CN115418532B - Nickel-based superalloy with long service life and crack resistance as well as preparation method and application thereof - Google Patents
Nickel-based superalloy with long service life and crack resistance as well as preparation method and application thereof Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- 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%
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- 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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- 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
- C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
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- 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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Abstract
The invention belongs to the technical field of alloys, and particularly relates to a long-life and crack-resistant nickel-based superalloy, and a preparation method and application thereof. The invention provides a nickel-based superalloy, comprising: c:0.01-0.10%, cr:17.00-22.00%, co:8.00-12.00%, mo:3.50-5.00%, al:2.10-2.80%, ti:1.70-2.10%, nb:0.90-1.60%, B:0.004-0.008%, sc:0.001-0.009%, W:0-0.05%, zr:0-0.05%, V:0.10-0.25% and Pd:0.05-0.15%, and the balance nickel and unavoidable impurities, based on mass percent. The alloy not only has better oxidation resistance, long service life and excellent room temperature tensile strength, but also has better plasticity at high temperature and room temperature, does not generate cracks during welding, and is convenient for processing and application.
Description
Technical Field
The invention belongs to the technical field of alloys, and particularly relates to a long-life and crack-resistant nickel-based superalloy, and a preparation method and application thereof.
Background
Superalloys generally have high room temperature and high temperature strength, good oxidation and hot corrosion resistance, excellent creep and fatigue resistance, good structural stability, and reliability in use.
Nickel-base superalloys are particularly important in the entire superalloy field. Compared with iron-based and cobalt-based superalloys, the nickel-based superalloy has higher high-temperature strength and tissue stability, and is widely applied to manufacturing hot end components of aviation jet engines and industrial gas turbines. Modern gas turbine engines use superalloys for more than 50% of the mass of the material, with nickel-base superalloys being used in an amount of about 40% of the engine material. The nickel-based alloy has excellent comprehensive properties at medium and high temperatures, is suitable for long-time working at high temperatures, can resist corrosion and abrasion, and is the most complex alloy which is most widely applied in high-temperature parts and is most interesting for a plurality of metallurgical workers in all superalloys.
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 processes of fuel oil atomization, oil-gas mixing, ignition, combustion and the like are all carried out in a combustion chamber, so that the combustion chamber is the region with the highest temperature in each part of the engine, and when the temperature of fuel gas in the combustion chamber is up to 1500-2000 ℃, the temperature born by the chamber wall alloy can be up to 800-900 ℃ or more, and the local temperature can be up to 1100 ℃. Therefore, the combustion chamber is subjected to smaller mechanical stress, but larger thermal stress, and the requirements on materials are mainly that: high temperature oxidation resistance and gas corrosion resistance; sufficient strength; good cold and hot fatigue performance; good process plasticity (durability, bending properties) and weldability; and long-term structural stability of the alloy at operating temperatures. With the development of technology, the requirements on the wall alloy of the combustion chamber are higher and higher, the conventional Inconel718 and the corresponding substitute alloy cannot meet the requirements, and therefore, new superalloy materials need to be developed.
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 nickel-based superalloy with long service life and crack resistance, which not only has better oxidation resistance, long service life and excellent room-temperature tensile strength, but also has better plasticity at high temperature and room temperature, does not generate cracks during welding, and is convenient for processing and application.
The embodiment of the invention provides a long-life and crack-resistant nickel-based superalloy, which comprises the following components: c:0.01-0.10%, cr:17.00-22.00%, co:8.00-12.00%, mo:3.50-5.00%, al:2.10-2.80%, ti:1.70-2.10%, nb:0.90-1.60%, B:0.004-0.008%, sc:0.001-0.009%, zr:0-0.05%, W:0-0.05%, V:0.10-0.25% and Pd:0.05-0.15%, and the balance nickel and unavoidable impurities, based on mass percent.
