High-strength, high-toughness, oxidation-resistant nickel-based superalloy and its preparation method and application

Abstract

The present invention discloses a nickel-based superalloy with high strength, high toughness and oxidation resistance, comprising: C: 0.08-0.2%; Cr: 8.2-10%; Co: 8.5-10.2%; W: 9.5-11.0%; Mo: 0.1-1.5%; Ta: 2.0-4.0%; Al: 4.0-6.5%; Ti: 0.2-1.5%; B: 0.002-0.018%; Hf: 1.2-2.8%; Zr: 0.001-0.05%; Mg ≤ 0.005%; Si ≤ 0.15%; Mn ≤ 0.05%; Ba: 0.01-0.05%; the balance being Ni and unavoidable impurities, by mass percentage. The nickel-based superalloy of the present invention has excellent mechanical properties, oxidation resistance and creep life.

Description

Technical Field

[0001] The present invention belongs to the technical field of superalloys, and particularly relates to a nickel-based superalloy with high strength, high toughness and oxidation resistance, and a preparation method and application thereof. Background Art

[0002] Superalloy materials generally refer to materials that work under certain stress load conditions above 600°C. They need to have good strength-toughness matching and oxidation resistance, and at the same time have excellent high-temperature strength, creep resistance, fatigue resistance and other characteristics. Therefore, a large number of strengthening elements such as W, Mo, Ti, Al, Hf, Co, etc. are added to the alloy to ensure its superior high-temperature performance.

[0003] At present, the hot-end components of advanced aero-engines and gas turbines have the highest working conditions up to 1300°C, and the stress action is complex, which puts harsh requirements on the alloy materials. There are almost no alloys among the existing superalloys at home and abroad that can fully meet the usage requirements. Generally, the alloys that can meet the mechanical property requirements have unmatched strength and toughness, and poor oxidation resistance.

[0004] Therefore, how to prepare a superalloy that can meet the usage requirements of aero-engines and gas turbines has received more and more extensive attention. Summary of the Invention

[0005] The present invention is made based on the inventor's discovery and understanding of the following facts and problems:

[0006] At present, the superalloys used in the fields of advanced aero-engines, gas turbines, etc. cannot meet the requirements. It is hoped that the superalloy can meet the following performance indicators: at room temperature, the tensile properties are Rm≥1100MPa, Rp0.2≥825MPa, A≥8%; at high temperature tensile of 900°C, Rm≥800MPa, Rp0.2≥650MPa, A≥8%, and the oxidation rate at 900°C for 100h ≤ 0.04g / m 2 ·h, but the current superalloys have unmatched strength and toughness, and poor oxidation resistance, and cannot meet the above requirements.

[0007] The present invention aims to solve at least one of the technical problems in the related art to some extent. For this reason, an embodiment of the present invention provides a nickel-based superalloy with high strength, high toughness and oxidation resistance. This alloy has excellent mechanical properties, oxidation resistance and creep rupture life, can meet the design and usage requirements of advanced aero-engines and gas turbines, and is suitable for components such as turbine blades that serve in the hot-end components of aero-engines and gas turbines for a long time.

[0008] The high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to the embodiments of the present invention comprises: C: 0.08-0.2%; Cr: 8.2-10%; Co: 8.5-10.2%; W: 9.5-11.0%; Mo: 0.1-1.5%; Ta: 2.0-4.0%; Al: 4.0-6.5%; Ti: 0.2-1.5%; B: 0.002-0.018%; Hf: 1.2-2.8%; Zr: 0.001-0.05%; Mg≤0.005%; Si≤0.15%; Mn≤0.05%; Ba: 0.01-0.05%; the balance is Ni and unavoidable impurities, by mass percentage.

[0009] The advantages and technical effects brought by the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to the embodiments of the present invention are as follows: 1. In the embodiments of the present invention, the added Ba element can partially disconnect the reticular β phase and distribute it in small pieces at the grain boundaries, which can significantly refine the grains of the alloy. After adding Ba to the alloy containing Mg, the tensile strength and elongation rate of the alloy can be improved simultaneously, achieving the effect of high strength and high toughness. In addition, Ba can further promote deoxidation and desulfurization in the alloy, making the alloy pure; 2. In the embodiments of the present invention, by controlling the dosage of each element within a reasonable range, the alloy not only has excellent tensile properties and oxidation resistance, but also has excellent strength-toughness matching, and can be applied to advanced aeroengines and gas turbines.

