CN115449669B - Creep-resistant and oxidation-resistant nickel-based superalloy, and preparation method and application thereof - Google Patents

Creep-resistant and oxidation-resistant nickel-based superalloy, and preparation method and application thereof Download PDF

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CN115449669B
CN115449669B CN202211110906.XA CN202211110906A CN115449669B CN 115449669 B CN115449669 B CN 115449669B CN 202211110906 A CN202211110906 A CN 202211110906A CN 115449669 B CN115449669 B CN 115449669B
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resistant
nickel
creep
oxidation
alloy
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CN115449669A (en
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余志勇
李慧威
徐超
文新理
刘伟
李国超
宋丽文
魏然
赵宇辰
安宁
刘西河
王卫丽
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Beijing Beiye Functional Materials Corp
China United Heavy Gas Turbine Technology Co Ltd
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Beijing Beiye Functional Materials Corp
China United Heavy Gas Turbine Technology Co Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/023—Alloys based on nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

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  • Crystallography & Structural Chemistry (AREA)
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Abstract

The invention belongs to the field of metal materials, and particularly relates to a creep-resistant and oxidation-resistant nickel-based superalloy, and a preparation method and application thereof. The invention provides a nickel-based superalloy, which is characterized by comprising the following components: 0.02-0.1%, cr:19.00-23.00%, co:7.50-11.50%, mo:4.50-6.50%, al:1.5-1.8%, ti:1.5-1.9%, nb:0.7-1.5%, pd:0.25-0.65%, B:0.001-0.01%, sc:0.001-0.015%, zr:0-0.05%, W:0-0.05%, and the balance nickel and unavoidable impurities in mass percent. The alloy has excellent creep resistance, long service life and oxidation resistance.

Description

Creep-resistant and oxidation-resistant nickel-based superalloy, and preparation method and application thereof
Technical Field
The invention belongs to the field of metal materials, and particularly relates to a creep-resistant and oxidation-resistant nickel-based superalloy, and a preparation method and application thereof.
Background
The nickel-based superalloy uses nickel as a matrix (the content is generally more than 50%), and has higher strength and good oxidation resistance and gas corrosion resistance in the range of 650-1000 ℃. It is Cr 20 Ni 80 On the basis of the development of the alloy, a large amount of strengthening elements such as W, mo, ti, al, nb, co and the like are added to meet the requirements of high-temperature heat resistance (high-temperature strength, creep resistance and high-temperature fatigue strength) at about 1000 ℃ and oxidation resistance and corrosion resistance in a gas medium so as to ensure the excellent high-temperature performance. In addition to having solid solution strengthening effect, the superalloy is further dependent on AI, ti, etc. to form intermetallic compound gamma' phase with Ni (Ni 3 A1 or Ni 3 Ti, etc.) precipitation strengthening and partial fine stabilization of MC, M 23 C 6 The carbide has the functions of purifying and strengthening grain boundary such as B, zr, re, etc.
Because in the aerospace engine, the working condition is high temperature of 600-1200 ℃, the stress effect is complex, and the requirements on materials are severe; the nickel-based superalloy has high enough heat resistance strength, good plasticity, high-temperature oxidation resistance, gas corrosion resistance and long-term tissue stability, so that the nickel-based superalloy is mainly applied to manufacturing hot end components of turbine engines and various high-temperature components of aerorocket engines.
Disclosure of Invention
The present invention has been made based on the findings and knowledge of the inventors regarding the following facts and problems:
the key hot-end components of modern gas turbine engines require that the nickel-base superalloy have long-term high-temperature structural stability, fatigue resistance, corrosion resistance, oxidation resistance and the like. However, the nickel-based superalloy has obviously reduced mechanical properties such as fatigue strength, yield strength, ultimate tensile strength and the like in the high-temperature long-term service process. With the continuous development of the aerospace industry, the performance requirements of aeroengines are higher and higher, and the high-temperature materials used by the aeroengines need higher temperature bearing capacity, better creep resistance and oxidation resistance.