The nickel-based superalloy of the embodiment of the invention has the advantages and technical effects that 1, in the embodiment of the invention, the low Mo design is adopted, and the addition of Mo element into the alloy can obviously increase the lattice constant of nickel solid solution and increase the stress field of long Cheng Danxing, thereby increasing the resistance for blocking dislocation movement and reducing the stacking fault energy, further obviously increasing the yield strength of the alloy and promoting M in the alloy 6 The C-type carbide is formed to play a role in strengthening, in addition, mo element enters a gamma 'phase to change the lattice mismatch degree of a matrix and the gamma' phase, and austenite grains can be refined by the Mo element, however, the excessive content of the Mo element can influence the crack resistance sensitivity of the alloy, so that the content of the Mo element is controlled within a range of 3.50-5.00 percent in the embodiment of the invention; 2. in the embodiment of the invention, V element is added, the V element is added into the high-temperature alloy, wherein 70 to 87 percent of the V element is distributed in gamma austenite, and the rest of the V element is distributed in gamma' phase and other precipitated phasesIn the method, as the atomic radius of V is larger than that of Ni atoms, lattice distortion can be generated, the effect of obviously strengthening solid solution is achieved, the yield strength of the alloy is further improved, V can achieve the effect of refining grains, the plasticity of a hot working process of the nickel-based superalloy can be obviously improved, the processing and manufacturing of the alloy are facilitated, secondly, V element is added into the alloy, notch sensitivity of the alloy can be improved, a certain amount of V element can be added, fine VC particles can be formed, the second-phase strengthening effect is achieved, and in addition, part of Al and Ti can be replaced by the V element, and the strength of a middle-low temperature interval of the alloy is improved; 3. in the embodiment of the invention, pd element is added, pd (palladium) is a platinum group element, and like other platinum group elements, pd has the characteristics of high temperature resistance, high melting point, excellent chemical stability and corrosion resistance, and a high temperature resistant material composed of Pd and other noble metals is widely applied in the fields of aerospace and the like, but no relevant report of adding Pd in nickel-based superalloy is yet seen; pd can obviously improve creep resistance and oxidation resistance of the alloy, improves plasticity while improving high-temperature strength of the alloy, and shows excellent comprehensive mechanical properties, but when the Pd content is too high, the high-temperature elongation is reduced instead. Therefore, in the embodiment of the invention, the content of the element Pd is controlled within the range of 0.05-0.15%; 4. in the embodiment of the invention, the contents of the elements are controlled within the designed proportion, the prepared alloy not only has the lasting life of more than 340h under the conditions of 89MPa and 927 ℃, excellent room temperature tensile strength, but also has the creep plastic elongation of less than 0.15 percent under the conditions of 816 ℃, 221MPa and 100h, simultaneously has very good oxidation resistance, and the average oxidation speed can be reduced to 0.07g/m 2 H is less than or equal to the specification, and the strain aging cracking resistance is more than 13 percent, and the welding performance is excellent.
In some embodiments, the V is 0.18-0.22% by mass.
In some embodiments, the Pd is present in an amount of 0.06-0.12% by mass.
In some embodiments, the mass percentages of Pd, V, and B satisfy the relationship 9.5< (v+3.8pd)/5.6b <13.6.
In some embodiments, the mass percentages of Pd, V, and B satisfy the relationship 10.2< (v+3.8pd)/5.6b <13.48.
In some embodiments, the nickel-base superalloy comprises: c:0.02-0.008%, cr:17.22-21.35%, co:8.02-11.24%, mo:3.56-4.96%, al:2.12-2.61%, ti:1.71-2.08%, nb:0.92-1.46%, B:0.006-0.008%, sc:0.001-0.007%, zr:0.001-0.042%, W:0.02-0.04%, V:0.18-0.22% and Pd:0.06-0.12%, and the balance nickel and unavoidable impurities, based on mass percent.
The embodiment of the invention also provides application of the long-life and crack-resistant nickel-based superalloy in an aeroengine.
The embodiment of the invention also provides application of the long-life and crack-resistant nickel-based superalloy in a gas turbine.
The embodiment of the invention also provides a preparation method of the long-life and crack-resistant nickel-based superalloy, which comprises the following steps:
(1) Melting raw materials in a vacuum induction furnace, and vacuum casting to obtain an ingot;
(2) And carrying out heat treatment on the cast ingot in an inert gas protective atmosphere.
