Nickel-based high temperature alloy, its preparation method and structural component

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 field of nickel-based high temperature alloys, and in particular to nickel-based high temperature alloys, their preparation methods and structural components.

[0002] (CROSS REFERENCE TO RELATED APPLICATIONS) This disclosure claims priority to a Chinese application bearing application number 202211701504.7 and entitled "Nickel-based high temperature alloy, its preparation method and structural member," filed with the China Patent Office on December 29, 2022, the entire contents of which are incorporated herein by reference. [Background technology]

[0003] High temperature alloys, which have excellent performance in high temperature environments, are widely used in critical hot-end components of aircraft, spacecraft engines, marine and industrial gas turbines; in current aircraft engines, their usage accounts for 40% to 60% of the engine mass. The pre-turbine temperature refers to the temperature before the high-temperature, high-pressure gas after combustion enters the turbine, and is an important indicator of engine performance. The higher this temperature is, the higher the internal energy of the pre-turbine gas is, and the greater the work done by the gas passing through the turbine at the same flow rate is, which means the better the engine's performance. Increasing the pre-turbine temperature is an important technical means of improving the thrust of the engine, but it imposes strict requirements on the performance of the material. Under high temperatures and high stress, the movement of dislocations in the alloy becomes easier, causing deformation and cracking of the alloy. The high-temperature alloys of related technology have insufficient operating temperatures and cannot meet the requirements for advanced aeroengine materials (780°C or higher). In view of the above, the present disclosure is submitted. Summary of the Invention [Problem to be solved by the invention]

[0004] The present disclosure provides a nickel-base high temperature alloy that overcomes technical problems in the related art, at least in which the service temperatures of the alloy cannot meet the requirements of advanced aero engines. The present disclosure also provides a method for preparing a nickel-base high temperature alloy. The present disclosure further provides a structural component prepared using the nickel-base high temperature alloy. [Means for solving the problem]

[0005] An embodiment of the present disclosure provides a nickel-base high temperature alloy having a composition containing, by mass fraction, 17%-22% Co, 9%-13% Cr, 2.95%-3.95% Ta, 2.5%-3.5% Al, 2.5%-3.5% Ti, 2.1%-3.5% W, 2.1%-3.5% Mo, 1.65%-1.95% Nb, 0.2%-0.7% Hf, 0.03%-0.08% C, 0.01%-0.06% B, 0.03%-0.07% Zr, and the balance: Ni, where the sum of the mass fractions of Nb and W is 3.75%-5.2%. In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a total mass fraction of Nb and W of 4.1% to 5.1%. In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a total mass fraction of Ti, Nb, and Ta of 7.8% to 9.3%. In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a mass fraction of Ti, Al, Nb, and Ta that satisfies (Ti+Al) / (Nb+Ta)=1.1 to 1.3. In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a mass fraction of Cr, Co, and Ni that satisfies Cr / (Co+Ni)=0.14 to 0.18. In any embodiment of the present disclosure, the nickel-base high temperature alloy may further include Mg and / or Ce, and the Mg content may be greater than 0 and less than or equal to 0.01%, and the Ce content may be greater than 0 and less than or equal to 0.01%. In any embodiment of the present disclosure, the nickel-base high temperature alloy 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 stacking faults of the superlattice due to creep deformation during creep at 780°C.

[0006] An embodiment of the present disclosure further provides a method for preparing any of the above nickel-base high temperature alloys, the method including the steps of preparing a bar by vacuum induction melting, producing alloy powder from the bar by vacuum inert gas atomization, subjecting the alloy powder to hot isostatic pressing to obtain a blank, and subjecting the blank to hot extrusion, forging and heat treatment. 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 has 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 has a temperature of 1120 to 1130° C. and a reduction rate of 0.8 to 1.2 mm / s.

[0007] An embodiment of the present disclosure further provides a structural member, the structural member being fabricated essentially from any of the nickel-base high temperature alloys described above. In any embodiment of the present disclosure, the structural member includes a turbine disk. Effect of the Invention

[0008] Compared with the related art, the present disclosure has at least the following beneficial effects: (1) In the nickel-base high temperature alloy of the present disclosure, Nb, W, Ti, and Ta are utilized to synergistically strengthen the γ′ phase, generate Suzuki atmospheres of specific elements in the fine twins and stacking faults of the superlattice, and pin dislocations, thereby improving creep resistance. (2) The operating temperature of the nickel-base high temperature alloy according to the present disclosure can be increased to 780-830°C, thereby satisfying the requirements for advanced aeroengine materials.