The present invention aims to solve at least one of the technical problems in the related art to some extent. Therefore, the embodiment of the invention provides the creep-resistant and oxidation-resistant nickel-based superalloy, which has excellent high-temperature durability, creep performance and high-temperature tensile performance and can meet the requirements of aeroengines and gas turbines.
The creep-resistant and oxidation-resistant nickel-based superalloy comprises the following components: 0.02-0.1%, cr:18.00-23.00%, co:7.50-11.50%, mo:4.50-6.50%, al:1.5-1.8%, ti:1.5-1.9%, nb:0.7-1.5%, pd:0.25-0.65%, B:0.001-0.01%, sc:0.001-0.015%, zr:0-0.05%, W:0-0.05%, and the balance nickel and unavoidable impurities in mass percent.
The creep-resistant and oxidation-resistant nickel-based superalloy provided by the embodiment of the invention has the advantages and technical effects that 1, in the embodiment of the invention, mo can be dissolved in an alloy matrix and a gamma' -strengthening phase, and meanwhile, the interatomic bonding force can be improved, the diffusion activation energy and the recrystallization temperature can be improved, so that the high-temperature strength can be effectively improved, but when Mo is too high, the mu phase is easy to generate after long-term high-temperature aging, and the alloy toughness is reduced, so that the content of Mo is controlled within the range of 4.50-6.50%; 2. in the embodiment of the invention, al is a gamma ' phase forming and strengthening element, the content of which can determine the percentage content of the strengthening phase gamma ' of the alloy and the strengthening element thereof, but too much gamma ' can deteriorate the welding performance and damage the processing performance, and the dosage of Al is reduced, so that the cost can be reduced, and the comprehensive performance of the alloy can be maintained at a higher level; 3. in the embodiment of the invention, pd element is introduced, so that the creep resistance and oxidation resistance of the alloy are obviously improved, the high-temperature strength of the alloy is improved, and meanwhile, the plasticity of the alloy is also improved, so that the alloy shows excellent comprehensive mechanical properties; 4. in the embodiment of the invention, the dosages of the components are limited within a proper range, so that the lasting life of the alloy under the conditions of 89MPa and 927 ℃ can reach more than 420h, the creep plastic elongation under the conditions of 816 ℃, 221MPa and 100h is less than 0.2%, the high-temperature tensile yield strength can reach more than 760MPa, the high-temperature tensile strength can reach more than 1110MPa, and the requirements of design and use of advanced aeroengines and gas turbines can be met.
In some embodiments, the Mo, al and Pd satisfy the relationship 3.2< Mo-0.45Al/Pd <4.6, wherein Mo is 4.50-6.50, al is 1.5-1.8, pd is 0.25-0.65, wherein the element values are calculated as their mass percent content minus the percentage number.
In some embodiments, the Mo, al, and Pd satisfy the relationship 3.73< Mo-0.45Al/Pd <4.32.
In some embodiments, the mass fraction of Pd in the nickel-base superalloy is 0.32-0.63%.
In some embodiments, the nickel-base superalloy comprises C:0.03-0.1%, cr:20.12-21.17%, co:9.50-11%, mo:5.2-6.12%, al:1.52-1.70%, ti:1.65-1.85%, nb:0.78-1.20%, pd:0.25-0.65%, B:0.006-0.008%, sc:0.001-0.008%, zr:0.02-0.032%, W:0.01-0.02%, and the balance nickel and unavoidable impurities, based on mass percent.
The embodiment of the invention also provides application of the creep-resistant and oxidation-resistant nickel-based superalloy in an aeroengine.
The embodiment of the invention also provides an application of the creep-resistant and oxidation-resistant nickel-based superalloy in a gas turbine.
The embodiment of the invention also provides application of the creep-resistant and oxidation-resistant nickel-based superalloy in rocket engines.
The embodiment of the invention also provides a preparation method of the creep-resistant and oxidation-resistant nickel-based superalloy, which comprises the following steps:
(1) Smelting according to the raw material proportion, wherein the refining temperature is 1500-1630 ℃;
(2) Regulating the casting temperature to 1450-1580 ℃ and casting into a blank;
(3) And (3) carrying out homogenizing annealing treatment on the casting blank prepared in the step (2).
