Low-inclusion, heat-shock-resistant nickel-based superalloy and its preparation method and application

Abstract

The present invention belongs to the technical field of superalloys, and particularly relates to a nickel-based superalloy with low inclusions and resistance to thermal shock, and a preparation method and application thereof. The present invention provides a nickel-based superalloy with low inclusions and resistance to thermal shock, comprising: C: 0.05 to 0.25%, Cr: 4.0 to 7.5%, Co: 4.5 to 7.0%, W: 13.5 to 17.5%, Al: 1.0 to 4.0%, Ta: 3.0 to 4.5%, Mo: 4.7 to 8.5%, Hf: 1.5 to 2.8%, Ti: 3.0 to 6.0%, B: 0.04 to 0.15%, Zr: 0.06 to 0.25%, Mg: 0.001 to 0.07%, Mn: ≤0.5%, Si: ≤0.5%, Nd: 0.1 to 0.5%, Ba: 0.06 to 0.25%, and the balance being nickel and unavoidable impurities, by mass percentage.

Description

Technical Field

[0001] The present invention belongs to the technical field of nickel-based superalloys, and particularly relates to a nickel-based superalloy with low inclusions and heat shock resistance, and a preparation method and application thereof. Background Art

[0002] In recent decades, with the continuous improvement of the thrust-to-weight ratio of aeroengines, the research on the working environment and failure modes of turbine blades has become increasingly in-depth at home and abroad. During the operation of the engine, operations such as startup, shutdown, sudden acceleration and deceleration cause the turbine blades to be repeatedly subjected to thermal shock, resulting in thermal shock fatigue failure of the turbine blades and greatly shortening the service life. Nickel-based superalloys are the core materials for manufacturing turbine blades of aeroengines and gas turbines. With the development of engines and gas turbines, higher requirements are put forward for the long-term high-temperature performance stability and thermal shock resistance of nickel-based superalloys.

[0003] In addition to the complex working environment, the reasons for the thermal shock fatigue failure of nickel-based superalloys are also related to the structure of the alloy itself. For example, internal defects and structures such as microvoids, carbides, residual eutectics, and grain boundaries, as well as some endogenous inclusions and exogenous inclusions in the alloy, will all become crack sources and cause a decrease in impact performance.

[0004] Therefore, how to prepare a nickel-based superalloy with excellent thermal shock resistance to meet the application requirements of aeroengine and gas turbine 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] Nickel-based superalloys are a kind of high-temperature alloys with nickel as the matrix and other alloying elements added, and have excellent high-temperature performance, good oxidation resistance and corrosion resistance, and are the core materials for manufacturing turbine blades. However, with the continuous improvement of the thrust-to-weight ratio of aeroengines, the working environment of turbine blades is complex. During the operation of the engine, the working temperature gradient of different parts of the turbine blades is relatively large, which puts forward higher requirements for the high-temperature performance and thermal shock resistance of nickel-based superalloys. At present, the prepared nickel-based superalloys still cannot meet the usage requirements.

[0007] The present invention aims to solve at least one of the technical problems in the related art to some extent. To this end, an embodiment of the present invention provides a nickel-based superalloy with low inclusions and heat shock resistance. This alloy has few inclusions, and has excellent high-temperature performance, heat shock resistance and toughness, and good processing performance at the same time. It solves the problems of poor high-temperature performance and short thermal shock fatigue life of the current nickel-based superalloys in a complex working environment, and can meet the usage requirements of high-temperature and high-stress components of aeroengines and gas turbines.

[0008] The low-inclusion and thermal-shock-resistant nickel-based superalloy according to the embodiment of the present invention comprises: C: 0.05-0.25%, Cr: 4.0-7.5%, Co: 4.5-7.0%, W: 13.5-17.5%, Al: 1.0-4.0%, Ta: 3.0-4.5%, Mo: 4.7-8.5%, Hf: 1.5-2.8%, Ti: 3.0-6.0%, B: 0.04-0.15%, Zr: 0.06-0.25%, Mg: 0.001-0.07%, Mn: ≤0.5%, Si: ≤0.5%, Nd: 0.1-0.5%, Ba: 0.06-0.25%, and the balance is nickel and inevitable impurities, by weight percentage.