The preparation method of the long-life and crack-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 long-life of the alloy prepared by the method under the conditions of 89MPa and 927 ℃ can reach more than 340h, and the average oxidation speed can also reach 0.1g/m 2 The alloy has better oxidation resistance below h, and in addition, the alloy has better room temperature tensile strength, better plasticity at high temperature and room temperature, no crack generation during welding, and is convenient for processing and application; 2. in the embodiment of the invention, the method is simple and easy to operate, saves energy consumption, has higher production efficiency, and is suitable for popularization and application of industrial production.
In some embodiments, in the step (2), the heat treatment is performed by heating to 1200-1250 ℃ for 2-6 hours, and then cooling to 800-900 ℃ for 15-25 hours.
Detailed Description
The following detailed description of embodiments of the invention is exemplary and intended to be illustrative of the invention and not to be construed as limiting the invention.
The embodiment of the invention provides a long-life and crack-resistant nickel-based superalloy, which comprises the following components: c:0.01-0.10%, cr:17.00-22.00%, co:8.00-12.00%, mo:3.50-5.00%, al:2.10-2.80%, ti:1.70-2.10%, nb:0.90-1.60%, B:0.004-0.008%, sc:0.001-0.009%, zr:0-0.05%, W:0-0.05%, V:0.10-0.25% and Pd:0.05-0.15%, and the balance nickel and unavoidable impurities, based on mass percent.
The long-life and crack-resistant nickel-based superalloy provided by the embodiment of the invention adopts a low Mo design, and the addition of Mo element into the alloy can obviously increase the solid solution lattice constant of nickel and increase the long Cheng Danxing stress field, thereby increasing the resistance for blocking dislocation movement and reducing the stacking fault energy, further obviously increasing the yield strength of the alloy, and promoting M in the alloy 6 The C-type carbide is formed to play a role in strengthening, in addition, mo element enters a gamma 'phase to change the lattice mismatch degree of a matrix and the gamma' phase, and austenite grains can be refined by the Mo element, however, the excessive content of the Mo element can influence the crack resistance sensitivity of the alloy, so that the content of the Mo element is controlled within a range of 3.50-5.00 percent in the embodiment of the invention; in the embodiment of the invention, the V element is added into the high-temperature alloy, wherein 70% -87% of the V element is distributed in gamma austenite, the rest of the V element is distributed in gamma' phase and other precipitation phases, as the atomic radius of V is larger than that of Ni atoms, lattice distortion can be generated, the effect of obviously strengthening solid solution is achieved, the yield strength of the alloy is further improved, the V can play a role of refining grains, the hot working process plasticity of the nickel-based superalloy can be obviously improved, the processing and manufacturing of the alloy are facilitated, the notch sensitivity of the alloy can be improved by adding the V element into the alloy, fine VC particles can be formed by adding a certain amount of the V element, the second-phase strengthening effect is achieved, and in addition, the V element can replace a part of Al and Ti, and the strength of the alloy in a middle-low temperature interval is improved; the invention is trueIn the embodiment, pd (palladium) is added, is a platinum group element, has the characteristics of high temperature resistance, high melting point, excellent chemical stability and corrosion resistance like other platinum group elements, and is widely applied to the fields of aerospace and the like, but no relevant report of adding Pd in nickel-based superalloy is available; pd can obviously improve creep resistance and oxidation resistance of the alloy, improves plasticity while improving high-temperature strength of the alloy, and shows excellent comprehensive mechanical properties, but when the Pd content is too high, the high-temperature elongation is reduced instead. Therefore, in the embodiment of the invention, the content of the element Pd is controlled within the range of 0.05-0.15%; in the embodiment of the invention, the prepared alloy has the long-lasting service life of more than 350h under the conditions of 89MPa and 927 ℃ and excellent room-temperature tensile strength, and the creep plastic elongation of less than 0.15 percent under the conditions of 816 ℃, 221MPa and 100h, and has very good oxidation resistance, and the average oxidation speed can be reduced to 0.07g/m by controlling the content of each element in the designed proportion 2 H is less than or equal to the specification, and the strain aging cracking resistance is more than 13 percent, and the welding performance is excellent.