The preparation method of the creep-resistant and oxidation-resistant nickel-based superalloy provided by the embodiment of the invention has the advantages and technical effects that 1, in the embodiment of the invention, the alloy prepared by the method has good creep resistance, long lasting life and oxidation resistance, and can meet the design and use requirements of an advanced aeroengine and a gas turbine; 2. in the embodiment of the invention, the preparation method is simple and easy to operate, saves energy consumption, has higher production efficiency, and is suitable for industrial popularization and application.
In some embodiments, in step (3), the solution treatment is performed at 1100-1200 ℃ for 40-60 hours, and then cooled to room temperature.
Detailed Description
Embodiments of the present invention are described in detail below. The following examples are illustrative and are intended to be illustrative of the invention and are not to be construed as limiting the invention.
The creep-resistant and oxidation-resistant nickel-based superalloy comprises the following components: 0.02-0.1%, cr:19.0018.00-23.00%, co:7.50-11.50%, mo:4.50-6.50%, al:1.5-1.8%, ti:1.5-1.9%, nb:0.7-1.5%, pd:0.25-0.65%, B:0.001-0.01%, sc:0.001-0.015%, zr:0-0.05%, W:0-0.05%, and the balance nickel and unavoidable impurities in mass percent.
According to the creep-resistant and oxidation-resistant nickel-based superalloy provided by the embodiment of the invention, mo can be dissolved in the alloy matrix and gamma' -strengthening phase, and meanwhile, the interatomic binding force and the diffusion activation energy and the recrystallization temperature can be improved, so that the high-temperature strength is effectively improved, but when Mo is too high, the mu phase is easily generated after long-term high-temperature aging, so that the alloy toughness is reduced, and the content of Mo is controlled within the range of 4.50-6.50%; al is a gamma ' -phase forming and strengthening element, the content of which can determine the percentage content of the strengthening phase gamma ' -of the alloy and the strengthening element thereof, but too much gamma ' -can deteriorate the welding performance and damage the processing performance, and the use level of Al is reduced, so that the cost can be reduced, and the comprehensive performance of the alloy can be maintained at a higher level; in the embodiment of the invention, pd element is introduced, so that the creep resistance and oxidation resistance of the alloy are obviously improved, the high-temperature strength of the alloy is improved, and meanwhile, the plasticity of the alloy is also improved, so that the alloy shows excellent comprehensive mechanical properties; in the embodiment of the invention, the dosages of the components are limited within a proper range, so that the lasting life of the alloy under the conditions of 89MPa and 927 ℃ can reach more than 420h, the creep plastic elongation under the conditions of 816 ℃, 221MPa and 100h is less than 0.2%, the high-temperature tensile yield strength can reach more than 760MPa, the high-temperature tensile strength can reach more than 1110MPa, and the requirements of design and use of advanced aeroengines and gas turbines can be met.
The nickel-based superalloy of the embodiment of the invention has the following elements:
mo: unlike W, the atoms of Mo are mostly dissolved in the gamma matrix, accounting for about 1/4 of the gamma' phase, and the atoms of Mo are larger than the atoms of Ni, co and Fe by 9-12%. Mo obviously increases the lattice constant of Ni solid solution and obviously improves the yield strength at room temperature and high temperature. Mo addition also forms a large amount of M 6 The C carbide is finely dispersed and can play a role in strengthening. Mo may also refine austenite grains. However, excessive addition of Mo promotes the formation of mu-phase, which is disadvantageous for long-term structural stability and reduces the long-lasting life of the nickel-base superalloy, so that the content of Mo is controlled within the range of 4.50-6.50%.
The main purpose of adding Al in the nickel-based superalloy is to form a gamma' strengthening phase under proper heat treatment conditions, so that the room temperature and high temperature strength, the lasting life and the creep resistance of the alloy are improved, and the effect is better when Ti is added. The other function of Al is to improve the oxidation resistance of the alloy, and Al can form a compact oxide film under the high temperature condition to prevent oxygen from further diffusing into the matrix.