[0009] The advantages and technical effects brought by the low-inclusion and thermal-shock-resistant nickel-based superalloy according to the embodiment of the present invention are as follows: 1. In the embodiment of the present invention, adding elements such as Cr, W, Mo, and Co for solution strengthening can improve the high-temperature strength of the alloy. By adding γ'-phase forming elements such as Al, Ti, Ta, and Hf, the alloy has stable long-term tissue properties at 900-1000°C. By reasonably matching grain boundary strengthening elements such as C, B, and Zr, and adding the carbide-refining effects of Mg, Nd, and Ba elements, the high-temperature performance and thermal shock performance of the alloy are significantly improved; 2. In the embodiment of the present invention, by adjusting the content of each element within a suitable range, the tensile strength of the alloy exceeds 900 MPa at 1000°C, the elongation after fracture is greater than 25.5%, the number of thermal shock fatigue cycles exceeds 3700 times, and the impact work is greater than 24.6 J. The greater the impact work, the better the impact toughness of the alloy. The number of inclusions is 17.5-22.5 per mm 2 , meeting the requirements for the design and use of advanced aeroengines and gas turbines.

[0010] In some embodiments, W, Mo, and Mg satisfy the relationship: 1.82 ≤ 0.9W / Mo - Mg ≤ 2.79, preferably 2.06 ≤ 0.9W / Mo - Mg ≤ 2.71, where W, Mo, and Mg are the values obtained by removing the percentage sign from the mass percentage contents of elements W, Mo, and Mg in the nickel-based superalloy.

[0011] In some embodiments, Al, Nd, and Ba satisfy the relationship: 0.68 ≤ Al - 2.5(Nd + Ba) ≤ 2.75, preferably 2.35 ≤ Al - 2.5(Nd + Ba) ≤ 2.7, where Al, Nd, and Ba are the values obtained by removing the percentage sign from the mass percentage contents of elements Al, Nd, and Ba in the nickel-based superalloy.

[0012] In some embodiments, the low-inclusion, thermal shock-resistant nickel-based superalloy comprises: C: 0.05 - 0.18%, Cr: 4.0 - 6.5%, Co: 5.0 - 6.3%, W: 14.0 - 16.8%, Al: 1.5 - 4.0%, Ta: 3.0 - 4.0%, Mo: 4.5 - 7.5%, Hf: 1.5 - 2.8%, Ti: 3.0 - 5.0%, B: 0.08 - 0.15%, Zr: 0.08 - 0.25%, Mg: 0.01 - 0.07%, Mn: ≤0.40%, Si: ≤0.4%, Nd: 0.2 - 0.5%, Ba: 0.1 - 0.25%, and the balance is nickel and unavoidable impurities, by weight percentage.

[0013] The embodiments of the present invention also provide an application of the low-inclusion, thermal shock-resistant nickel-based superalloy in an aeroengine.

[0014] The embodiments of the present invention also provide an application of the low-inclusion, thermal shock-resistant nickel-based superalloy in a gas turbine.

[0015] The embodiments of the present invention also provide a preparation method of a low-inclusion, thermal shock-resistant nickel-based superalloy, which is characterized by comprising the following steps:

[0016] (1) Conduct vacuum smelting according to the raw material ratio;

[0017] (2) Adjust the casting temperature and cast into a billet;

[0018] (3) Heat-treat the cast billet prepared in step (2).

[0019] The advantages and technical effects brought by the preparation method of the low-inclusion, thermal shock-resistant nickel-based superalloy in the embodiments of the present invention are as follows: 1. The method in the embodiments of the present invention can prepare a nickel-based superalloy with few inclusions, excellent high-temperature performance and thermal shock performance, good casting performance, and no defects such as shrinkage cavities and thermal cracks, meeting the requirements of the design and use of advanced aeroengines and gas turbines; 2. The method in the embodiments of the present invention has a simple process, reduces energy consumption, shortens the production cycle, improves production efficiency, and is suitable for popularization and application in industrial production.

[0020] In some embodiments, in step (1), the smelting temperature is 1210 - 1320 °C.

[0021] In some embodiments, in step (2), the casting temperature is 1000 - 1190 °C.

[0022] In some embodiments, in step (3), the heat treatment temperature is 850 - 1170 °C, and the heat treatment time is 18 - 28 h. Detailed implementation manners

[0023] 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.

[0024] The low-inclusion and thermal-shock-resistant nickel-based superalloy of the embodiment of the present invention comprises: C: 0.05-0.25%, Cr: 4.0-7.5%, Co: 4.5-7.0%, W: 13.5-17.5%, Al: 1.0-4.0%, Ta: 3.0-4.5%, Mo: 4.7-8.5%, Hf: 1.5-2.8%, Ti: 3.0-6.0%, B: 0.04-0.15%, Zr: 0.06-0.25%, Mg: 0.001-0.07%, Mn: ≤0.5%, Si: ≤0.5%, Nd: 0.1-0.5%, Ba: 0.06-0.25%, and the balance is nickel and inevitable impurities, by weight percentage.