[0010] In some embodiments, W, Hf and Ba satisfy the relationship 5.0 < W - Hf / 15.5Ba < 8.0, where W, Hf and Ba are the values obtained by removing the percentage sign from the mass percentages of elements W, Hf and Ba in the nickel-based superalloy.

[0011] In some embodiments, W, Hf and Ba satisfy the relationship 5.4 < W - Hf / 15.5Ba < 7.7.

[0012] In some embodiments, Hf, W and Al satisfy the relationship 0.7 < Hf - 0.25W / Al < 1.8, where Hf, W and Al are the values obtained by removing the percentage sign from the mass percentages of elements Hf, W and Al in the nickel-based superalloy.

[0013] In some embodiments, Hf, W and Al satisfy the relationship 0.7 < Hf - 0.25W / Al < 1.6.

[0014] In some embodiments, the high-strength, high-toughness, oxidation-resistant nickel-based superalloy comprises: C: 0.08 to 0.16%; Cr: 8.3 to 9.8%; Co: 8.6 to 10.1%; W: 9.7 to 10.9%; Mo: 0.2 to 1.5%; Ta: 2.2 to 4.0%; Al: 4.1 to 6.4%; Ti: 0.2 to 1.5%; B: 0.002 to 0.017%; Hf: 1.2 to 2.5%; Zr: 0.001 to 0.05%; Mg ≤ 0.004%; Si ≤ 0.03%; Mn ≤ 0.04%; Ba: 0.02 to 0.04%; the balance being Ni and unavoidable impurities, by mass percentage.

[0015] The embodiments of the present invention also provide an application of the high-strength, high-toughness, oxidation-resistant nickel-based superalloy in the turbine blade of the hot-end component of an aeroengine.

[0016] The embodiments of the present invention also provide an application of the high-strength, high-toughness, oxidation-resistant nickel-based superalloy in the turbine blade of the hot-end component of a gas turbine.

[0017] The embodiments of the present invention also provide a preparation method of the high-strength, high-toughness, oxidation-resistant nickel-based superalloy, comprising the following steps:

[0018] (1) According to the alloy design ratio, add raw materials of Cr, Co, W, Mo, Ta, B, Hf, Zr, Mg, Si, Mn, Ba and part of C into the crucible, heat and melt under vacuum, and then carry out heat preservation treatment;

[0019] (2) After the heat preservation treatment in the step (1) is completed, add Al, Ti and the remaining C raw materials into the crucible, introduce argon, heat and melt under vacuum, and cast to obtain the nickel-based superalloy.

[0020] The advantages and technical effects brought by the preparation method of the high-strength, high-toughness, oxidation-resistant nickel-based superalloy in the embodiments of the present invention are as follows: 1. In the method of the embodiments of the present invention, adding the C element step by step is beneficial to removing the gas in the alloy and can also improve the mechanical properties of the alloy; 2. The alloy prepared by the method of the embodiments of the present invention not only has excellent strength and toughness properties and creep life, but also has good oxidation resistance, and can meet the requirements of the design and use of advanced aeroengines and gas turbines.

[0021] In some embodiments, in the step (1), the part of C raw material is 8 to 25% of the designed dosage of C raw material. Detailed Embodiments

[0022] The embodiments of the present invention will be described in detail below. The embodiments are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0023] The high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to the embodiment of the present invention comprises: C: 0.08-0.2%; Cr: 8.2-10%; Co: 8.5-10.2%; W: 9.5-11.0%; Mo: 0.1-1.5%; Ta: 2.0-4.0%; Al: 4.0-6.5%; Ti: 0.2-1.5%; B: 0.002-0.018%; Hf: 1.2-2.8%; Zr: 0.001-0.05%; Mg≤0.005%; Si≤0.15%; Mn≤0.05%; Ba: 0.01-0.05%; the balance being Ni and inevitable impurities, by mass percentage.

