CN115058625A - Double-precipitated-phase-strengthened nickel-based high-temperature alloy for turbine disc and preparation method thereof - Google Patents
Double-precipitated-phase-strengthened nickel-based high-temperature alloy for turbine disc and preparation method thereof Download PDFInfo
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 130
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 71
- 239000000956 alloy Substances 0.000 title claims abstract description 71
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 61
- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 31
- 238000010438 heat treatment Methods 0.000 claims abstract description 22
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 18
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 12
- 239000000126 substance Substances 0.000 claims abstract description 11
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 11
- 238000011282 treatment Methods 0.000 claims description 24
- 230000032683 aging Effects 0.000 claims description 16
- 238000001816 cooling Methods 0.000 claims description 14
- 230000009977 dual effect Effects 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 239000002244 precipitate Substances 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 4
- 238000003723 Smelting Methods 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims 2
- 230000001627 detrimental effect Effects 0.000 claims 1
- 230000003647 oxidation Effects 0.000 abstract description 20
- 238000007254 oxidation reaction Methods 0.000 abstract description 20
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 abstract description 13
- 239000011651 chromium Substances 0.000 description 33
- 239000010955 niobium Substances 0.000 description 15
- 230000007797 corrosion Effects 0.000 description 12
- 238000005260 corrosion Methods 0.000 description 12
- 238000001556 precipitation Methods 0.000 description 9
- 230000009286 beneficial effect Effects 0.000 description 6
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 5
- 230000018109 developmental process Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000011031 large-scale manufacturing process Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- 229910001247 waspaloy Inorganic materials 0.000 description 5
- 239000010941 cobalt Substances 0.000 description 4
- 229910017052 cobalt Inorganic materials 0.000 description 4
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 4
- 238000005265 energy consumption Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000004090 dissolution Methods 0.000 description 3
- 238000005098 hot rolling Methods 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000002441 X-ray diffraction Methods 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000010187 selection method Methods 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 229910052715 tantalum Inorganic materials 0.000 description 2
- BKUKXOMYGPYFJJ-UHFFFAOYSA-N 2-ethylsulfanyl-1h-benzimidazole;hydrobromide Chemical compound Br.C1=CC=C2NC(SCC)=NC2=C1 BKUKXOMYGPYFJJ-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
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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
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
-
- 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
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
-
- 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
Abstract
The invention discloses a double precipitated phase strengthened nickel-based high-temperature alloy for a turbine disc and a preparation method thereof, and belongs to the technical field of high-temperature alloys for nickel-based turbine discs. The nickel-based turbine disk high-temperature alloy comprises the following chemical components in atomic percentage: al: 5.0-6.0 at.%, V: 8.5-13.0 at.%, Nb: 7.5-9.5 at.%, Cr: 10.0-15.0 at.%, and the balance of Ni. Through selection of components and heat treatment, the prepared nickel-based turbine disk superalloy has the advantages that the gamma 'mole fraction is 10.01-23.12 mol%, the gamma' mole fraction is 22.01-28.12 mol%, the harmful phase mole fraction is 0 mol%, the yield strength is high at 1000 ℃, the structure stability is excellent, and the oxidation resistance is good.
Description
Technical Field
The invention belongs to the technical field of high-temperature alloys for nickel-based turbine disks, and relates to a double precipitated phase strengthened nickel-based turbine disk high-temperature alloy and a preparation method thereof.
Background
High temperature materials require materials with a significant ability to maintain their properties at high temperatures, a notable feature being the ability to withstand loads at operating temperatures near their melting points. If the operating temperature is denoted T oper And melting point T m Then define the corresponding temperature τ ═ T oper /T m Then actual application proves that τ is greater than about 0.6. Based on this theory, it was found that nickel (melting point 1455 ℃) works at 1000 ℃ with τ of (1000+273)/(1455+273) to 0.75 in the search for this high temperature material. Therefore, Ni is selected as a material for high temperature environment applications, and a high temperature application alloy of Ni is called a nickel-based superalloy.