Pd is a platinum group element, and has the characteristics of high temperature resistance, high melting point, excellent chemical stability and corrosion resistance like other platinum group elements. High temperature resistant materials composed of Pd and other noble metals are widely applied in the fields of aerospace and the like, but no report on the addition of Pd in nickel-based superalloy is available. Through researches, the creep resistance and oxidation resistance of the alloy can be obviously improved by adding Pd into the nickel-based superalloy, the high-temperature strength of the alloy is improved, the plasticity is also improved, and the alloy is endowed with excellent comprehensive mechanical properties, but when the Pd content is higher than 0.65%, the high-temperature elongation is reduced, so that the Pd content is controlled within the range of 0.25-0.65%, preferably 0.32-0.63%.
In some embodiments, preferably, the Mo, al and Pd satisfy the relation 3.2< Mo-0.45Al/Pd <4.6, where the values of Mo, al and Pd refer to the values of Mo, al and Pd with mass percentages removed, specifically: mo is 4.50-6.50, al is 1.5-1.8, pd is 0.25-0.65, more preferably 3.73< Mo-0.45Al/Pd <4.32, still more preferably Mo is 5.2-6.12, al is 1.52-1.70, pd is 0.32-0.63.
In the embodiment of the invention, the Mo, al and Pd are further preferable to satisfy the relation 3.2<Mo-0.45Al/Pd<4.6, the synergistic effect of Mo, al and Pd can be maximized, the lasting life under the conditions of 89MPa and 927 ℃ can reach more than 450h, and the average oxidation speed can be reduced to 0.002g/m 2 And the alloy has higher high-temperature tensile yield strength and high-temperature tensile strength, achieves the best comprehensive performance level, and can meet the design and use requirements of advanced aeroengines, gas turbines and rockets.
In some embodiments, preferably, the nickel-base superalloy comprises C:0.03-0.1%, cr:20.12-21.17%, co:9.50-11%, mo:5.2-6.12%, al:1.52-1.70%, ti:1.65-1.85%, nb:0.78-1.20%, pd:0.25-0.65%, B:0.006-0.008%, sc:0.001-0.008%, zr:0.02-0.032%, W:0.01-0.02%, and the balance nickel and unavoidable impurities, based on mass percent.
The embodiment of the invention also provides application of the creep-resistant and oxidation-resistant nickel-based superalloy in an aeroengine. The nickel-based superalloy in the embodiment of the invention meets the design and use requirements of an advanced aeroengine and can be applied to precision equipment of the advanced aeroengine.
The embodiment of the invention also provides an application of the creep-resistant and oxidation-resistant nickel-based superalloy in a gas turbine. The nickel-based superalloy in the embodiment of the invention meets the design and use requirements of the gas turbine, and can be applied to precise equipment of the gas turbine.
The embodiment of the invention also provides application of the creep-resistant and oxidation-resistant nickel-based superalloy in rocket engines. The nickel-based superalloy in the embodiment of the invention meets the requirements of rocket design and use, and can be applied to rocket engines.
The embodiment of the invention also provides a preparation method of the creep-resistant and oxidation-resistant nickel-based superalloy, which comprises the following steps:
(1) Smelting according to the raw material proportion, wherein the smelting temperature is 1500-1630 ℃;
(2) Regulating the casting temperature to 1450-1580 ℃ and casting into a blank;
(3) And (3) carrying out homogenizing annealing treatment on the casting blank prepared in the step (2).
According to the preparation method of the creep-resistant and oxidation-resistant nickel-based superalloy, the prepared alloy has good creep resistance, long service life and oxidation resistance, and can meet the design and use requirements of an advanced aeroengine and a gas turbine; the preparation method is simple and easy to operate, saves energy consumption, has higher production efficiency, and is suitable for industrial popularization and application.
In some embodiments, preferably, in step (3), the homogenizing annealing treatment is performed at 1100-1200 ℃ for 40-60 hours, and then cooled to room temperature.
In the embodiment of the invention, the technological parameters of solution treatment and aging treatment are optimized, which is favorable for obtaining the nickel-based superalloy with good comprehensive performance and can meet the use requirement of the existing industry on the nickel-based alloy.
The present invention will be described in detail with reference to examples.