[0024] For the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to the embodiment of the present invention, the added Ba element can partially disconnect the network-like β phase and distribute it in small pieces at the grain boundaries, which can significantly refine the grains of the alloy. After adding Ba to the alloy containing Mg, the tensile strength and elongation rate of the alloy can be improved simultaneously, achieving the effect of high strength and high toughness. In addition, Ba can further promote deoxidation and desulfurization in the alloy, making the alloy pure. By controlling the dosage of each element within a reasonable range, the alloy not only has excellent tensile properties and oxidation resistance, but also has excellent strength-toughness matching, and can be applied to advanced aeroengines and gas turbines.

[0025] Among them, the functions of the main elements in the alloy according to the embodiment of the present invention are as follows:

[0026] C: In the nickel-based superalloy, C mainly inhibits the growth of austenite grains during heating by forming MC-type carbides at the end of solidification, and forms M 23 C6 and other types of carbides along the grain boundaries during heat treatment, playing a role in strengthening the grain boundaries, which can delay the initiation, propagation and coalescence of microcracks, thereby improving the high-temperature creep life of the alloy. In the embodiment of the present invention, the C content is controlled to be 0.08-0.2%.

[0027] Cr: Cr can improve the oxidation resistance of the alloy and has a solid solution strengthening effect. After aging treatment, it can also combine with C to form granular M 23 C6 distributed along the grain boundaries, playing a role in strengthening the grain boundaries. In the embodiment of the present invention, the Cr content is controlled to be 8.2-10%.

[0028] Co: Co is an important solid solution strengthening element and precipitation strengthening element, providing a good solid solution strengthening effect for the alloy, significantly reducing the stacking fault energy of the matrix, broadening the width of the extended dislocation, making it difficult for dislocations to bundle and cross-slip, thereby improving the creep resistance and creep life of the alloy; Co can also partially replace the elements in the Ni3Al-type precipitation strengthening phase, improving the stability of the phase during long-term service; in the embodiment of the present invention, the Co content is controlled to be 8.5-10.2%.

[0029] W and Mo: They are one of the main solid solution strengthening elements. They can be dissolved in both the alloy matrix and the γ′ strengthening phase, and at the same time can increase the interatomic binding force, raise the diffusion activation energy and the recrystallization temperature, thereby effectively improving the high-temperature strength of the alloy. In the embodiments of the present invention, the W content is controlled at 9.5 - 11.0%, and the Mo content is controlled at 0.1 - 1.5%.

[0030] Al, Ti and Ta: They are the forming elements of the strengthening phase γ′ in nickel-based alloys. With the increase of the contents of the three, the number of γ′ increases, and the high-temperature creep and stress rupture properties are improved. However, too much γ′ will deteriorate the processing performance. In the embodiments of the present invention, Al is controlled at 4.0 - 6.5%, Ti is controlled at 0.2 - 1.5%, and Ta is controlled at 2 - 4%.

[0031] B: B atoms are easily enriched at grain boundaries, increasing the grain boundary binding force; borides on grain boundaries can prevent grain boundary slip, void initiation and propagation, which is beneficial to improving the creep resistance and stress rupture life of the alloy. In the embodiments of the present invention, the B content is controlled at 0.002 - 0.018%.

[0032] Zr: Zr can purify grain boundaries and enhance the grain boundary binding force, but excessive Zr is likely to reduce the processing performance. In the embodiments of the present invention, the Zr content is controlled at 0.001 - 0.05%.

[0033] Mg: Mg atoms segregate at grain boundaries, which can increase the grain boundary binding force and the grain boundary strength; Mg atoms also segregate at the carbide phase boundary and the γ′ phase boundary and enter γ′ and carbides, which is beneficial to improving the mechanical properties. In the embodiments of the present invention, the Mg content is controlled to be less than 0.005%.