[0025] The low-inclusion and thermal-shock-resistant nickel-based superalloy of the embodiment of the present invention can improve the high-temperature strength of the alloy through solution strengthening by adding Cr, W, Mo, and Co elements. By adding γ'-phase forming elements such as Al, Ti, Ta, and Hf, the alloy has stable long-term tissue properties at 900-1000°C. By reasonably matching grain boundary strengthening elements such as C, B, and Zr, and adding the carbide-refining effect of Mg, Nd, and Ba elements, the high-temperature performance and thermal shock performance of the alloy are significantly improved. In the embodiment of the present invention, through the solution strengthening effect of elements such as Cr, Co, W, and Mo, the age strengthening effect of elements such as Al, Ti, Ta, and Hf, and the grain boundary strengthening effect of elements such as C, B, Zr, Mg, Nd, and Ba, the tensile strength of the alloy at 1000°C exceeds 900 MPa, the elongation after fracture is greater than 25.5%, the number of thermal shock fatigue cycles exceeds 3700 times, the impact energy is greater than 24.6 J, the greater the impact energy, the better the impact toughness of the alloy, and the number of inclusions is 17.5-22.5 per mm 2 , meeting the requirements for the design and use of advanced aero-engines and gas turbines.

[0026] The functions of Mg, Nd, and Ba in the nickel-based superalloy in the embodiment of the present invention are as follows:

[0027] As a trace element, Mg mainly acts on the grain boundaries, which can change and refine the morphology of carbides at the grain boundaries, significantly increasing the creep time and fracture plasticity of the alloy at high temperatures. At the same time, Mg can reduce the influence of harmful impurity sulfur, has a good deoxidizing effect during the melting process, reduces the number of sulfide and oxide inclusions, and improves the strength and toughness of the alloy. However, when the Mg content is too high, a large amount of MC carbides will precipitate at the grain boundaries, becoming crack sources and reducing the impact toughness and creep life of the alloy. Therefore, in the embodiments of the present invention, the content of Mg element is controlled within the range of 0.001-0.07%;

[0028] Nd element can enrich at the grain boundaries, purify the grain boundaries of the alloy, and at the same time strengthen the grain boundaries. Nd element also exists in the γ / γ' two phases of the alloy in the form of Nd2O3 oxide, playing a role of dispersion strengthening, and can also refine the grains, forming Al 11 Nd3 and Mg 12 Nd strengthening phases, which pin the grain boundaries, hinder dislocation movement, and improve the strength and toughness of the alloy. However, when the Nd content is too high, it will segregate in large amounts at the grain boundaries, causing the alloy to fracture. Therefore, in the embodiments of the present invention, the content of Nd element is controlled within the range of 0.1-0.5%;

[0029] Ba element can significantly refine the as-cast structure of the alloy. Ba element is an element with relatively strong surface activity, which can combine with oxides and sulfides in the alloy. During the casting process of the alloy, inclusions gradually float up, purifying the molten steel. And Ba element can make the long strip-shaped carbides shorter and distribute in the matrix, strengthening the matrix. However, when the Ba content is too high, metal compounds distributed in a network along the grain boundaries will appear, increasing the brittleness of the alloy. Therefore, in the embodiments of the present invention, the content of Ba element is controlled within the range of 0.06-0.25%.

[0030] In some embodiments, preferably, W, Mo, and Mg satisfy the relationship: 1.82 ≤ 0.9W / Mo - Mg ≤ 2.79, preferably 2.06 ≤ 0.9W / Mo - Mg ≤ 2.71, where W, Mo, and Mg are the values after removing the percentage signs of the mass percentages of elements W, Mo, and Mg in the nickel-based superalloy, that is, W is 13.5-17.5, Mo is 4.7-8.5, and Mg is 0.001-0.07.

[0031] In the embodiments of the present invention, limiting that W, Mo, and Mg satisfy the relationship: 1.82 ≤ 0.9W / Mo - Mg ≤ 2.79 can give full play to the synergistic effect among W, Mo, and Mg, not only improving the high-temperature strength of the nickel-based superalloy, but also enabling the alloy to have better fracture plasticity at high temperatures.