Turbine disks are key parts of aircraft engines, are intended to operate in high temperature, high speed, heavy duty and corrosive, oxidizing environments, and are capable of withstanding the sustained effects of high centrifugal, thermal, gas and vibrational loads. With the continuous development of the aerospace industry of China, the development of a high-performance turbine disc becomes an important link for the development of an aero-engine. The development of a new generation of aero-engine is started in the last 90 th century, the new generation of aero-engine requires supersonic cruise capacity, parts such as a gas compressor, a high-pressure turbine and the like need to work for a long time under high temperature/high stress, and the hot service life of the new generation of aero-engine is 20-30 times that of the existing third generation of aero-engine. The development of novel turbine disk high-temperature alloy is an urgent technical problem to be solved in the field of aerospace. Although the prior art has many component selection and preparation methods of turbine disk high-temperature alloy, the component selection and preparation method of the turbine disk high-temperature alloy with high yield strength, high structure stability and high oxidation resistance at the high temperature of 1000 ℃ does not exist.
For example: chinese patent CN113957365A discloses a heat treatment process for casting precipitation-strengthened nickel-based superalloy, wherein the heat treatment mode is complex, the operation difficulty is high, the obtained nickel-based superalloy does not contain γ "phase in the structure, the size of the precipitated phase is large, although the yield strength is high at 760 ℃, the plasticity is poor, the elongation is low, the high temperature performance is poor, and the oxidation resistance is low.
Chinese patent CN110093532A discloses a precipitation strengthening nickel-based high-chromium superalloy and a preparation method thereof, wherein the nickel-based high-chromium superalloy has very high chromium content, also contains a large amount of high-cost cobalt content, can be prepared only by homogenization treatment, hot rolling and heat treatment, and has less precipitated phases, so that the yield strength is lower.
Chinese patent CN101270427A discloses a high-anchoring-base superalloy reinforced by a rich-chromium precipitated phase and a preparation method thereof, wherein the chromium content is very high, a high-density granular rich-chromium alpha-Cr precipitated phase is uniformly distributed in an austenite matrix, and the size of the granular rich-chromium alpha-Cr precipitated phase is 0.1-2 mu m, so that the optimized matching of the structure is realized, and the ductility, toughness and strength of the alloy are ensured. Obviously, the yield strength at 800 ℃ is lower, the tissue stability is poorer, and the overall mechanical property is poorer.
Chinese patent CN114182139A discloses a precipitation strengthening nickel-based superalloy and a preparation method thereof, wherein the precipitation strengthening nickel-based superalloy has low chromium content, poor high-temperature oxidation resistance and hot corrosion resistance, does not contain aluminum, vanadium and niobium, has high density, does not have yield strength at 1000 ℃, but has low structure stability according to estimation.
Disclosure of Invention
The invention aims to solve the technical problems that in the prior art, the addition cost of cobalt which is an alloy element of a plurality of precipitation strengthening nickel-based high-temperature alloys is high, the content of chromium is low, and the activity of chromium in the nickel-based high-temperature alloys is low, so that the alloys have poor anti-hot corrosion effect and high harmful phase content; the heat treatment consumes much energy, is complex to operate and is not beneficial to industrial large-scale production; the alloy has high density, poor stability of high-temperature structure at 1000 ℃, poor oxidation resistance and the like.
The invention provides the following technical scheme:
the nickel-based turbine disk high-temperature alloy strengthened by double precipitated phases comprises the following chemical components in atomic percentage: al: 5.0-6.0 at.%, V: 8.5-13.0 at.%, Nb: 7.5-9.5 at.%, Cr: 10.0-15.0 at.%, and the balance of Ni.
Preferably, the chemical components of the nickel-based turbine disk superalloy are as follows according to atomic percentage: al: 5.0-6.0 at.%, V: 9.0-12.0 at.%, Nb: 8.0-9.0 at.%, Cr: 11.0-13.0 at.%, and the balance Ni.
