CN116463526A - High-strength long-life hit entropy high-temperature alloy and preparation method and application thereof - Google Patents
High-strength long-life hit entropy high-temperature alloy and preparation method and application thereof Download PDFInfo
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 106
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- 238000002360 preparation method Methods 0.000 title abstract description 13
- 239000012535 impurity Substances 0.000 claims abstract description 9
- 239000002994 raw material Substances 0.000 claims description 36
- 229910000601 superalloy Inorganic materials 0.000 claims description 33
- 239000000203 mixture Substances 0.000 claims description 22
- 238000010438 heat treatment Methods 0.000 claims description 20
- 238000005098 hot rolling Methods 0.000 claims description 9
- 238000005097 cold rolling Methods 0.000 claims description 8
- 238000007670 refining Methods 0.000 claims description 8
- 230000032683 aging Effects 0.000 claims description 6
- 229910052726 zirconium Inorganic materials 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 5
- 238000002156 mixing Methods 0.000 claims description 5
- 238000000137 annealing Methods 0.000 claims description 4
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 238000009966 trimming Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 3
- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 230000007774 longterm Effects 0.000 abstract description 10
- 238000012545 processing Methods 0.000 abstract description 3
- 230000007797 corrosion Effects 0.000 abstract description 2
- 238000005260 corrosion Methods 0.000 abstract description 2
- 230000003647 oxidation Effects 0.000 abstract 1
- 238000007254 oxidation reaction Methods 0.000 abstract 1
- 230000000052 comparative effect Effects 0.000 description 26
- 238000005728 strengthening Methods 0.000 description 21
- 230000000694 effects Effects 0.000 description 15
- 229910052721 tungsten Inorganic materials 0.000 description 14
- 239000006104 solid solution Substances 0.000 description 10
- 229910052715 tantalum Inorganic materials 0.000 description 10
- 238000013461 design Methods 0.000 description 7
- 238000005242 forging Methods 0.000 description 6
- 229910052758 niobium Inorganic materials 0.000 description 6
- 238000001556 precipitation Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000002045 lasting effect Effects 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000004220 aggregation Methods 0.000 description 2
- 230000002776 aggregation Effects 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000003009 desulfurizing effect Effects 0.000 description 2
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- 230000018109 developmental process Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
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- 229910052748 manganese Inorganic materials 0.000 description 2
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- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 239000002105 nanoparticle Substances 0.000 description 2
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- 230000035945 sensitivity Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000005275 alloying Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- 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 embodiment of the invention discloses a high-strength long-life hit entropy high-temperature alloy and a preparation method and application thereof. The medium-entropy high-temperature alloy comprises the following components in percentage by weight: c:0.01 to 0.09 percent, cr:26.5 to 29.0 percent, co:33.2 to 35.5 percent of Al:1.1 to 2.8 percent of Ti:2.3 to 3.5 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc:0 to 0.01 percent, and the balance of Ni and unavoidable impurities. The alloy not only has high-temperature strength, good oxidation resistance and corrosion resistance, but also has good long-term tissue stability and long-term service life, and good processing formability, and meets the use requirements of hot-end components of aeroengines and gas turbines.
Description
Technical Field
The embodiment of the invention relates to the technical field of metallurgy, in particular to a high-strength long-life hit entropy high-temperature alloy and a preparation method and application thereof.
Background
CoCrFeMnNi is one of the most widely studied high-entropy alloys at present, is formed by mixing five elements of Co, cr, fe, ni and Mn in equal molar ratio, and has an FCC face-centered cubic structure; the high-entropy alloy exhibits very strong high-temperature strength and plasticity, and in addition, the alloy has 200 MPa-m when the temperature is reduced from room temperature to 196 ℃ below zero 1/2 The fracture toughness value is increased from 763MPa to 1280MPa, and the elongation is increased from 50% to 70%. Although the CoCrFeMnNi high-entropy alloy has better toughness at low temperature, the common toughness is poor in matching, for example, the FeCoNiCrMn high-entropy alloy can be stretched and shaped to 60 percent, but the tensile strength is lower than 500MPa, and for these reasons, the development and engineering application of the high-entropy alloy are limited.