[0032] In some embodiments, preferably, Al, Nd, and Ba satisfy the relational expression 0.68 ≤ Al - 2.5(Nd + Ba) ≤ 2.75, and preferably, 2.35 ≤ Al - 2.5(Nd + Ba) ≤ 2.7, where Al, Nd, and Ba are the values obtained by removing the percentage signs from the mass percentage contents of elements Al, Nd, and Ba in the nickel-based superalloy, that is, Al is 1.0 - 4.0, Nd is 0.1 - 0.5, and Ba is 0.06 - 0.25.

[0033] In the embodiments of the present invention, it is defined that Al, Nd, and Ba satisfy the relational expression 0.68 ≤ Al - 2.5(Nd + Ba) ≤ 2.75, which can give full play to the synergistic effect among Al, Nd, and Ba. It can not only make the alloy have better microstructural stability at 900 - 1000 °C, but also be beneficial to improving the high-temperature performance and thermal shock performance of the alloy.

[0034] In some embodiments, preferably, the low-inclusion and thermal-shock-resistant nickel-based superalloy includes: C: 0.05 - 0.18%, Cr: 4 - 6.5%, Co: 5.0 - 6.3%, W: 14.0 - 16.8%, Al: 1.5 - 4.0%, Ta: 3.0 - 4.0%, Mo: 4.5 - 7.5%, Hf: 1.5 - 2.8%, Ti: 3.0 - 5.0%, B: 0.08 - 0.15%, Zr: 0.08 - 0.25%, Mg: 0.01 - 0.07%, Mn: ≤ 0.40%, Si: ≤ 0.4%, Nd: 0.2 - 0.5%, Ba: 0.1 - 0.25%, and the balance is nickel and inevitable impurities, by weight percentage.

[0035] The embodiments of the present invention also provide an application of the low-inclusion and thermal-shock-resistant nickel-based superalloy in an aeroengine. The low-inclusion and thermal-shock-resistant nickel-based superalloy in the embodiments of the present invention meets the requirements of the design and use of advanced aeroengines and can be applied to the precision equipment of advanced aeroengines.

[0036] The embodiments of the present invention also provide an application of the low-inclusion and thermal-shock-resistant nickel-based superalloy in a gas turbine. The low-inclusion and thermal-shock-resistant nickel-based superalloy in the embodiments of the present invention meets the requirements of the design and use of gas turbines and can be applied to the precision equipment of gas turbines.

[0037] The embodiments of the present invention also provide a preparation method of a low-inclusion and thermal-shock-resistant nickel-based superalloy, which is characterized by including the following steps:

[0038] (1) Conduct vacuum smelting according to the raw material ratio;

[0039] (2) Adjust the casting temperature and cast into a billet;

[0040] (3) Heat-treat the ingot prepared in step (2).

[0041] The preparation method of the low-inclusion and heat-shock-resistant nickel-based superalloy according to the embodiments of the present invention results in a nickel-based superalloy with few inclusions, excellent high-temperature properties and heat-shock properties, good casting performance, and no defects such as shrinkage cavities and hot cracks, meeting the requirements for the design and use of advanced aeroengines and gas turbines; the process is simple, reducing energy consumption, shortening the production cycle, and improving production efficiency, making it suitable for industrial production and popularization.

[0042] In some embodiments, preferably, in step (1), the smelting temperature is 1210 - 1320 °C.

[0043] In some embodiments, preferably, in step (2), the casting temperature is 1000 - 1190 °C.

[0044] In some embodiments, preferably, in step (3), the heat-treatment temperature is 850 - 1170 °C, and the heat-treatment time is 18 - 28 h.

[0045] In the embodiments of the present invention, the process parameters of the heat treatment are optimized, which is beneficial to obtaining a nickel-based superalloy with good comprehensive properties and better meeting the usage requirements of the existing industry for nickel-based alloys.

[0046] Example 1

[0047] (1) Conduct vacuum smelting according to the raw material ratio, with a smelting temperature of 1220 °C;

[0048] (2) Adjust the casting temperature to 1100 °C and cast it into an ingot;

[0049] (3) Treat the ingot prepared in step (2) at 1120 °C for 18 hours.

[0050] The alloy composition of Example 1 is shown in Table 1, and the performance is shown in Table 2.

[0051] The preparation methods of Examples 2 - 4 are the same as that of Example 1, except for the different alloy compositions. The alloy compositions of Examples 2 - 4 are shown in Table 1, and the performance is shown in Table 2.