The chemical composition of the alloy of the invention is designed mainly based on the following reasons:
in the high-temperature alloy except L1 2 In addition to the gamma 'phase of the structure, a gamma' phase is also used for precipitation strengthening. The structure of the gamma phase is D0 22 The structure of the catalyst also forms a coherent interface with an FCC matrix. Form D0 22 The structural elements are Nb, Ta, V and Cr. However, in the past, it was found that Ni 3 Cr formation is very difficult in the whole superalloy, and Ni is still difficult to find in 20 at.% Cr 3 Cr, and Ni is not present in ICSD database 3 And Cr. For the Nb and Ta elements common in superalloys, the formation of D0 into the gamma prime phase 22 The gamma "phase of the structure. Ni 3 V has been shown to precipitate in the Ni-Al-V system. Ni 3 V、Ni 3 Nb and Ni 3 Ta are all D0 22 Structure, found in ICSD. And moreover, the gamma is more dispersed and fine, so that the high-temperature mechanical resistance of the high-temperature alloy can be further improved. Therefore, Al and V become essential additional elements.
Nb preferentially enters γ ", can significantly increase γ" to make it the predominant phase out, and raise the dissolution temperature of γ ". Meanwhile, Nb element can enter gamma 'phase, so that the content and the dissolving temperature of the gamma' phase are improved.
Cr is a key element for improving the hot corrosion resistance and the oxidation resistance of the alloy and must be added into the alloy. The addition of more than 10 at.% of Cr to the alloy system can obviously improve the hot corrosion resistance and oxidation resistance of the alloy. Meanwhile, V and Nb are contained in the alloy, which increases the precipitation tendency of harmful phases, so that the addition amount of Cr is not more than 15 at.%.
The high-performance nickel-based turbine disk high-temperature alloy strengthened by double precipitated phases provided by the invention has the tensile property superior to that of a typical forged nickel-based turbine disk high-temperature alloy Waspaloy and has good oxidation resistance.
Preferably, the gamma 'mole fraction of the nickel-based turbine disk superalloy is 10.01-23.12 mol%, the gamma' mole fraction is 22.01-28.12 mol%, and the harmful phase mole fraction is 0 mol%.
The preparation method of the double precipitated phase strengthened nickel-based turbine disk high-temperature alloy comprises the following steps: weighing the raw materials according to the component ratio, smelting by adopting a vacuum induction arc furnace, casting into a master alloy with chemical components meeting the requirements, finally carrying out heat treatment on the master alloy, and carrying out air cooling to obtain the double-precipitation-phase reinforced nickel-based turbine disk high-temperature alloy.
Preferably, the raw material selection in the preparation method adopts pure Al and nickel-based intermediate alloy.
Preferably, the heat treatment in the preparation method is solution treatment and aging treatment.
Preferably, the temperature of the solution treatment in the preparation method is 1180-1220 ℃, and the time is 8-12 h; the aging treatment is divided into two stages, the temperature of the first stage of aging treatment is 1130-1160 ℃, the time is 4-6 h, and air cooling is carried out; and air cooling the second stage at 880-1000 ℃ for 14-18 h.
Preferably, the temperature of the solution treatment in the preparation method is 1200 ℃, the time is 8h, and the air cooling is carried out; the aging treatment is divided into two stages, the temperature of the aging treatment in the first stage is 1150 ℃, the time is 4 hours, and air cooling is carried out; and the temperature of the aging treatment of the second stage is 900 ℃, the time is 16h, and the air cooling is carried out.
Compared with the prior art, the invention has the following beneficial effects:
in the scheme, compared with the nickel-based high-temperature alloy for the turbine disk, the nickel-based high-temperature alloy for the turbine disk strengthened by the double precipitated phases provided by the invention has the advantages that the high yield strength at 1000 ℃, the high-temperature structure stability and the high oxidation resistance can be realized.