At present, the removal of Mn and Fe elements in the CoCrFeMnNi high-entropy alloy is studied, and the rest CrCoNi equimolar ratio mid-entropy alloy is still a single-phase solid solution with an FCC structure. Meanwhile, compared with the pentabasic CoCrFeMnNi high-entropy alloy, the ternary CrCoNi medium-entropy alloy has higher fracture toughness. Ternary mid-entropy alloys have therefore become a hotspot for development applications and research in recent two years.
The CrCoNi medium entropy alloy is a single face-centered cubic (FCC) solid solution, and has more excellent strength and plasticity than FeCoNiCrMn high entropy alloy. However, the strength of the medium entropy alloy is still low at present, and further optimization is needed. The alloy component is common elements in high-temperature alloys such as Cr, co, ni and the like, can be used as a matrix of the high-temperature alloys, and can be used for preparing high-strength long-life hit entropy high-temperature alloys with the characteristics of the high-temperature alloys and the medium-entropy alloys by adding other alloying elements and controlling the preparation process on the basis of the high-temperature alloys, so that the problem that the high-strength long-life hit entropy high-temperature alloys are required to be solved in engineering is promoted.
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 medium-entropy superalloy is an alloy which consists of 3 main elements, wherein the constituent elements have equal or approximately equal atomic ratios, and the alloy has the characteristics of higher strength, good durability, corrosion resistance, good long-term tissue stability and the like at the temperature of more than 600 ℃. Although the room temperature performance of the existing medium-entropy superalloy is better, as the high temperature resistant requirement of each industry on the high temperature resistant alloy is higher and higher, the medium-entropy superalloy in the prior art cannot meet the use requirement, and the high-strength long-life hit entropy superalloy with higher temperature resistance needs to be prepared to meet the use requirement. Therefore, the invention provides the high-strength long-life hit entropy high-temperature alloy and the preparation method and the application thereof, and solves the technical problems of insufficient high-temperature strength, unstable long-term structure, poor lasting life and the like of the conventional medium entropy alloy.
The invention provides a high-strength long-life hit entropy superalloy, which comprises the following components in percentage by weight: c:0.01 to 0.09 percent, cr:26.5 to 29.0 percent, co:33.2 to 35.5 percent of Al:1.1 to 2.8 percent of Ti:2.3 to 3.5 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc:0 to 0.01 percent, and the balance of Ni and unavoidable impurities.
The high-strength long-life hit entropy superalloy provided by the embodiment of the invention has the advantages and technical effects that:
1. in the embodiment of the invention, cr, co and Ni are added in an equimolar atomic percentage, so that a higher entropy value is maintained, and a strong solid solution strengthening effect is achieved; in addition, by adding two gamma 'phase forming elements of Al and Ti, the alloy has a precipitation strengthening effect on the nano gamma' phase which exists stably at 850-900 ℃, and by reasonably matching C, B and Zr grain boundary strengthening elements, the high-temperature plasticity and long-term lasting life of the alloy are obviously improved.
2. In the embodiment of the invention, nb is added, and Nb is not only a solid solution strengthening element, but also a gamma 'strengthening phase forming element in the medium-entropy high-temperature alloy, and the quantity of gamma' is increased along with the increase of the Nb content, so that the high-temperature strength and the durability are improved. However, too much γ' deteriorates the weldability and damages the workability, in addition, nb is combined with C to form MC type carbide, which hinders the grain boundary growth and grain boundary sliding at high temperature, thereby improving the high temperature mechanical properties, but Nb forms large grain MC type carbide at the same time, which is disadvantageous to the mechanical properties of the alloy, in addition, too much Nb damages the weldability, so that the strain age cracking sensitivity of the alloy is enhanced, which is manifested as easily occurring weld crack defects, and the effect of Nb is comprehensively considered, and 0.6 to 1.8% Nb is added in the embodiment of the present invention.
