrate through the strengthening phase and expand.

[0034] Figure 3 is a diagram showing the deformed superlattice stacking defects of nickel - based superalloy 1# after long - term rupture according to Example 1 of the present disclosure and the detection results of the chemical composition near the stacking defects. Figure 4 is a diagram showing the deformed fine twins of nickel - based superalloy 1# after long - term rupture according to Example 1 of the present disclosure and the detection results of the chemical composition near the fine twins. Figure 5 is a diagram showing the deformed superlattice stacking defects of nickel - based superalloy Comparative Example 1# after long - term rupture according to Comparative Example 1 and the detection results of the chemical composition near the stacking defects. As can be seen from the figures, for nickel - based superalloy 1# according to Example 1 of the present disclosure, after long - term rupture, there are Co, Nb, Ta, W - rich Suzuki segregation in the superlattice stacking defects, the Suzuki atmosphere of Co, W, Ta, Nb exists, there are Co, Cr - rich Suzuki segregation in the fine twins, and the Suzuki atmosphere of Co, Cr exists. On the other hand, for nickel - based superalloy Comparative Example 1# according to Comparative Example 1, after long - term rupture, there is no segregation of elements in the stacking defects. Due to the effect of Suzuki segregation in the examples of the present disclosure, dislocations and stacking defects are dragged, making deformation difficult to proceed and improving the creep strength. When detecting the chemical composition near the deformed laminated defects after long-term rupture of the nickel-based superalloy according to other embodiments, the results are almost the same as those in Example 1. When detecting the chemical composition near the deformed laminated defects after long-term rupture of the nickel-based superalloy according to other comparative examples, there is no segregation of elements in the laminated defects as well.

[0035] Experimental Example 2 In accordance with GB / T2039-2012, the high-temperature lifetimes of the 1#-10# nickel-based superalloys prepared in Examples 1-10 and each alloy of Comparative Examples 1-10 were measured, and the measurement results are shown in Table 3.

[0036]

Table 3

[0037] As can be seen from the above measurement results, in the present disclosure, by adjusting the contents of Nb, W, Ti, Ta, Cr, Co, etc. within a predetermined range, the alloy strengthening method is changed, a Suzuki atmosphere of specific elements is generated in the fine twins and superlattice laminated defects, and the dislocations are pinned to improve the creep resistance. Therefore, the use temperature of the alloy can be raised to 780 °C or higher.

[0038] Finally, it should be noted that each of the above embodiments is only for explaining the technical solutions of the present disclosure and is not intended to limit them. Despite the detailed description of the present disclosure with reference to each of the above embodiments, those skilled in the art may modify the technical solutions described in each of the above embodiments, or may equally replace some or all of the technical features therein. These modifications or replacements do not deviate from the essence of the corresponding technical solutions from the scope of the technical solutions of each embodiment of the present disclosure.

Industrial Applicability

[0039] Embodiments of the present disclosure provide a nickel-based superalloy, a preparation method thereof, and a structural member. The nickel-based superalloy according to the present disclosure synergistically strengthens the γ' phase by using Nb, W, Ti, and Ta, generates a Suzuki atmosphere of specific elements in fine twins and superlattice stacking faults, and pins dislocations to improve the creep resistance. The service temperature of the nickel-based superalloy according to the present disclosure can be raised to 780-830 °C, which can meet the requirements for materials of advanced aeroengines.

[0040] It should be noted that the nickel-based superalloy, the preparation method thereof, and the structural member according to the embodiments of the present disclosure are reproducible and applicable to various industrial applications. For example, the nickel-based superalloy, the preparation method thereof, and the structural member according to the embodiments of the present disclosure can be applied to the technical field related to nickel-based superalloys.

Claims

1. In terms of mass fraction, Co: 17% - 22%, Cr: 9% - 13%, Ta: 2.95% - 3.95%, Al: 2.5% - 3.5%, Ti: 2.5% - 3.5%, W: 2.1% - 3.5%, Mo: 2.1% - 3.5%, Nb: 1.65% - 1.95%, Hf: 0.2% - 0.7%, C: 0.03% - 0.08%, B: 0.01% - 0.06%, Zr: 0.03% - 0.07%, Mg: more than 0 and 0.01% or less, Ce: more than 0 and 0.01% or less, and has a composition of the balance: Ni and inevitable impurities, and the total mass fraction of Nb and W is 3.75% - 5.25%, the mass fractions of Cr, Co, and Ni satisfy Cr / (Co + Ni) = 0.14 - 0.18, in the creep process at 780°C, it has a Suzuki atmosphere containing Cr and Co in the fine twins due to creep deformation, and a Suzuki atmosphere containing Ta, Nb, W, and Ti in the superlattice stacking faults due to creep deformation A nickel-based superalloy.

2. The nickel-based superalloy according to Claim 1, wherein the total mass fraction of Nb and W is 4.1% - 5.1%.

3. The nickel-based superalloy according to Claim 1, wherein the total mass fraction of Ti, Nb, and Ta is 7.8% - 9.3%.

4. The nickel-based superalloy according to Claim 1, wherein the mass fractions of Ti, Al, Nb, and Ta satisfy (Ti + Al) / (Nb + Ta) = 1.1 - 1.

3.

5. A preparation method for preparing the nickel-based superalloy according to any one of Claims 1 to 4, comprising the step of preparing a bar by vacuum induction melting, the step of producing alloy powder from the bar by vacuum inert gas atomization, the step of obtaining a material by performing hot isostatic pressing on the alloy powder, and the step of performing hot extrusion, forging, and heat treatment on the material. A preparation method.

6. A turbine disk manufactured from the nickel-based superalloy according to any one of Claims 1 to 4.

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