[0052] Example 5

[0053] The preparation method of Example 5 is the same as that of Example 1, except for the different alloy compositions, where 0.9W / Mo - Mg = 1.62. The alloy composition of Example 5 is shown in Table 1, and the performance is shown in Table 2.

[0054] Example 6

[0055] Example 6 has the same preparation method as Example 1, except that the alloy composition is different, where Al-2.5(Nd+Ba) = 3.55. The alloy composition of Example 6 is shown in Table 1, and the performance is shown in Table 2.

[0056] Example 7

[0057] Example 7 has the same preparation method as Example 1, except that the alloy composition is different, where 0.9W / Mo-Mg = 3.15 and Al-2.5(Nd+Ba) = 0.25. The alloy composition of Example 7 is shown in Table 1, and the performance is shown in Table 2.

[0058] Comparative Example 1

[0059] Comparative Example 1 has the same preparation method as Example 1. The difference lies in the alloy composition, which does not contain Nd and Ba elements. The alloy composition of Comparative Example 1 is shown in Table 1, and the performance is shown in Table 2.

[0060] Comparative Example 2

[0061] Comparative Example 2 has the same preparation method as Example 1. The difference lies in the alloy composition, which does not contain Nd element. The alloy composition of Comparative Example 2 is shown in Table 1, and the performance is shown in Table 2.

[0062] Comparative Example 3

[0063] Comparative Example 3 has the same preparation method as Example 1. The difference lies in the alloy composition, which does not contain Ba element. The alloy composition of Comparative Example 3 is shown in Table 1, and the performance is shown in Table 2.

[0064] Comparative Example 4

[0065] Comparative Example 4 has the same preparation method as Example 1. The difference lies in the alloy composition, where the Nd content is 0.72% and the Ba content is 0.56%. The alloy composition of Comparative Example 4 is shown in Table 1, and the performance is shown in Table 2.

[0066] Table 1

[0067]

[0068] Table 2

[0069]

[0070]

[0071] Note: Impact energy test method: The ability of the material to resist impact load is measured by a single pendulum impact bending test, that is, the impact energy Ak consumed when the impact load specimen is broken is measured.

[0072] Number of thermal shock cycles: First, place the specimen in the heating device of the testing machine and rapidly heat it to 1050°C at a heating rate of 220°C / s. Then, quickly quench it in water for cooling. After the cooling is completed, the specimen re-enters the electric furnace for heating. This cycle repeats, and record the number of cycles when the specified crack length reaches 4.5 mm.

[0073] Inclusion statistics: Take multiple field-of-view photos of the specimen through a scanning electron microscope and count the inclusions in each field of view.

[0074] As can be seen from the data in Table 1 and Table 2, for the nickel-based superalloys prepared by controlling the content of each element in Examples 1 - 7, the tensile strength of the alloy at 1000°C exceeds 900 MPa, the elongation after fracture is greater than 25.5%, the number of thermal shock fatigue cycles exceeds 3700 times, the impact energy is greater than 24.6 J, and the number of inclusions is between 17.5 - 22.5 per mm 2 , and it has good processing fluidity. Especially when the content of alloying elements satisfies 1.82 ≤ 0.9W / Mo - Mg ≤ 2.79 and 0.68 ≤ Al - 2.5(Nd + Ba) ≤ 2.75, such as in Examples 1 - 4, the prepared nickel-based superalloys have more excellent properties.

[0075] In Comparative Example 1, the alloy does not add Nd and Ba elements, and the grain boundary strengthening and alloy purification effects are significantly weakened. Therefore, the prepared nickel-based superalloy has low high-temperature strength, a large amount of inclusions, and poor thermal shock fatigue resistance, and cannot meet the usage requirements.

[0076] In Comparative Example 2, no Nd element is added. Since the Nd element can exist in the γ / γ′ two phases of the alloy in the form of oxides to play a dispersion strengthening role, and the Nd element can also refine the grains, segregate at the grain boundaries, pin the grain boundaries, and hinder the movement of dislocations, thereby improving the strength and toughness of the alloy. However, in Comparative Example 2, no Nd element is introduced, resulting in an increase in the inclusion content in the prepared nickel-based superalloy to 23 per mm 2 , and the number of thermal shock cycles is only 3675 times, and the tensile strength also decreases to 862 MPa.

[0077] In Comparative Example 3, no Ba element is added. The Ba element can reduce the inclusions in the alloy and make the inclusions float during the smelting process, purify the molten steel, and reduce the fracture caused by inclusions. In Comparative Example 3, due to the absence of Ba, the inclusion content in the prepared nickel-based superalloy increases to 23.9 per mm 2 , and the number of thermal shock cycles is only 3520 times.