3. In the embodiment of the invention, W, mo and Ta elements are not added, W, mo and Ta mainly play a solid solution strengthening role in the alloy, but W, mo and Ta form harmful brittle TCP phases such as a eta phase, a mu phase, a delta phase and the like when in long-term service, so that the strength and the toughness of the alloy are reduced. Furthermore, the density of W, mo and Ta is relatively high, such as W is as high as 19.25g/cm 3 Considering that the alloy in the embodiment of the invention is mainly used on aeroengines and gas turbines, the lighter the required material is, the better the lighter the material is, therefore, W, mo and Ta elements are not added in the alloy in the embodiment of the invention.
4. In the embodiment of the invention, the medium-entropy high-temperature alloy has a wider hot working window of 300-340 ℃, less surface cracks, good plasticity and high yield in the alloy forging process. By controlling the content of Al, ti and Nb elements, the alloy is ensured to have good processing performance while fully playing a role in ageing strengthening, and gamma' phase is controlled to be dispersed and distributed in nano particles and stably exist at a high temperature of 850-900 ℃.
5. In the embodiment of the invention, sc element is added, sc has strong deoxidizing and desulfurizing capabilities, can purify molten steel, delay carbide precipitation and aggregation growth along a grain boundary, can also block the formation and expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements at the grain boundary so as to strengthen the grain boundary, thereby playing the role of improving the high-temperature durable service life and creep resistance of the alloy. Therefore, the embodiment of the invention controls the content of Sc to be in the range of 0-0.01%.
6. In the embodiment of the invention, the medium-entropy high-temperature alloy has the tensile strength of 420-457 MPa at 900 ℃ and the elongation after break of more than or equal to 20 percent and the density of less than or equal to 8.16g/cm through the solid solution strengthening effect of Cr, co, nb and other elements, the precipitation strengthening effect of Al, ti and Nb elements and the grain boundary strengthening effect of C, B, zr and Sc 3 The service life of the gas turbine engine is longer than 120 hours at 900 ℃ and 40MPa, and the design and use requirements of an advanced aeroengine and the gas turbine engine are met.
In some embodiments, the atomic percent of Cr: co: ni is 1:1:1.
In some embodiments, the weight percent of Sc is 0.001 to 0.01%.
In some embodiments, the weight percentages of Al, ti, nb, sc and Zr satisfy the relationship 0.12 < 0.34 (Nb+Sc+Zr)/(Al+Ti).
In some embodiments, the weight percentages of Al, ti, nb, sc and Zr satisfy the relationship 0.13 < 0.32 (Nb+Sc+Zr)/(Al+Ti).
In some embodiments, the high strength, long life hit entropy superalloy comprises, in weight percent: c:0.01 to 0.09 percent, cr:27.6 to 28.8 percent, co:33.8 to 35.0 percent, al:1.1 to 1.7 percent of Ti:2.3 to 3.2 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc: 0.001-0.01%, and the balance of Ni and unavoidable impurities.
The embodiment of the invention also provides application of the high-strength long-life hit entropy superalloy in an aeroengine.
The embodiment of the invention also provides application of the high-strength long-life hit entropy superalloy in a gas turbine.
The embodiment of the invention also provides a preparation method of the high-strength long-life hit entropy superalloy, which comprises the following steps:
co, ni, cr, nb and part of the raw material C are placed in an environment with the vacuum degree less than or equal to 1.5Pa for mixed heating, and the gas attached to the raw material is discharged;
heating the raw materials to a molten state in an environment with the vacuum degree less than or equal to 0.8Pa, heating to 1560-1680 ℃, refining at a high temperature for 10-25min, and stopping heating to enable the raw materials to be molten into a film;
raising the temperature to break the film of the melting raw material, adding Al, ti, B, zr, sc and the rest of the raw material C, and uniformly mixing;
refining the mixed raw materials added with Al, ti, B, zr, sc and the rest of the raw materials C at 1600-1670 ℃;
pouring the refined raw materials at 1500-1560 ℃ to obtain flat blanks;
finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy strip;
aging the alloy strip at 820-900 ℃ for 10-20 h to form the high-strength long-life hit entropy high-temperature alloy.