Example 1
(1) Smelting according to the proportion of raw materials, wherein the smelting temperature is 1500 ℃;
(2) Regulating the casting temperature to 1400 ℃, and casting into a blank;
(3) And (3) carrying out diffusion annealing treatment on the casting blank prepared in the step (2), wherein the diffusion annealing treatment is carried out at 1150 ℃ for 40 hours, and then cooling to room temperature.
The alloy composition obtained in example 1 is shown in Table 1 and the properties are shown in Table 2.
Examples 2 to 6 were prepared in the same manner as in example 1, except that the alloy compositions were different, and the alloy compositions obtained in examples 2 to 6 were shown in Table 1, and the properties were shown in Table 2.
Example 7
Example 7 was prepared in the same manner as in example 1 except that the alloy composition was different in that Mo-0.45 Al/pd=2.70, and the alloy composition obtained in example 7 was shown in table 1 and the properties were shown in table 2.
Example 8
Example 8 was prepared in the same manner as in example 1 except that the alloy composition was different in that Mo-0.45 Al/pd=4.91, and the alloy composition obtained in example 8 was shown in table 1 and the properties were shown in table 2.
Comparative example 1
Comparative example 1 was the same as the preparation method of example 1, except that the content of elemental Mo in the alloy composition was 3.22%, and the alloy composition obtained in comparative example 1 was shown in table 1, and the properties were shown in table 2.
Comparative example 2
Comparative example 2 was the same as the preparation method of example 1, except that the content of elemental Mo in the alloy composition was 3.25%, and the alloy composition obtained in comparative example 2 was shown in table 1, and the properties were shown in table 2.
Comparative example 3
Comparative example 3 was the same as the preparation method of example 1, except that the content of elemental Mo in the alloy composition was 7.52%, and the alloy composition obtained in comparative example 3 was shown in table 1, and the properties were shown in table 2.
Comparative example 4
Comparative example 4 was the same as the preparation method of example 1, except that the content of elemental Mo in the alloy composition was 8.30%, and the alloy composition obtained in comparative example 4 was shown in table 1, and the properties were shown in table 2.
Comparative example 5
Comparative example 5 was the same as the preparation method of example 1, except that the content of elemental Pd in the alloy composition was 0.22%, and the alloy composition obtained in comparative example 7 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 6
Comparative example 6 was the same as the preparation method of example 1, except that the content of elemental Pd in the alloy composition was 0.23%, and the alloy composition obtained in comparative example 7 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 7
Comparative example 7 was the same as the production method of example 1, except that the content of elemental Pd in the alloy composition was 0.68%, and the alloy composition obtained in comparative example 7 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 8
Comparative example 8 was the same as the production method of example 1, except that the content of elemental Pd in the alloy composition was 0.75%, and the alloy composition obtained in comparative example 8 was shown in Table 1, and the properties were shown in Table 2.
TABLE 1
Note that: the contents of the elements in the table are in wt%; mn and Si content less than 0.50%.
TABLE 2
Note that: 1. epsilon p The creep plastic elongation of the alloy in an ageing state is that under the conditions of 816 ℃, 221MPa and 100 h;
2.τ is the lasting life of the aging state alloy at 89MPa and 927 ℃, and δ is the lasting elongation after breaking of the aging state alloy at 89MPa and 927 ℃;
3、R p0.2 816 ℃ high temperature tensile yield strength and R of ageing alloy m The high-temperature tensile strength of the aging alloy at 816 ℃ is obtained, and A is the elongation after the aging alloy is stretched at 816 ℃ at high temperature;
4. the Mo-0.45Al/Pd in the table is calculated by the numerical value obtained by removing the percentage numbers of the mass percentages of Mo, al and Pd.
As can be seen from tables 1 and 2, the embodiments are provided with the respective elementsThe prepared alloy has a durable service life of more than 410h at 89MPa and 927 ℃, a creep plastic elongation of less than 0.2% at 816 ℃, 221MPa and 100h, a high-temperature tensile yield strength of more than 567MPa, a high-temperature tensile strength of more than 692MPa basically, and an average oxidation rate of less than 0.004g/m 2 H. Therefore, the alloy prepared by the method has good creep resistance, long service life and oxidation resistance, and can meet the design and use requirements of advanced aeroengines and gas turbines. In particular, when Pd is added to the alloy and Mo, al and Pd satisfy the relation 3.2<Mo-0.45Al/Pd<4.6, the alloys prepared as in examples 1-6 have better overall properties.