In some embodiments, preferably, the V is 0.18-0.22% by mass and the Pd is 0.06-0.12% by mass.
In some embodiments, preferably, the mass percentages of Pd, V and B satisfy the relationship 9.5< (v+3.8pd)/5.6b <13.6. Further preferably, the mass percentages of Pd, V and B satisfy the relation 10.2< (V+3.8Pd)/5.6B <13.48.
In the embodiment of the invention, the dosages of Pd, V and B are limited to meet the above relation, the synergistic effect among elements can be exerted, the alloy not only has excellent room temperature tensile yield strength and room temperature tensile strength, but also has better plasticity at high temperature and room temperature, the oxidation resistance is very outstanding, and the average oxidation speed can be controlled at 0.067g/m 2 H or less, in addition, the alloy has no crack formation after welding, the alloy achieves the best comprehensive performance level, and can meet advanced aviation engineRequirements for engine and gas turbine design and use.
In some embodiments, preferably, the nickel-base superalloy comprises: c:0.02-0.008%, cr:17.22-21.35%, co:8.02-11.24%, mo:3.56-4.96%, al:2.12-2.61%, ti:1.71-2.08%, nb:0.92-1.46%, B:0.006-0.008%, sc:0.001-0.007%, zr:0.001-0.042%, W:0.02-0.04%, V:0.18-0.22% and Pd:0.06-0.12%, and the balance nickel and unavoidable impurities, based on mass percent.
The embodiment of the invention also provides application of the long-life and crack-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 application of the long-life and crack-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 a preparation method of the long-life and crack-resistant nickel-based superalloy, which comprises the following steps:
(1) Melting raw materials in a vacuum induction furnace, and vacuum casting to obtain an ingot;
(2) And carrying out heat treatment on the cast ingot in an inert gas protective atmosphere.
The long-life and crack-resistant nickel-based superalloy preparation method provided by the embodiment of the invention can ensure that the durability of the prepared alloy can reach more than 340h under the conditions of 89MPa and 927 ℃, and the average oxidation speed can also reach 0.1g/m 2 The alloy has better oxidation resistance below h, and in addition, the alloy has better room temperature tensile strength, better plasticity at high temperature and room temperature, no crack generation during welding, and is convenient for processing and application; the method is simple and easy to operate, saves energy consumption, has higher production efficiency, and is suitable for popularization and application of industrial production.
In some embodiments, preferably, in the step (2), the heat treatment is performed by heating to 1200-1250 ℃ for 2-6 hours, and cooling to 800-900 ℃ for 15-25 hours.
In the embodiment of the invention, the heat treatment process is optimized, and the proper heat treatment process has positive significance for controlling and stabilizing the microstructure of the alloy and improving the high-temperature performance of the alloy
The present invention will be described in detail with reference to examples.
Example 1
(1) Melting raw materials in a vacuum induction furnace, and vacuum casting to obtain an ingot;
(2) And (3) carrying out heat treatment on the cast ingot in an inert gas protective atmosphere, wherein the heat treatment is to heat up to 1200 ℃ for 6 hours, and then cool down to 900 ℃ for 15 hours.
The alloy composition obtained in example 1 is shown in Table 1 and the properties are shown in Table 2.
Examples 2 to 5 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 5 were shown in Table 1, and the properties were shown in Table 2.
Example 6
Example 6 was prepared in the same manner as in example 1, except that the alloy composition was different, (v+3.8pd)/5.6b=7.77, and the alloy composition obtained in example 6 was 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 changed, (v+3.8pd)/5.6b=17.26, and the alloy composition obtained in example 7 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 3.02%, 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 5.85%, 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 the element V in the alloy composition was 0.08%, 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 the element V in the alloy composition was 0.29%, 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 0.16%, and the alloy composition obtained in comparative example 5 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 the element B in the alloy composition was 0.001%, the alloy composition obtained in comparative example 6 was shown in table 1, and the properties were shown in table 2.