The high-strength long-life hit entropy superalloy prepared by the preparation method has excellent high-temperature strength, long-life, long-term tissue stability and no forging, hot rolling and cold rolling crack formation, and meets the design and use requirements of an advanced aeroengine and a gas turbine; 2. in the embodiment of the invention, the alloy has low cost and simple preparation process, reduces energy consumption, shortens the production period, improves the production efficiency, and is suitable for popularization and application in industrial production.
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 high-strength long-life hit entropy high-temperature alloy provided by the embodiment of the invention comprises the following components in percentage by weight: c:0.01 to 0.09 percent, cr:26.5 to 29.0 percent, co:33.2 to 35.5 percent of Al:1.1 to 2.8 percent of Ti:2.3 to 3.5 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc:0 to 0.01 percent, and the balance of Ni and unavoidable impurities.
The high-strength long-life hit entropy superalloy provided by the embodiment of the invention has the advantages and technical effects that:
1. in the embodiment of the invention, cr, co and Ni are added in an equimolar atomic percentage, so that a higher entropy value is maintained, and a strong solid solution strengthening effect is achieved; in addition, by adding two gamma 'phase forming elements of Al and Ti, the alloy has a precipitation strengthening effect on the nano gamma' phase which exists stably at 850-900 ℃, and by reasonably matching C, B and Zr grain boundary strengthening elements, the high-temperature plasticity and long-term lasting life of the alloy are obviously improved.
2. In the embodiment of the invention, nb is added, and Nb is not only a solid solution strengthening element, but also a gamma 'strengthening phase forming element in the medium-entropy high-temperature alloy, and the quantity of gamma' is increased along with the increase of the Nb content, so that the high-temperature strength and the durability are improved. However, too much γ' deteriorates the weldability and damages the workability, in addition, nb is combined with C to form MC type carbide, which hinders the grain boundary growth and grain boundary sliding at high temperature, thereby improving the high temperature mechanical properties, but Nb forms large grain MC type carbide at the same time, which is disadvantageous to the mechanical properties of the alloy, in addition, too much Nb damages the weldability, so that the strain age cracking sensitivity of the alloy is enhanced, which is manifested as easily occurring weld crack defects, and the effect of Nb is comprehensively considered, and 0.6 to 1.8% Nb is added in the embodiment of the present invention.
3. In the embodiment of the invention, W, mo and Ta elements are not added, W, mo and Ta mainly play a solid solution strengthening role in the alloy, but W, mo and Ta form harmful brittle TCP phases such as a eta phase, a mu phase, a delta phase and the like when in long-term service, so that the strength and the toughness of the alloy are reduced. Furthermore, W, mo and TaHigher density, such as W up to 19.25g/cm 3 Considering that the alloy in the embodiment of the invention is mainly used on aeroengines and gas turbines, the lighter the required material is, the better the lighter the material is, therefore, W, mo and Ta elements are not added in the alloy in the embodiment of the invention.
4. In the embodiment of the invention, the medium-entropy high-temperature alloy has a wider hot working window of 300-340 ℃, less surface cracks, good plasticity and high yield in the alloy forging process. By controlling the content of Al, ti and Nb elements, the alloy is ensured to have good processing performance while fully playing a role in ageing strengthening, and gamma' phase is controlled to be dispersed and distributed in nano particles and stably exist at a high temperature of 850-900 ℃.