[0009] In order to more clearly describe the technical solutions of specific embodiments or related technologies in the present disclosure, the drawings necessary for describing the specific embodiments or related technologies are briefly described below. The drawings described are only some embodiments of the present disclosure. Those skilled in the art can obtain other drawings based on these drawings without using inventive abilities. [Brief description of the drawings]

[0010] [Figure 1] 1 is a microstructure photograph of nickel-based high temperature alloy 1# according to Example 1 of the present disclosure after long-term fracture. [Diagram 2] 1 is a microstructure photograph of the nickel-based high temperature alloy Comparative Example 1# after long-term fracture according to Comparative Example 1. [Diagram 3] FIG. 1 shows the stacking fault diagram of the deformed superlattice after long-term fracture of the nickel-based high temperature alloy 1# according to Example 1 of the present disclosure and the detection results of the chemical composition in the vicinity of the stacking fault. [Figure 4] FIG. 1 shows the diagram of deformed microtwin crystals after long-term fracture of nickel-based high temperature alloy 1# according to Example 1 of the present disclosure and the detection results of the chemical composition in the vicinity of the microtwin crystals. [Diagram 5] FIG. 1 shows the stacking fault diagram of the deformed superlattice after long-term fracture of the nickel-based high temperature alloy Comparative Example 1# according to Comparative Example 1 of the present disclosure, and the detection results of the chemical composition in the vicinity of the stacking fault. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] The following will clearly and completely describe the technical solution of the present disclosure with the aid of drawings and specific embodiments, and the examples described below are only some examples for describing the present disclosure, not all examples, and should not be considered as limiting the scope of the present disclosure. All other examples obtained by those skilled in the art without using their inventive abilities based on the examples of the present disclosure also belong to the scope of protection of the present disclosure. In the examples, specific conditions are not specified, and the examples can be performed under conventional conditions or conditions recommended by the manufacturer. For reagents or instruments used that are not specified by the manufacturer, conventional products available on the market can be used.

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

[0013] The creep of high temperature alloys is mainly caused by micro twins and dislocation climb, so suppressing twins and dragging dislocations are the basic mechanisms of the present disclosure. The nickel-based high temperature alloy of the present disclosure has excellent creep resistance properties and a service temperature of 780°C or higher. Nb, W, Ti and Ta can synergistically strengthen the γ' phase, and the main strengthening method is to use specific Nb, W, Ti, Ta, Cr and Co to generate Suzuki atmosphere of specific elements in micro twins and superlattice stacking faults, thereby pinning dislocations and improving creep resistance properties.

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

[0015] The total mass fraction of Ti, Nb and Ta is adjusted to 7.8% to 9.3% so that the Al sublattice and Ti sublattice of the γ' phase are replaced by Ta and Nb. The alloy obtained within the composition range of the nickel-based high temperature alloy according to the present disclosure generates Suzuki atmospheres in which different elements are unevenly distributed at different positions, and in the creep process at 780°C or higher, a stable Cr, Co-rich Suzuki atmosphere is obtained with fine twins, and a stable Ta, Nb, W, Ti-rich Suzuki atmosphere is obtained with stacking faults of superlattices. The strengthening method of pinning dislocations by the Suzuki effect requires an alloy composition within the above content range. If the sum of the mass fractions of Nb and W exceeds a certain range, a lumpy μ phase is precipitated in the matrix, and if it is below the certain range, W is not effectively dragged by the stacking faults. If the sum of the mass fractions of Ti, Nb, and Ta is below the certain range, a stable Suzuki effect is not obtained in the creep process at 780°C or higher, and if it exceeds the certain range, a lumpy η phase is precipitated in the matrix.

[0016] For example, in different embodiments, the content of each element in the nickel-base high temperature alloy, in mass fraction, can be as follows: The Co content can be 17%, 17.5%, 18%, 18.5%, 19%, 19.5%, 20%, 20.5%, 21%, 21.5%, 22%, etc. The Cr content can be 9%, 9.5%, 10%, 10.5%, 11%, 11.5%, 12%, 12.5%, 13%, etc. The Ta content 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 Al content 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 Ti content 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 W content 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 Mo content 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 Nb content can be 1.65%, 1.7%, 1.75%, 1.8%, 1.85%, 1.9%, 1.95%, etc. The Hf content can be 0.2%, 0.3%, 0.4%, 0.5%, 0.6%, 0.7%, etc. The C content can be 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, etc. The B content can be 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, etc. The Zr content may be 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, etc.