Comparative example 7
Comparative example 7 was the same as the preparation method of example 1, except that the content of the element B in the alloy composition was 0.01%, 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 prepared in the same manner as in example 1 except that the alloy composition was different, and the element Pd was not contained, and the alloy composition obtained in comparative example 8 was shown in Table 1, and the properties were shown in Table 2.
Table 1 alloy compositions (wt.%) of comparative and example alloys
Note that: mn and Si content less than 0.50%.
Table 2 alloy properties of examples and comparative examples
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 is room temperature tensile yield strength, R of the aging state alloy m The room-temperature tensile strength of the aging state alloy is that A is the elongation after room-temperature tensile breaking of the aging state alloy;
4. strain age cracking sensitivity (CHRT value): the temperature rising rate of 15 ℃/min is adopted for the solid solution state plate, the plate is immediately stretched to 816 ℃ according to a constant rate, the measured stretching plasticity at different temperatures is taken as the minimum value of the stretching plasticity, namely the strain aging cracking resistance sensitivity (CHRT value) of the alloy, and the larger the value is, the better the strain aging cracking resistance is, and the less easy the cracking is during welding;
5. the average oxidation rate is the oxidation rate per unit area of the alloy at 900 ℃/100h, and a smaller value indicates better oxidation resistance.
As can be seen from the data in tables 1 and 2, the contents of the elements in the alloy are controlled within the designed range of the invention, the prepared alloy has a lasting life of more than 340h under the conditions of 89MPa and 927 ℃ and an average oxidation speed of 0.1g/m 2 H is less than or equal to the sum of the values, and has better oxidation resistance. In addition, the alloy has good room temperature tensile strength, good plasticity at high temperature and room temperature, no crack during welding, and convenient processing and application. In particular, when the mass percentages of Pd, V and B satisfy the relation 9.5<(V+3.8Pd)/5.6B<13.6, the alloy has better overall properties as in examples 1-5.
Comparative examples 1 and 2 have the content of elemental Mo adjusted, and in comparative example 1, the content of elemental Mo is 3.02%, and a lower content of elemental Mo results in a reduction of room temperature tensile yield strength of the alloy to 580MPa, and a reduction of room temperature tensile strength to 995MPa, failing to meet the use requirements; the comparative example 2 has an elemental Mo content of 5.85% and a higher elemental Mo content maintains the strength of the alloy at a higher level, but the strain age cracking resistance (CHRT value) is reduced to 3.50%, and the alloy is susceptible to cracking during welding, which is detrimental to processing applications.
Comparative examples 3 and 4 were adjusted for the content of element V, the content of element V in comparative example 3 was 0.08%, and the lower content of V resulted in a significant reduction in the long-lasting life of the alloy to 186h at 89MPa, 927℃while the creep plastic elongation of the alloy increased to 0.883% at 816℃221MPa, 100h and the creep properties were deteriorated; the content of the element V in the comparative example 4 is 0.29%, the content of V is increased, and although the lasting life of the alloy is improved, the plasticity and the oxidation resistance of the alloy are obviously reduced, and the use requirement cannot be met.
The content of Pd was adjusted in comparative example 5, and the content of Pd in comparative example 5 was 0.16%, and the higher content of Pd element, while keeping the room temperature tensile strength of the alloy at a higher level, was liable to crack during welding, and was unfavorable for production and processing.
The content of the element B is adjusted in comparative examples 6 and 7, the content of the element B in comparative example 6 is 0.001%, the content of the element B is low, the lasting life of the alloy is reduced to 198h under the conditions of 89MPa and 927 ℃, the elongation of the alloy is reduced to 19.5% after room temperature stretching breaking, and the plasticity is poor, so that the use requirement cannot be met; in comparative example 7, the content of element B was 0.010%, and although the durability life of the alloy was improved, the plasticity of the alloy at high temperature and room temperature was still poor, and the use requirement could not be satisfied.
In comparative example 8, no Pd element was added, but although the room temperature tensile strength of the aged alloy could meet the requirements, the creep resistance, the durability life, the plasticity were significantly reduced, and the oxidation resistance was poor.