[0034] Ba: Ba can significantly refine the as-cast structure of the alloy, disconnect part of the network β phase, and distribute it in small pieces at grain boundaries, and the alloy grain refinement effect is significant; after adding Ba to the Mg-containing nickel-based alloy, the tensile strength and elongation of the alloy can be improved simultaneously, achieving excellent strength-ductility matching; Ba can promote further deoxidation and desulfurization of the alloy in the alloy, making the alloy pure. In the embodiments of the present invention, the Ba content is controlled at 0.01 - 0.05%.

[0035] In some embodiments, preferably, the W, Hf and Ba satisfy the relationship 5.0 < W - Hf / 15.5Ba < 8.0, where W, Hf and Ba are the values obtained by removing the percentage sign from the mass percentage contents of the elements W, Hf and Ba in the nickel-based superalloy. Further preferably, the W, Hf and Ba satisfy the relationship 5.4 < W - Hf / 15.5Ba < 7.7.

[0036] In the implementation of the present invention, it is defined that W, Hf, and Ba satisfy the relational expression 5.0 < W - Hf / 15.5Ba < 8.0, which can enable the alloy to improve the tensile strength and elongation rate of the alloy while maintaining good oxidation resistance, endow the alloy with excellent high strength and high toughness matching, and is beneficial to improving the creep life of the alloy.

[0037] In some embodiments, preferably, Hf, W, and Al satisfy the relational expression 0.7 < Hf - 0.25W / Al < 1.8, where Hf, W, and Al are the values after removing the percentage signs of the mass percentages of elements Hf, W, and Al in the nickel-based superalloy. Further preferably, Hf, W, and Al satisfy the relational expression 0.7 < Hf - 0.25W / Al < 1.6.

[0038] In the embodiments of the present invention, it is defined that Hf, W, and Al satisfy the relational expression 0.7 < Hf - 0.25W / Al < 1.8, which is beneficial to further improving the tensile properties and creep life of the alloy.

[0039] In some embodiments, the high-strength, high-toughness, and oxidation-resistant nickel-based superalloy includes: C: 0.08 - 0.16%; Cr: 8.3 - 9.8%; Co: 8.6 - 10.1%; W: 9.7 - 10.9%; Mo: 0.2 - 1.5%; Ta: 2.2 - 4.0%; Al: 4.1 - 6.4%; Ti: 0.2 - 1.5%; B: 0.002 - 0.017%; Hf: 1.2 - 2.5%; Zr: 0.001 - 0.05%; Mg ≤ 0.004%; Si ≤ 0.03%; Mn ≤ 0.04%; Ba: 0.02 - 0.04%; the balance is Ni and unavoidable impurities, by mass percentage.

[0040] The embodiments of the present invention also provide an application of the high-strength, high-toughness, and oxidation-resistant nickel-based superalloy in the turbine blade of the hot end component of an aeroengine. The high-strength, high-toughness, and oxidation-resistant nickel-based superalloy in the embodiments of the present invention meets the requirements of advanced aeroengine design and use and can be applied in the turbine blade of the hot end component of an advanced aeroengine.

[0041] The embodiments of the present invention also provide an application of the high-strength, high-toughness, and oxidation-resistant nickel-based superalloy in the turbine blade of the hot end component of a gas turbine. The high-strength, high-toughness, and oxidation-resistant nickel-based superalloy in the embodiments of the present invention meets the requirements of gas turbine design and use and can be applied in the turbine blade of the hot end component of a gas turbine.

[0042] The embodiments of the present invention also provide a preparation method of the high-strength, high-toughness, and oxidation-resistant nickel-based superalloy, including the following steps:

[0043] (1) According to the alloy design ratio, add the raw materials of Cr, Co, W, Mo, Ta, B, Hf, Zr, Mg, Si, Mn, Ba and part of C into the crucible, heat and melt them under vacuum, and then carry out heat preservation treatment;

[0044] (2) After the heat preservation treatment in step (1) is completed, add Al, Ti and the remaining C raw materials into the crucible, introduce argon, heat and melt them under vacuum, and cast to obtain a nickel-based superalloy.

[0045] In the preparation method of the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to the embodiment of the present invention, adding C element step by step is beneficial to removing the gas in the alloy and can also improve the mechanical properties of the alloy; the obtained alloy not only has excellent strength and toughness properties and creep life, but also has good oxidation resistance, and can meet the requirements of the design and use of advanced aeroengines and gas turbines.