[0017] The above contents of each element are merely examples and are not limited thereto, and the contents may be within other specified ranges. In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a total mass fraction of Nb and W of 4.1% to 5.1%. For example, in different embodiments, the nickel-base high temperature alloy 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 to the above range, W can be effectively dragged to stacking faults while avoiding the precipitation of agglomerated μ phase in the matrix. As a result, when blended with other components, a Ta, Nb, W, Ti-rich Suzuki atmosphere that is stable in the stacking faults of the superlattice under high temperature conditions can be obtained.

[0018] In any embodiment of the present disclosure, the nickel-base high temperature alloy 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-base high temperature alloy 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 to the above range, the Al sublattice and Ti sublattice in the γ' phase can be substituted with Ta and Nb at a good ratio while avoiding the precipitation of massive η phase in the matrix. As a result, when blended with other components, a Ta, Nb, W, Ti-rich Suzuki atmosphere that is stable in the stacking faults of the superlattice under high temperature conditions can be obtained.

[0019] In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a mass fraction of Ti, Al, Nb, and Ta that satisfies (Ti+Al) / (Nb+Ta)=1.1 to 1.3. For example, in different embodiments, the nickel-base high temperature alloy may have a (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 fractions of Ti, Al, Nb, and Ta within the above ranges, the Al sublattice and Ti sublattice in the γ' phase are replaced by Ta and Nb in optimal ratios, ensuring the stability of the Suzuki atmosphere that is formed.

[0020] In any embodiment of the present disclosure, the nickel-base high temperature alloy may have a mass fraction of Cr, Co, and Ni that satisfies Cr / (Co+Ni)=0.14 to 0.18. For example, in different embodiments, the nickel-based high temperature alloy may have a 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 to fall 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 high temperature alloy may further include Mg and / or Ce. Furthermore, the Mg content may be greater than 0 and less than or equal to 0.01%, and the Ce content may be greater than 0 and less than or equal to 0.01%. For example, the Mg content may be 0.0005%-0.01%, and the Ce content may be 0.0005%-0.01%.

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

[0023] In any embodiment of the present disclosure, the nickel-base high temperature alloy 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 stacking faults of the superlattice due to creep deformation during creep at 780°C. In any embodiment of the present disclosure, the nickel-base high temperature alloy has a structure in which the deformed stacking faults are mainly located within the strengthening phase during creep at 780°C.

[0024] The present disclosure further provides a method for preparing any of the above nickel-base high temperature alloys, the method comprising the steps of preparing a bar by vacuum induction melting, producing alloy powder from the bar by vacuum inert gas atomization, subjecting the alloy powder to hot isostatic pressing to obtain a blank, and subjecting the blank to hot extrusion, forging and heat treatment.

[0025] In any embodiment of the present disclosure, the hot isostatic pressing treatment is performed at a temperature of 1120 to 1130° C., at a pressure of 140 to 150 MPa, and for a time of 4 to 10 hours. In any embodiment of the present disclosure, the hot extrusion has 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 has a temperature of 1120 to 1130° C. and a reduction rate of 0.8 to 1.2 mm / s. In actual operation, the heat treatment includes solution treatment and aging treatment. Furthermore, the solution treatment is performed by heating at 1180°C for 3 hours, followed by oil quenching at an oil temperature of 150°C. The aging treatment is performed by heating at 760°C for 16 hours. The heat treatment of the dual structure (a structure having two grain sizes) uses the usual dual structure heat treatment so that the grain size of the rim is grade 5-6 and the grain size of the hub is grade 10-12.

[0026] The present disclosure further provides a structural member, the structural member being fabricated essentially from any of the nickel-base high temperature alloys described above. In any embodiment of the present disclosure, the structural member includes a turbine disk. The operating temperature of the nickel-based high temperature alloy according to the present disclosure can be increased to 780-830°C, and can meet the requirements for advanced aeroengine materials.

[0027] Examples 1 to 10 In Examples 1 to 10, nickel-based high temperature alloys 1# to 10# and their preparation methods are provided, respectively. The measured component values ​​of the nickel-based high temperature alloys are shown in Table 1.