Comparative examples 1 to 4, in which the content of elemental Mo was adjusted, the content of elemental Mo in comparative examples 1 and 2 was low, and the durability life and creep properties of the resulting alloy were remarkably reduced, and also resulted in a durable elongation delta and a high-temperature tensile strength R p0.2 Lower than the former; comparative examples 3 and 4, the content of elemental Mo was higher, the durability life and the durability elongation δ of the prepared alloy were significantly reduced, and the high temperature elongation was lower.
Comparative examples 5 to 8 were adjusted for the content of elemental Pd, and comparative examples 5 and 6 were lower in the content of elemental Pd, resulting in serious deterioration of the long-life of the alloy, lower in the long-life elongation, high-temperature tensile strength, high-temperature tensile elongation, and significant deterioration of creep resistance and oxidation resistance. The content of the element Pd in the comparative examples 7 and 8 is higher, the durability life of the prepared alloy is reduced, particularly, the durability life of the alloy is obviously reduced due to the fact that more Pd elements are added in the comparative example 8, and meanwhile, the durability elongation delta and the high-temperature tensile elongation A of the alloy are lower due to the fact that more Pd elements are added.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.

Claims (9)

1. A creep-resistant, oxidation-resistant nickel-base superalloy comprising C:0.02-0.1%, cr:18.00-23.00%, co:7.50-11.50%, mo:4.50-6.50%, al:1.5-1.8%, ti:1.5-1.9%, nb:0.7-1.5%, pd:0.25-0.65%, B:0.001-0.01%, sc:0.001-0.015%, zr:0-0.05%, W:0-0.05%, the balance nickel and unavoidable impurities, based on mass percent,
wherein Mo, al and Pd satisfy the relation of 3.2< Mo-0.45Al/Pd <4.6, mo is 4.50-6.50, al is 1.5-1.8, pd is 0.25-0.65, and the numerical values of the elements are calculated according to the numerical values obtained by removing percentage numbers from the mass percentage content.
2. The creep-resistant, oxidation-resistant nickel-base superalloy according to claim 1, wherein Mo, al and Pd satisfy the relation 3.73< Mo-0.45Al/Pd <4.32.
3. Creep-resistant and oxidation-resistant nickel-base superalloy according to claim 1 or 2, characterised in that the mass fraction of Pd in the nickel-base superalloy is 0.32-0.63%.
4. The creep-resistant, oxidation-resistant nickel-base superalloy of claim 1, wherein the nickel-base superalloy comprises C:0.03-0.1%, cr:20.12-21.17%, co:9.50-11%, mo:5.2-6.12%, al:1.52-1.70%, ti:1.65-1.85%, nb:0.78-1.20%, pd:0.25-0.65%, B:0.006-0.008%, sc:0.001-0.008%, zr:0.02-0.032%, W:0.01-0.02%, and the balance nickel and unavoidable impurities, based on mass percent.
5. Use of the creep-resistant, oxidation-resistant nickel-base superalloy as claimed in any of claims 1-4 in an aircraft engine.
6. Use of the creep-resistant, oxidation-resistant nickel-base superalloy as claimed in any of claims 1-4 in a gas turbine.
7. Use of the creep-resistant, oxidation-resistant nickel-base superalloy of any of claims 1-4 in a rocket engine.
8. A method of preparing a creep-resistant, oxidation-resistant nickel-base superalloy as claimed in any of claims 1 to 4, comprising the steps of:
(1) Smelting according to the raw material proportion, wherein the refining temperature is 1500-1630 ℃;
(2) Regulating the casting temperature to 1450-1580 ℃ and casting into a blank;
(3) And (3) carrying out homogenizing annealing treatment on the casting blank prepared in the step (2).
9. The method of producing a nickel-base superalloy according to claim 8, wherein in step (3), the homogenizing annealing is performed at 1100-1200 ℃ for 40-60 hours, and then cooled to room temperature.
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Citations (6)

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