The double precipitated phase strengthened nickel-based turbine disk high-temperature alloy provided by the invention has the functions of respectively forming a gamma 'phase by V, forming a gamma' phase by Al and preferentially entering the gamma by Nb, and can obviously increase the gamma so as to enable the gamma to become a main phase and improve the dissolution temperature of the gamma. Meanwhile, Nb element can enter gamma 'phase, so that the content and the dissolving temperature of the gamma' phase are improved. Cr is a key element for improving the hot corrosion resistance and the oxidation resistance of the alloy and must be added into the alloy. The addition of more than 10 at.% of Cr to the alloy system can obviously improve the hot corrosion resistance and oxidation resistance of the alloy. Meanwhile, V and Nb are contained in the alloy, which increases the precipitation tendency of harmful phases, so that the addition amount of Cr is not more than 15 at.%. The method does not contain high-cost cobalt element selection, has simple and easy-to-operate heat treatment mode, does not need hot rolling and complex heat treatment, has less energy consumption and is beneficial to industrial large-scale production.
The double-precipitation-phase strengthened nickel-based turbine disk superalloy provided by the invention has the Cr content of 10 at.% which is not available in the prior art, and has better oxidation resistance and hot corrosion resistance than the prior art.
In the nickel-based turbine disk high-temperature alloy reinforced by double precipitated phases, the mole fractions of a gamma 'phase and a gamma' phase are moderate, the gamma 'phase is higher than the gamma' phase, the harmful phase is 0 mol%, the structure stability at 1000 ℃ is good, and the oxidation resistance is excellent.
In a word, the double precipitated phase reinforced nickel-based turbine disk high-temperature alloy provided by the invention is low in component selection cost, simple and convenient in heat treatment, low in energy consumption, high in resource utilization rate, free of harmful phases, good in structure stability at 1000 ℃, and beneficial to industrial large-scale production.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a typical microstructural structure of a dual precipitation strengthened nickel-based turbine disk superalloy of example 4 of the present invention after heat treatment;
fig. 2 is an XRD pattern after heat treatment of the dual precipitate strengthened nickel-base turbine disk superalloy of example 4 of the present invention.
Detailed Description
The technical solutions and the technical problems to be solved in the embodiments of the present invention will be described below with reference to the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the patent of the invention, not all embodiments.
The chemical compositions of the nickel-based single crystal superalloys of examples 1-4 in atomic percent are shown in table 1.
Weighing raw materials according to the component proportion of examples 1-4 in Table 1, smelting by adopting a vacuum induction arc furnace, casting into a master alloy with chemical components meeting the requirements, and finally carrying out heat treatment on the master alloy, wherein the heat treatment comprises solid solution treatment and aging treatment, the temperature of the solid solution treatment is 1200 ℃, the time is 8 hours, and air cooling is carried out; the aging treatment is divided into two stages, the temperature of the aging treatment in the first stage is 1150 ℃, the time is 4 hours, and air cooling is carried out; the temperature of the aging treatment of the second stage is 1020 ℃, the time is 4 hours, and air cooling is carried out; obtaining the nickel-based high-temperature alloy with the strengthened double precipitated phases for the turbine disk.
Table 1 chemical composition (at.%) of examples 1-4
The typical microstructure of the nickel-based turbine disk superalloy strengthened by the double precipitated phases after heat treatment in example 4 is shown in fig. 1, and it can be seen that the alloy does contain two precipitated phases of γ' and γ ″, the distribution and content of the two precipitated phases can play a role in improving the high-temperature yield strength, and the XRD pattern after heat treatment shows that no harmful phases exist in the alloy.
The samples of the nickel-based turbine disk high-temperature alloy strengthened by the double precipitated phases are subjected to heat treatment and then subjected to tensile property test, wherein the yield strengths of the examples 1-4 are respectively 815MPa, 852MPa, 875MPa and 863MPa, and the yield strength of the Waspaloy alloy in the prior art is 795 MPa. Obviously, the tensile property of the nickel-based high-temperature alloy strengthened by the double precipitated phases is superior to that of the Waspaloy alloy in the prior art.
The Cr activities at 1000 ℃ were calculated for examples 1-4 using Thermo-Calc software, and the Cr activities for examples 1-4 were 0.00341, 0.00339, 0.0037, and 0.00335, respectively, compared to 0.00302 for the 1000 ℃ Cr activity of the Waspaloy alloy of the prior art. The comparison shows that the oxidation corrosion resistance of the alloy is obviously superior to that of the Waspaloy alloy in the prior art.