[0046] In some embodiments, preferably, in step (1), the part of C raw material is 8-25% of the designed dosage of C raw material. Further preferably, in step (1), the heat preservation temperature is 1600°C - 1650°C, and the heat preservation time is 10 - 30 min. In step (2), the introduction amount of argon is based on making the air pressure in the crucible be -0.02 - -0.1 MPa; the vacuum degree of the vacuum condition is <0.1 Pa, and the casting temperature is ≥1560°C.

[0047] The technical solution of the present invention will be described in detail below in conjunction with specific embodiments.

[0048] Example 1

[0049] (1) Add Cr, Co, W, Mo, Ta, B, Hf, Zr, Mg, Si, Mn, Ba and 15% of C raw material into the crucible, heat it under vacuum until it is completely melted, then control the temperature at 1610°C, control the vacuum degree to be less than 0.1 Pa, keep heat preservation for 10 min and then stop heating, and keep it for 5 min;

[0050] (2) Add Al, Ti and the remaining C raw materials into the crucible; at the same time, fill the furnace with argon until the pressure is -0.02 MPa, heat and melt it under the vacuum degree less than 0.1 Pa, tap the steel at 1560°C for casting, cool it to room temperature, demold it, and carry out surface sandblasting and grinding to remove the oxide scale to obtain a nickel-based superalloy.

[0051] The preparation methods of Examples 2 - 8 are the same as those of Example 1, except that the alloy compositions are different.

[0052] The alloy compositions obtained in Examples 1 - 8 are shown in Table 1, and the properties are shown in Table 2.

[0053] Comparative Example 1

[0054] Same as Example 1, except that the alloy does not contain Ba element.

[0055] The performance data of the alloy prepared in Comparative Example 1 are shown in Table 2.

[0056] Comparative Example 2

[0057] Same as Example 1, except that the Ba content of the alloy is 0.12%.

[0058] The performance data of the alloy prepared in Comparative Example 2 are shown in Table 2.

[0059] Comparative Example 3

[0060] Same as Example 1, except that the W content in the alloy is 8.2%.

[0061] The performance data of the alloy prepared in Comparative Example 3 are shown in Table 2.

[0062] Table 1

[0063]

[0064]

[0065] Table 2

[0066]

[0067]

[0068] Note: 1. Rm is the tensile strength, Rp0.2 is the tensile yield strength, and A is the elongation;

[0069] 2. The average oxidation rate is the oxidation rate per unit area of the alloy at 900 °C / 100 h. The smaller this value, the better the oxidation resistance.

[0070] It can be seen from the data in the above table that Examples 1 to 8 have very good tensile properties, creep life and oxidation resistance at room temperature and 900 °C. At room temperature, Rm ≥ 1110 MPa, Rp0.2 ≥ 850 MPa, A ≥ 9.0%; at 900 °C high temperature tensile, Rm ≥ 820 MPa, Rp0.2 ≥ 680 MPa, A ≥ 9.0%, the creep time at 980 °C and 200 MPa is greater than 120 h, and the oxidation rate at 900 °C and 100 h is ≤ 0.04 g / m 2 ·h, which can meet the use requirements of superalloys in the fields of aeroengines, gas turbines, etc. In particular, when the relational expressions 0.8 < Hf - 0.25W / Al < 1.8 and 5.0 < W - Hf / 15.5Ba < 8.0 are satisfied, such as Examples 2 to 8, the prepared nickel-based superalloy has more excellent properties.

[0071] In Comparative Example 1, the element Ba was not contained, resulting in a significant decrease in the tensile strength of the nickel-based superalloy prepared in Comparative Example 1 at room temperature and 900 °C, and a substantial decrease in the elongation A. At the same time, the creep rupture time at 980 °C and 200 MPa decreased to 54 h, and the oxidation rate at 900 °C for 100 h increased to 0.08 g / m 2 ·h.

[0072] In Comparative Example 2, the content of the element Ba was too high, which also led to a decrease in the tensile strength and elongation of the prepared nickel-based superalloy at room temperature and 900 °C, and a decrease in the creep rupture life and oxidation resistance, failing to meet the usage requirements.