[0028] The method for preparing the nickel-based high temperature alloy includes the following steps: (1) Prepare a φ70 mm rod by vacuum induction melting, and prepare high-temperature alloy powder from the φ70 mm rod prepared by vacuum induction melting using vacuum inert gas atomization (VIGA). (2) Sift the powder with a particle size of 53 μm or less into a stainless steel sheath. The sheath is degassed and sealed. The sealed sheath is subjected to hot isostatic pressing (HIP). The hot isostatic pressing is performed at a temperature of 1120°C, a pressure of 140 MPa, and for a period of 4 hours. (3) The hot isostatically pressed material is then hot extruded in a heating furnace. The hot extrusion temperature is 1120°C, the extrusion ratio is 6:1, and the extrusion speed is 20 mm / s. (4) The bar formed by hot extrusion was cut to a length of 400 mm, and then was isothermally forged to a disk having a diameter of 600 mm. The forging temperature was 1120°C and the reduction rate was 1 mm / s. (5) The disk material was subjected to solution treatment, oil quenching and aging treatment. After solution treatment at 1180℃ for 3 hours, it was oil quenched at an oil temperature of 150℃. Aging treatment was performed at 760℃ for 16 hours.

[0029] [Table 1]

[0030] Comparative Examples 1 to 5 In Comparative Examples 1 to 5, Comparative Example 1# to Comparative Example 5# of nickel-based high temperature alloys are provided, respectively, and the preparation methods thereof are the same as those of Example 1, except for the composition of the nickel-based high temperature alloys. The measured component values ​​of the nickel-based high temperature alloys of Comparative Examples 1 to 5 are shown in Table 2.

[0031] [Table 2]

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

[0033] Experimental Example 1 In order to compare the differences between the nickel-based high temperature alloys of the examples and the comparative examples, the microstructures of the nickel-based high temperature alloys of the examples and the comparative examples are shown. FIG. 1 is a microstructure photograph of the nickel-based high temperature alloy 1# according to the example 1 of the present disclosure after a long-term fracture. FIG. 2 is a microstructure photograph of the nickel-based high temperature alloy Comparative Example 1# according to the comparative example 1 after a long-term fracture. Taking the example of the example 1 as an example, the deformed stacking faults in the structure are mainly located inside the reinforced phase, while the deformed stacking faults in the comparative example 1 extend through the reinforced phase.

[0034] FIG. 3 is a diagram showing the stacking faults of the deformed superlattice after a long-term fracture of the nickel-based high temperature alloy 1# according to Example 1 of the present disclosure and the detection result of the chemical composition in the vicinity of the stacking faults. FIG. 4 is a diagram showing the deformed fine twins after a long-term fracture of the nickel-based high temperature alloy 1# according to Example 1 of the present disclosure and the detection result of the chemical composition in the vicinity of the fine twins. FIG. 5 is a diagram showing the stacking faults of the deformed superlattice after a long-term fracture of the nickel-based high temperature alloy Comparative Example 1# according to Comparative Example 1 and the detection result of the chemical composition in the vicinity of the stacking faults. As can be seen from the figure, the nickel-based high temperature alloy 1# according to Example 1 of the present disclosure has Suzuki uneven distribution rich in Co, Nb, Ta, and W in the stacking faults of the superlattice, and Suzuki atmospheres of Co, W, Ta, and Nb, and Suzuki uneven distribution rich in Co and Cr in the fine twins, and Suzuki atmospheres of Co and Cr. On the other hand, the nickel-based high temperature alloy Comparative Example 1# according to Comparative Example 1 has no uneven distribution of elements in the stacking faults after a long-term fracture. Due to the effect of Suzuki uneven distribution in the embodiment of the present disclosure, dislocations and stacking faults are pulled, making it difficult for deformation to proceed, thereby improving creep strength. When the chemical composition in the vicinity of the deformed stacking faults after a long-term fracture of the nickel-based high temperature alloy according to another embodiment was detected, the result was almost the same as that of Example 1. When the chemical composition in the vicinity of the deformed stacking faults after a long-term fracture of the nickel-based high temperature alloy according to another comparative example was detected, similarly, there was no uneven distribution of elements in the stacking faults.

[0035] Experimental Example 2 In accordance with GB / T2039-2012, the high temperature life of the nickel-based high temperature alloys 1# to 10# prepared in Examples 1 to 10 and the alloys of Comparative Examples 1 to 10 was 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 certain range, the strengthening method of the alloy is changed, and the Suzuki atmosphere of specific elements is generated in the stacking faults of the fine twins and superlattices, and the creep resistance is improved by pinning the dislocations. Therefore, the use temperature of the alloy can be increased to above 780°C.