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 long life, crack resistant nickel base superalloy characterized by comprising, in mass percent: c:0.01-0.10%, cr:17.00-22.00%, co:8.00-12.00%, mo:3.50-4.96%, al:2.10-2.80%, ti:1.70-2.10%, nb:0.90-1.60%, B:0.004-0.008%, sc:0.001-0.009%, zr:0-0.05%, W:0-0.05%, V:0.10-0.25% and Pd:0.05-0.15%, and the balance nickel and unavoidable impurities, wherein the mass percentage of Pd, V and B satisfies the relation 9.5< (V+3.8Pd)/5.6B <13.6.
2. The long life, crack resistant nickel base superalloy of claim 1, wherein the V is 0.18-0.22 mass percent.
3. The long life, crack resistant nickel base superalloy of claim 2, wherein the Pd is present in an amount of 0.06-0.12% by mass.
4. The long life, crack resistant nickel base superalloy of claim 1, wherein the mass percentages of Pd, V and B satisfy the relationship 10.2< (v+3.8pd)/5.6b <13.48.
5. The long life, crack resistant nickel base superalloy of claim 1, wherein the nickel base superalloy comprises: c:0.02-0.08%, cr:17.22-21.35%, co:8.02-11.24%, mo:3.56-4.96%, al:2.12-2.61%, ti:1.71-2.08%, nb:0.92-1.46%, B:0.006-0.008%, sc:0.001-0.007%, zr:0.001-0.042%, W:0.02-0.04%, V:0.18-0.22% and Pd:0.06-0.12%, and the balance nickel and unavoidable impurities, based on mass percent.
6. Use of a long-life, crack-resistant nickel-base superalloy as claimed in any of claims 1 to 5 in an aircraft engine.
7. Use of a long life, crack resistant nickel-base superalloy as claimed in any of claims 1 to 5 in a gas turbine.
8. A method for preparing a long life, crack resistant nickel base superalloy as claimed in any of claims 1 to 5, comprising the steps of:
(1) Melting raw materials in a vacuum induction furnace, and vacuum casting to obtain an ingot;
(2) And carrying out heat treatment on the cast ingot in an inert gas protective atmosphere.
9. The method for producing a long-life, crack-resistant nickel-base superalloy according to claim 8, wherein in step (2), the heat treatment is performed by heating to 1200 to 1250 ℃ for 2 to 6 hours, and then cooling to 800 to 900 ℃ for 15 to 25 hours.
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Citations (4)
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|---|---|---|---|---|
| CN103160710A (en) * | 2012-11-15 | 2013-06-19 | 北京北冶功能材料有限公司 | Nickel base alloy and preparation method thereof |
| CN111448327A (en) * | 2017-07-28 | 2020-07-24 | 奥克斯梅特科技有限公司 | Nickel-based alloy |
| CN112575229A (en) * | 2020-11-19 | 2021-03-30 | 东莞材料基因高等理工研究院 | Long-life high-strength hot-corrosion-resistant nickel-based high-temperature alloy and application thereof |
| CN112575228A (en) * | 2020-11-12 | 2021-03-30 | 中国联合重型燃气轮机技术有限公司 | Creep-resistant long-life nickel-based deformation superalloy and preparation method and application thereof |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103160710A (en) * | 2012-11-15 | 2013-06-19 | 北京北冶功能材料有限公司 | Nickel base alloy and preparation method thereof |
| CN111448327A (en) * | 2017-07-28 | 2020-07-24 | 奥克斯梅特科技有限公司 | Nickel-based alloy |
| CN112575228A (en) * | 2020-11-12 | 2021-03-30 | 中国联合重型燃气轮机技术有限公司 | Creep-resistant long-life nickel-based deformation superalloy and preparation method and application thereof |
| CN112575229A (en) * | 2020-11-19 | 2021-03-30 | 东莞材料基因高等理工研究院 | Long-life high-strength hot-corrosion-resistant nickel-based high-temperature alloy and application thereof |
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