The γ 'content, γ' content, harmful phase content at 1000 ℃ of examples 1-4 were calculated using Thermo-Calc software, and the calculation results are shown in Table 2. The microstructure of the alloy of the invention conforms to the structure of the superalloy.
TABLE 2. gamma.' content, gamma. "content, harmful phase content at 1000 ℃ of examples 1 to 4
Therefore, the nickel-based turbine disk superalloy in the prior art is lower than that of the present application in the aspect of comprehensive performance of the above properties, and does not have the high yield strength, the structural stability, the new hot corrosion resistance and the oxidation resistance at the high temperature of 1000 ℃ of the present application.
In the scheme, compared with the nickel-based high-temperature alloy for the turbine disk, the nickel-based high-temperature alloy for the turbine disk strengthened by the double precipitated phases provided by the invention can realize high yield strength, high-temperature structure stability and high oxidation resistance at 1000 ℃.
The double precipitated phase reinforced nickel-based turbine disk high-temperature alloy provided by the invention has the functions of selecting the component content of V to form a gamma 'phase, Al to form a gamma' phase, and Nb to enter gamma preferentially, so that the gamma 'phase can be increased remarkably to become a main phase, and the dissolution temperature of the gamma' phase is increased. Meanwhile, Nb element can enter gamma 'phase, so that the content and the dissolving temperature of the gamma' phase are improved. Cr is a key element for improving the hot corrosion resistance and the oxidation resistance of the alloy and must be added into the alloy. The addition of more than 10 at.% of Cr to the alloy system can obviously improve the hot corrosion resistance and oxidation resistance of the alloy. At the same time, the presence of V and Nb in the alloy increases the tendency to precipitation of harmful phases, so that the amount of Cr does not exceed 15 at.%. The method does not contain high-cost cobalt element selection, has simple and easy-to-operate heat treatment mode, does not need hot rolling and complex heat treatment, has less energy consumption and is beneficial to industrial large-scale production.
The double-precipitation-phase strengthened nickel-based turbine disk superalloy provided by the invention has the Cr content of 10 at.% which is not available in the prior art, and has better oxidation resistance and hot corrosion resistance than the prior art.
In the nickel-based turbine disk high-temperature alloy reinforced by double precipitated phases, the mole fractions of a gamma 'phase and a gamma' phase are moderate, the gamma 'phase is higher than the gamma' phase, the harmful phase is 0 mol%, the structure stability at 1000 ℃ is good, and the oxidation resistance is excellent.
In a word, the double precipitated phase reinforced nickel-based turbine disk high-temperature alloy provided by the invention is low in component selection cost, simple and convenient in heat treatment, low in energy consumption, high in resource utilization rate, free of harmful phases, good in structure stability at 1000 ℃, and beneficial to industrial large-scale production.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (8)
1. The nickel-based turbine disk high-temperature alloy reinforced by double precipitated phases is characterized by comprising the following chemical components in atomic percentage: al: 5.0-6.0 at.%, V: 8.5-13.0 at.%, Nb: 7.5-9.5 at.%, Cr: 10.0-15.0 at.%, and the balance Ni.
2. The dual precipitate phase strengthened nickel-based turbine disk superalloy as claimed in claim 1, wherein the nickel-based turbine disk superalloy comprises the following chemical components in atomic percent: al: 5.0-6.0 at.%, V: 9.0-12.0 at.%, Nb: 8.0-9.0 at.%, Cr: 11.0-13.0 at.%, and the balance of Ni.
3. The dual precipitate phase strengthened nickel-based turbine disk superalloy as in claim 1, wherein the nickel-based turbine disk superalloy has a gamma prime mole fraction of 10.01 to 23.12 mol%, a gamma prime mole fraction of 22.01 to 28.12 mol%, and a detrimental phase mole fraction of 0 mol%.
4. The method for preparing the dual precipitate phase strengthened nickel-based turbine disk superalloy as claimed in claim 1, wherein the method comprises: weighing the raw materials according to the component ratio, smelting by adopting a vacuum induction arc furnace, casting into a master alloy with chemical components meeting the requirements, finally carrying out heat treatment on the master alloy, and carrying out air cooling to obtain the double-precipitation-phase reinforced nickel-based turbine disk high-temperature alloy.