[0038] Finally, it should be noted that the above embodiments are merely for illustrating the technical solutions of the present disclosure, and are not intended to limit the same. Although the present disclosure has been described in detail with reference to the above embodiments, those skilled in the art may modify the technical solutions described in the above embodiments, and 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 the embodiments of the present disclosure. [Industrial Applicability]

[0039] The embodiments of the present disclosure provide a nickel-based high temperature alloy, its preparation method, and structural members. The nickel-based high temperature alloy of the present disclosure uses Nb, W, Ti, and Ta to synergistically strengthen the γ' phase, generate Suzuki atmospheres of specific elements in fine twins and stacking faults of superlattices, and pin dislocations to improve creep resistance. The operating temperature of the nickel-based high temperature alloy of the present disclosure can be increased to 780-830°C, and the requirements for materials of advanced aviation engines can be met.

[0040] In addition, the nickel-based high temperature alloy, its preparation method, and structural member according to the embodiment of the present disclosure are reproducible and can be applied to various industrial applications. For example, the nickel-based high temperature alloy, its preparation method, and structural member according to the embodiment of the present disclosure can be applied to technical fields related to nickel-based high temperature alloys.

Claims

1. 1. A nickel-base high-temperature alloy having a composition containing, in mass fractions, 17% to 22% Co, 9% to 13% Cr, 2.95% to 3.95% Ta, 2.5% to 3.5% Al, 2.5% to 3.5% Ti, 2.1% to 3.5% W, 2.1% to 3.5% Mo, 1.65% to 1.95% Nb, 0.2% to 0.7% Hf, 0.03% to 0.08% C, 0.01% to 0.06% B, 0.03% to 0.07% Zr, and the balance: Ni, wherein the sum of the mass fractions of Nb and W is 3.75% to 5.25%.

2. The nickel-based high temperature alloy according to claim 1, wherein the nickel-based high temperature alloy has a total mass fraction of Nb and W of 4.1% to 5.1%.

3. The nickel-based high temperature alloy according to claim 1 or 2, wherein the nickel-based high temperature alloy has a total mass fraction of Ti, Nb, and Ta of 7.8% to 9.3%.

4. The nickel-based high temperature alloy according to any one of claims 1 to 3, wherein the mass fractions of Ti, Al, Nb, and Ta satisfy (Ti + Al) / (Nb + Ta) = 1.1 to 1.

3.

5. The nickel-based high temperature alloy according to any one of claims 1 to 4, wherein the mass fraction of Cr, Co and Ni in the nickel-based high temperature alloy satisfies Cr / (Co+Ni) = 0.14 to 0.

18.

6. The nickel-based high temperature alloy further comprises Mg and / or Ce; The Mg content is more than 0 and 0.01% or less, and the Ce content is more than 0 and 0.01% or less. A nickel-based high temperature alloy according to any one of claims 1 to 5.

7. The nickel-based high temperature alloy has a Suzuki atmosphere containing Cr and Co in the fine twin crystals due to creep deformation during the creep process at 780°C, and has a Suzuki atmosphere containing Ta, Nb, W and Ti in the stacking faults of the superlattice due to creep deformation. A nickel-based high temperature alloy according to any one of the preceding claims.

8. A process for preparing the nickel-based high temperature alloy according to any one of claims 1 to 7, comprising the steps of: preparing a bar by vacuum induction melting; preparing alloy powder from the rod by a vacuum inert gas atomization method; performing hot isostatic pressing on the alloy powder to obtain a blank; and subjecting the blank to hot extrusion, forging and heat treatment. Preparation method.

9. The preparation method according to claim 8, wherein the hot isostatic pressing is performed at a temperature of 1120-1130°C, a pressure of 140-150MPa, and a time of 4-10 hours.

10. The preparation method according to claim 8 or 9, wherein the hot extrusion is 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.

11. The preparation method according to any one of claims 8 to 10, wherein the forging is isothermal forging, the temperature of the isothermal forging is 1120 to 1130 ° C, and the rolling speed is 0.8 to 1.2 mm / s.

12. A structural component made essentially of the nickel-based high temperature alloy according to any one of claims 1 to 7.

13. The structural member of claim 12 , wherein the structural member comprises a turbine disk.

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