[0073] In Comparative Example 3, the content of the element W was adjusted. Although the tensile strength at room temperature could be maintained at Rm = 1003 MPa and Rp0.2 = 845 MPa, the tensile strength at 900 °C decreased significantly, and the elongation A at room temperature and 900 °C decreased to 5.5%. In addition, the creep rupture life and oxidation resistance also decreased significantly, failing to meet the usage requirements.

[0074] In the present invention, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0075] Although the above embodiments have been shown and described, it can be understood that the above embodiments are exemplary and should not be construed as limitations on the present invention. Any changes, modifications, substitutions, and variations made by those of ordinary skill in the art to the above embodiments are within the protection scope of the present invention.

Claims

1. A nickel-based superalloy with high strength, high toughness and oxidation resistance, characterized in that, Comprising: C: 0.08 - 0.2%; Cr: 8.2 - 10%; Co: 8.5 - 10.2%; W: 9.5 - 11.0%; Mo: 0.1 - 1.5%; Ta: 2.0 - 4.0%; Al: 4.0 - 6.5%; Ti: 0.2 - 1.5%; B: 0.002 - 0.018%; Hf: 1.2 - 2.8%; Zr: 0.001 - 0.05%; Mg ≤ 0.005%; Si ≤ 0.15%; Mn ≤ 0.05%; Ba: 0.01 - 0.05%; the balance being Ni and unavoidable impurities, by mass percentage; The W, Hf and Ba satisfy the relation 5.0 < W - Hf / 15.5Ba < 8.0, where W, Hf and Ba are the values after removing the percentage sign of the mass percentages of elements W, Hf and Ba in the nickel-based superalloy.

2. The high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to claim 1, characterized in that, The W, Hf and Ba satisfy the relation 5.4 < W - Hf / 15.5Ba < 7.

7.

3. The high-strength, high-toughness, oxidation-resistant nickel-based superalloy according to claim 1, characterized in that, The Hf, W and Al satisfy the relation 0.7 < Hf - 0.25W / Al < 1.8, where Hf, W and Al are the values after removing the percentage sign of the mass percentages of elements Hf, W and Al in the nickel-based superalloy.

4. The high-strength, high-toughness, oxidation-resistant nickel-based superalloy according to claim 3, characterized in that, The Hf, W, Al satisfy the relation 0.7 < Hf - 0.25W / Al < 1.

6.

5. The high-strength, high-toughness, oxidation-resistant nickel-based superalloy according to claim 1, characterized in that, Comprising: C: 0.08 - 0.16%; Cr: 8.3 - 9.8%; Co: 8.6 - 10.1%; W: 9.7 - 10.9%; Mo: 0.2 - 1.5%; Ta: 2.2 - 4.0%; Al: 4.1 - 6.4%; Ti: 0.2 - 1.5%; B: 0.002 - 0.017%; Hf: 1.2 - 2.5%; Zr: 0.001 - 0.05%; Mg ≤ 0.004%; Si ≤ 0.03%; Mn ≤ 0.04%; Ba: 0.02 - 0.04%; the balance being Ni and unavoidable impurities, by mass percentage.

6. Application of the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to any one of claims 1 - 5 in hot-end components of an aeroengine.

7. Application of the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to any one of claims 1 - 5 in hot-end components of a gas turbine.

8. A method for preparing a high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to any one of claims 1 to 5, characterized in that, Comprising the following steps: (1) According to the alloy design ratio, add Cr, Co, W, Mo, Ta, B, Hf, Zr, Mg, Si, Mn, Ba and part of the C raw materials into the crucible, heat and melt them under vacuum, and then carry out heat preservation treatment; (2) After the heat preservation treatment in step (1) ends, add Al, Ti and the remaining C raw materials into the crucible, introduce argon, heat and melt them under vacuum, and cast to obtain the nickel-based superalloy.

9. The preparation method of the high-strength, high-toughness and oxidation-resistant nickel-based superalloy according to claim 8, characterized in that, In step (1), the part of the C raw materials is 8 - 25% of the designed dosage of the C raw materials.

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