5. The method for preparing the dual precipitate phase strengthened nickel-based turbine disk superalloy as claimed in claim 1, wherein the raw material selection in the preparation method is pure Al and nickel-based master alloy.
6. The method of making a dual precipitate phase strengthened nickel based turbine disk superalloy as in claim 1, wherein the heat treatment in the method of making is solution treatment and aging.
7. The preparation method of the double-precipitation-phase-strengthened nickel-based turbine disk superalloy as claimed in claim 1, wherein the temperature of solution treatment in the preparation method is 1180-1220 ℃, and the time is 8-12 hours; the aging treatment is divided into two stages, the temperature of the first stage of aging treatment is 1130-1160 ℃, the time is 4-6 h, and air cooling is carried out; and air cooling the second stage at 880-1000 ℃ for 14-18 h.
8. The method for preparing the dual-precipitation-phase-strengthened nickel-based turbine disk superalloy according to claim 1, wherein the solution treatment temperature in the preparation method is 1200 ℃, the time is 8 hours, and the nickel-based turbine disk superalloy is air-cooled; the aging treatment is divided into two stages, the temperature of the aging treatment in the first stage is 1150 ℃, the time is 4 hours, and air cooling is carried out; and the temperature of the aging treatment of the second stage is 900 ℃, the time is 16h, and the air cooling is carried out.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4325756A (en) * | 1978-12-18 | 1982-04-20 | United Technologies Corporation | Fatigue resistant nickel superalloy |
| US20030034098A1 (en) * | 2001-04-24 | 2003-02-20 | General Electric Company | Nickel-base superalloys and articles formed therefrom |
| US20180066340A1 (en) * | 2015-04-01 | 2018-03-08 | Oxford University Innovation Limited | A nickel-based alloy |
| CN110551920A (en) * | 2019-08-30 | 2019-12-10 | 北京北冶功能材料有限公司 | High-performance easy-processing nickel-based wrought superalloy and preparation method thereof |
| CN112853156A (en) * | 2021-01-11 | 2021-05-28 | 北京科技大学 | High-structure-stability nickel-based high-temperature alloy and preparation method thereof |
| CN114182139A (en) * | 2021-12-10 | 2022-03-15 | 西北工业大学 | Precipitation strengthening nickel-based high-temperature alloy and preparation method thereof |
| CN114231767A (en) * | 2021-12-16 | 2022-03-25 | 中国科学院金属研究所 | Method for controlling sigma phase precipitation of hot corrosion resistant nickel-based superalloy |
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- 2022-05-30 CN CN202210602412.7A patent/CN115058625A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4325756A (en) * | 1978-12-18 | 1982-04-20 | United Technologies Corporation | Fatigue resistant nickel superalloy |
| US20030034098A1 (en) * | 2001-04-24 | 2003-02-20 | General Electric Company | Nickel-base superalloys and articles formed therefrom |
| US20180066340A1 (en) * | 2015-04-01 | 2018-03-08 | Oxford University Innovation Limited | A nickel-based alloy |
| CN110551920A (en) * | 2019-08-30 | 2019-12-10 | 北京北冶功能材料有限公司 | High-performance easy-processing nickel-based wrought superalloy and preparation method thereof |
| CN112853156A (en) * | 2021-01-11 | 2021-05-28 | 北京科技大学 | High-structure-stability nickel-based high-temperature alloy and preparation method thereof |
| CN114182139A (en) * | 2021-12-10 | 2022-03-15 | 西北工业大学 | Precipitation strengthening nickel-based high-temperature alloy and preparation method thereof |
| CN114231767A (en) * | 2021-12-16 | 2022-03-25 | 中国科学院金属研究所 | Method for controlling sigma phase precipitation of hot corrosion resistant nickel-based superalloy |
Non-Patent Citations (1)
| Title |
|---|
| BIN XU ET AL.: "CALPHAD design and high-throughput searh of novel Ni-based superalloys that are reinforced by γ\' + γ\'\'" * |
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