5. In the embodiment of the invention, sc element is added, sc has strong deoxidizing and desulfurizing capabilities, can purify molten steel, delay carbide precipitation and aggregation growth along a grain boundary, can also block the formation and expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements at the grain boundary so as to strengthen the grain boundary, thereby playing the role of improving the high-temperature durable service life and creep resistance of the alloy. Therefore, the embodiment of the invention controls the content of Sc to be in the range of 0-0.01%.
6. In the embodiment of the invention, the medium-entropy high-temperature alloy has the tensile strength of 420-457 MPa at 900 ℃ and the elongation after break of more than or equal to 20 percent and the density of less than or equal to 8.16g/cm through the solid solution strengthening effect of Cr, co, nb and other elements, the precipitation strengthening effect of Al, ti and Nb elements and the grain boundary strengthening effect of C, B, zr and Sc 3 The service life of the gas turbine engine is longer than 120 hours at 900 ℃ and 40MPa, and the design and use requirements of an advanced aeroengine and the gas turbine engine are met.
In some embodiments, the high strength, long life hit entropy superalloy Cr: co: ni is preferably 1:1:1 atomic percent.
In some embodiments, the high strength, long life hit entropy high temperature Sc is preferably 0.001 to 0.01% by weight.
In some embodiments, preferably, the high strength, long life hit entropy superalloy has a weight percent of Al, ti, nb, and Sc that satisfies the relationship 0.12 < Nb+Sc+Zr)/(Al+Ti) 0.34. Under the relational expression, the synergistic effect of Al, ti, nb and Sc can be exerted to the greatest extent, and the prepared medium-entropy superalloy has more excellent comprehensive performance and can meet the design and use requirements of advanced aeroengines and gas turbines. Further preferably, the weight percentage of Al, ti, nb and Sc satisfies the relation 0.13.ltoreq.Nb+Sc+Zr)/(Al+Ti.ltoreq.0.32.
In the embodiment of the invention, preferably, the high-strength long-life hit entropy superalloy comprises the following components in percentage by weight: c:0.01 to 0.09 percent, cr:27.6 to 28.8 percent, co:33.8 to 35.0 percent, al:1.1 to 1.7 percent of Ti:2.3 to 3.2 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc: 0.001-0.01%, and the balance of Ni and unavoidable impurities.
The embodiment of the invention also provides application of the high-strength long-life hit entropy superalloy in an aeroengine. The high-strength long-life hit entropy superalloy in the embodiment of the invention meets the design and use requirements of an advanced aeroengine, and can be applied to hot end components of the advanced aeroengine.
The embodiment of the invention also provides application of the high-strength long-life hit entropy superalloy in a gas turbine. The high-strength long-life hit entropy superalloy in the embodiment of the invention meets the design and use requirements of an advanced gas turbine, and can be applied to a hot end component of the advanced gas turbine.
The embodiment of the invention also provides a preparation method of the high-strength long-life hit entropy superalloy, which comprises the following steps:
co, ni, cr, nb and part of the raw material C are placed in an environment with the vacuum degree less than or equal to 1.5Pa for mixed heating, and the gas attached to the raw material is discharged;
heating the raw materials to a molten state in an environment with the vacuum degree less than or equal to 0.8Pa, heating to 1560-1680 ℃, refining at a high temperature for 10-25min, and stopping heating to enable the raw materials to be molten into a film;
raising the temperature to break the film of the melting raw material, adding Al, ti, B, zr, sc and the rest of the raw material C, and uniformly mixing;
refining the mixed raw materials added with Al, ti, B, zr, sc and the rest of the raw materials C at 1600-1670 ℃;
pouring the refined raw materials at 1500-1560 ℃ to obtain flat blanks;
finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy strip;
aging the alloy strip at 820-900 ℃ for 10-20 h to form the high-strength long-life hit entropy high-temperature alloy.