[0078] In Comparative Example 4, a relatively large amount of Nd and Ba elements were added. The addition amount of Nd was 0.72%, and the addition amount of Ba was 0.56%. When Nd and Ba were added in combination, they could play a role in alloy strengthening and purification. However, when the content of Nd was too high, a large amount of segregation would occur at the grain boundaries, causing alloy fracture. When the content of Ba was too high, metal compounds distributed in a network along the grain boundaries would appear, increasing the brittleness of the alloy. Since the contents of Nd and Ba in the nickel-based superalloy prepared in Comparative Example 4 were relatively high, the tensile strength of the alloy was only 807 MPa, and there were many inclusions, with a content of 24.5 per mm 2 , and the number of thermal shock cycles was only 3400 times, which could not meet the usage requirements in related fields.

[0079] 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 a suitable manner in any one or more embodiments or examples. 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.

[0080] 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 of 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 low inclusions and resistance to thermal shock, characterized in that, Comprising: C: 0.05 - 0.25%, Cr: 4.0 - 7.5%, Co: 4.5 - 7.0%, W: 13.5 - 17.5%, Al: 1.0 - 4.0%, Ta: 3.0 - 4.5%, Mo: 4.7 - 8.5%, Hf: 1.5 - 2.8%, Ti: 3.0 - 6.0%, B: 0.04 - 0.15%, Zr: 0.06 - 0.25%, Mg: 0.001 - 0.07%, Mn: ≤0.5%, Si: ≤0.5%, Nd: 0.1 - 0.5%, Ba: 0.06 - 0.25%, the balance being nickel and unavoidable impurities, by weight percentage; The W, Mo and Mg satisfy the relationship: 1.82 ≤ 0.9W / Mo - Mg ≤ 2.79, where W, Mo, Mg are the values after removing the percentage sign of the mass percentage of elements W, Mo, Mg in the nickel-based superalloy.

2. The low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 1, wherein The W, Mo and Mg satisfy the relationship: 2.06 ≤ 0.9W / Mo - Mg ≤ 2.

71.

3. The low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 1, characterized in that, The Al, Nd and Ba satisfy the relationship 0.68 ≤ Al - 2.5(Nd + Ba) ≤ 2.75, where Al, Nd, Ba are the values after removing the percentage sign of the mass percentage of elements Al, Nd, Ba in the nickel-based superalloy.

4. The low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 3, characterized in that, The Al, Nd and Ba satisfy the relationship: 2.35 ≤ Al - 2.5(Nd + Ba) ≤ 2.

7.

5. The low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 1, characterized in that, Comprising: C: 0.05 - 0.18%, Cr: 4.0 - 6.5%, Co: 5.0 - 6.3%, W: 14.0 - 16.8%, Al: 1.5 - 4.0%, Ta: 3.0 - 4.0%, Mo: 4.5 - 7.5%, Hf: 1.5 - 2.8%, Ti: 3.0 - 5.0%, B: 0.08 - 0.15%, Zr: 0.08 - 0.25%, Mg: 0.01 - 0.07%, Mn: ≤0.40%, Si: ≤0.4%, Nd: 0.2 - 0.5%, Ba: 0.1 - 0.25%, the balance being nickel and unavoidable impurities, by weight percentage.

6. Application of the low-inclusion and heat-shock-resistant nickel-based superalloy according to any one of claims 1 - 5 in an aeroengine.

7. Application of the low-inclusion and heat-shock-resistant nickel-based superalloy according to any one of claims 1 - 5 in a gas turbine.

8. A method for preparing a low-inclusion and thermal shock-resistant nickel-based superalloy according to any one of claims 1 to 5, characterized in that, Comprising the following steps: (1) Conduct vacuum smelting according to the raw material ratio; (2) Adjust the casting temperature and cast into a billet; (3) Heat-treat the cast billet prepared in step (2).

9. The preparation method of the low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 8, characterized in that, In step (1), the smelting temperature is 1210 - 1320 °C.

10. The preparation method of the low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 8, wherein, In step (2), the casting temperature is 1000 - 1190 °C.

11. The preparation method of the low-inclusion and thermal shock-resistant nickel-based superalloy according to claim 8, characterized in that, In step (3), the heat treatment temperature is 850 - 1170 °C, and the heat treatment time is 18 - 28 h.

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