The high-strength long-life hit entropy superalloy prepared by the preparation method has excellent high-temperature strength, long-life, long-term tissue stability and no forging, hot rolling and cold rolling crack formation, and meets the design and use requirements of an advanced aeroengine and a gas turbine; 2. in the embodiment of the invention, the alloy has low cost and simple preparation process, reduces energy consumption, shortens the production period, improves the production efficiency, and is suitable for popularization and application in industrial production.
Example 1
(1) Co, ni, cr, nb and part of the raw material C are placed in an environment with the vacuum degree of 1.2Pa for mixed heating, and the gas attached to the raw material is discharged;
(2) Heating the raw materials to a molten state in an environment with the vacuum degree of 0.6Pa, heating to 1560 ℃, refining at a high temperature for 18min, and stopping heating to melt the raw material film;
(3) Raising the temperature to break the film of the melting raw material, adding Al, ti, B, zr, sc and the rest of the raw material C, and uniformly mixing;
(4) Refining the mixed raw material added with Al, ti, B, zr, sc and the rest part of C raw material at 1620 ℃;
(5) Pouring the refined raw materials at 1540 ℃ to obtain flat blanks;
(6) Finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy strip;
(7) Aging the alloy strip for 10 hours at 850 ℃ to form the high-strength long-life hit entropy high-temperature alloy.
The alloy composition obtained in example 1 is shown in Table 1 and the properties are shown in Table 2.
Examples 2 to 8
Examples 2-8 were prepared in the same manner as in example 1, except that the alloy compositions were different, and the alloy compositions obtained in examples 2-8 were shown in Table 1, and the properties were shown in Table 2.
Example 9
Example 9 was prepared in the same manner as in example 1, except that the alloy composition was 0.37 in terms of (Nb+Sc+Zr)/(Al+Ti), and the alloy composition obtained in example 9 was shown in Table 1, and the properties were shown in Table 2.
Example 10
Example 10 was prepared in the same manner as in example 1, except that the alloy composition was 0.11 (Nb+Sc+Zr)/(Al+Ti), and the alloy composition obtained in example 10 was shown in Table 1 and the properties were shown in Table 2.
Example 11
Example 11 was prepared in the same manner as in example 1, except that the alloy composition was varied, wherein the atomic percentage of Cr: co: ni was 1:1:1, and the alloy composition obtained in example 11 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 alloy composition contains W and Mo elements, the alloy composition obtained in comparative example 1 is shown in Table 1, and the properties are shown in Table 2.
Comparative example 2
Comparative example 2 was the same as in example 1 except that the alloy composition contained 1.4% by weight of Ta element, 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 prepared in the same manner as in example 1 except that the alloy composition contained 2.3% by weight of Nb, 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 prepared in the same manner as in example 1 except that the alloy composition contained 0.4% by weight of Nb, and the alloy composition obtained in comparative example 4 was shown in Table 1, and the properties thereof were shown in Table 2.
Comparative example 5
Comparative example 5 was the same as the production method of example 1, except that the content of the element Sc in the alloy composition was 0.19%, and the alloy composition obtained in comparative example 5 was shown in table 1, and the properties were shown in table 2.
Table 1 shows the alloy compositions of examples 1 to 11 and comparative examples 1 to 6.
TABLE 1
Table 2 shows the alloy compositions of examples 1-11 and the properties of the alloys of comparative examples 1-5
TABLE 2
As can be seen from the data in tables 1 and 2, the medium entropy superalloy prepared by the embodiment of the invention by controlling the content of each element has high tensile strength at 900 ℃ which is far higher than 422MPa, high yield strength at 900 ℃ which can be higher than 180MPa, and density which is less than or equal to 8.16g/cm 3 The service life of the alloy is more than or equal to 120 hours at 900 ℃ and 40MPa, and meanwhile, the alloy has better processability, and no crack is generated after forging, hot rolling and cold rolling.
Comparative examples 1 and 2 were alloys in which W, mo and Ta were added, comparative example 1 contained W and Mo elements, and comparative example 2 contained Ta elements due to W, mo and TThe density of the a element is larger, resulting in the density of the alloy being larger than 8.16g/cm 3 The use requirements cannot be met.
Comparative examples 3 and 4 were alloys in which element Nb was added in an amount of 2.3% to comparative example 3 and 0.4% to comparative example 4, and the element Nb improved high temperature mechanical properties to achieve 584MPa for high temperature tensile strength at 900 c of the alloy of comparative example 3, but excessive Nb impaired workability, resulting in crack defects during hot rolling and cold rolling. In comparative example 4, the Nb content is low, the strengthening effect is weak, the high-temperature strength of the alloy is low, only 434MPa is needed, and the use requirement cannot be met.
Comparative example 5 was adjusted to an amount of 0.19% of the element Sc, and when the amount of the element Sc was too large, hot workability was impaired, forging and hot rolling cracks were caused, and large-sized inclusions were formed, resulting in deterioration of the comprehensive properties of the alloy.
While the invention has been described in detail in the foregoing general description and specific examples, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (9)
1. The high-strength long-life hit entropy superalloy is characterized by comprising the following components in percentage by weight: c:0.01 to 0.09 percent, cr:26.5 to 29.0 percent, co:33.2 to 35.5 percent of Al:1.1 to 2.8 percent of Ti:2.3 to 3.5 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc:0 to 0.01 percent, and the balance of Ni and unavoidable impurities.
2. The high strength, long life hit entropy superalloy of claim 1, wherein the atomic percent of Cr, co, and Ni is 1:1:1.
3. The high strength, long life hit entropy superalloy of claim 1, wherein the weight percent of Sc is 0.001-0.01%.
4. The high strength, long life hit entropy superalloy of claim 1, wherein the weight percentages of Al, ti, nb, sc and Zr satisfy the relationship 0.12 +.ltoreq.nb+sc+zr)/(al+ti) +.ltoreq.0.34.
5. The high strength, long life hit entropy superalloy of claim 4, wherein the weight percentages of Al, ti, nb, sc and Zr satisfy the relationship 0.13-0.32 (nb+sc+zr)/(al+ti).
6. The high strength, long life hit entropy superalloy of claim 1, wherein the composition of the medium entropy superalloy, in weight percent: c:0.01 to 0.09 percent, cr:27.6 to 28.8 percent, co:33.8 to 35.0 percent, al:1.1 to 1.7 percent of Ti:2.3 to 3.2 percent, nb:0.6 to 1.8 percent, B: 0.005-0.012%, zr:0.001 to 0.01 percent, sc: 0.001-0.01%, and the balance of Ni and unavoidable impurities.
7. Use of the high strength, long life hit entropy superalloy of any of claims 1 to 6 in an aeroengine.
8. Use of the high strength, long life hit entropy superalloy of any of claims 1 to 6 in a gas turbine.
9. A method of preparing a high strength, long life hit entropy superalloy as claimed in any of claims 1 to 6, comprising the steps of:
co, ni, cr, nb and part of the raw material C are placed in an environment with the vacuum degree less than or equal to 1.5Pa for mixed heating, and the gas attached to the raw material is discharged;
heating the raw materials to a molten state in an environment with the vacuum degree less than or equal to 0.8Pa, heating to 1560-1680 ℃, refining at a high temperature for 10-25min, and stopping heating to enable the raw materials to be molten into a film;
raising the temperature to break the film of the melting raw material, adding Al, ti, B, zr, sc and the rest of the raw material C, and uniformly mixing;
refining the mixed raw materials added with Al, ti, B, zr, sc and the rest of the raw materials C at 1600-1670 ℃;
pouring the refined raw materials at 1500-1560 ℃ to obtain flat blanks;
finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy strip;
aging the alloy strip at 820-900 ℃ for 10-20 h to form the high-strength long-life hit entropy high-temperature alloy.
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