CN115747577B - Deformed superalloy for turbine disk and preparation method thereof - Google Patents
Deformed superalloy for turbine disk and preparation method thereof Download PDFInfo
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 61
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 24
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 13
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims description 47
- 229910045601 alloy Inorganic materials 0.000 claims description 39
- 239000000956 alloy Substances 0.000 claims description 39
- 238000001816 cooling Methods 0.000 claims description 36
- 238000005242 forging Methods 0.000 claims description 34
- 230000032683 aging Effects 0.000 claims description 20
- 238000004321 preservation Methods 0.000 claims description 20
- 238000011282 treatment Methods 0.000 claims description 11
- 238000003723 Smelting Methods 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 6
- 238000000265 homogenisation Methods 0.000 claims description 5
- 238000009826 distribution Methods 0.000 claims description 4
- 238000010275 isothermal forging Methods 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 238000010791 quenching Methods 0.000 claims description 3
- 230000000171 quenching effect Effects 0.000 claims description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract description 15
- 229910052726 zirconium Inorganic materials 0.000 abstract description 10
- 229910052804 chromium Inorganic materials 0.000 abstract description 6
- 229910052742 iron Inorganic materials 0.000 abstract description 6
- 229910052758 niobium Inorganic materials 0.000 abstract description 6
- 229910052759 nickel Inorganic materials 0.000 abstract description 3
- 239000000243 solution Substances 0.000 description 17
- 238000005728 strengthening Methods 0.000 description 10
- 230000000052 comparative effect Effects 0.000 description 9
- 239000006104 solid solution Substances 0.000 description 7
- 238000007711 solidification Methods 0.000 description 7
- 230000008023 solidification Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 5
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- 230000008018 melting Effects 0.000 description 5
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- 230000001105 regulatory effect Effects 0.000 description 3
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- 239000013078 crystal Substances 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000010274 multidirectional forging Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 241001085205 Prenanthella exigua Species 0.000 description 1
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Abstract
The invention relates to the technical field of nickel-based superalloy, in particular to a deformed superalloy for a turbine disc and a preparation method thereof. The deformation superalloy for the turbine disk comprises the following components in percentage by mass: 17 to 20 percent of Co, 10 to 13 percent of Cr, 2.5 to 4 percent of Mo, 2.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 0.7 to 2 percent of Nb, 2.5 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.005 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni. The deformed superalloy can meet the requirements of hot end rotating parts such as a turbine disk of a domestic aviation and aerospace engine on high-temperature creep strength resistance, excellent comprehensive performance, high homogeneity and low cost.
Description
Technical Field
The invention relates to the technical field of nickel-based superalloy, in particular to a deformed superalloy for a turbine disc and a preparation method thereof.
Background
Future generation aerospace turbine engines are required to have excellent service performance and high temperature durability. The compressor and turbine disk materials can bear higher rotational speed, stress and temperature, so that the turbine engine has higher thrust-weight ratio, maneuverability and fuel efficiency. The higher temperatures experienced by advanced turbine disks require long periods of high temperature stress throughout the rim to the hub, higher strength, high temperature creep resistance, thermo-mechanical fatigue performance, and excellent notched low cycle fatigue performance.
The long-term use temperature of the existing nickel-based turbine disc deformation alloy is limited to be 600-750 ℃, so that the development of the aerospace turbine engine is limited.
In view of this, the present invention has been made.
Disclosure of Invention
The invention aims to provide a deformation superalloy for a turbine disk, which solves the technical problems of insufficient temperature bearing capacity and the like in the prior art.
Another object of the present invention is to provide a method of producing a wrought superalloy for a turbine disk.
In order to achieve the above object of the present invention, the following technical solutions are specifically adopted:
the deformation superalloy for the turbine disk comprises the following components in percentage by mass:
17 to 20 percent of Co, 10 to 13 percent of Cr, 2.5 to 4 percent of Mo, 2.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 0.7 to 2 percent of Nb, 2.5 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.005 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni.
In a specific embodiment of the invention, the deformation superalloy for turbine discs comprises the following components in percentage by mass:
17 to 19 percent of Co, 11 to 13 percent of Cr, 2.5 to 3.5 percent of Mo, 2.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 1 to 1.8 percent of Nb, 3 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.01 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni.
In a specific embodiment of the present invention, the mass fractions of B, zr and C satisfy: (B+Zr)/C is 3 to 7. Namely, the ratio of the sum of the mass fractions of B and Zr to the mass fraction of C element is 3-7.
In a specific embodiment of the present invention, the deformation superalloy for a turbine disc does not include Hf.
In a specific embodiment of the invention, the sum of the mass fractions of Al, ti, nb and Ta is 10-13.5%.
In the specific embodiment of the invention, the sum of the mass fractions of Al and Ta is 6-8.5%; the mass fraction ratio of Al to Ta is 0.6-1.
In a specific embodiment of the present invention, the ratio of the mass fraction of Ta to Ti is 1 to 1.7.
In the specific embodiment of the invention, the sum of the mass fractions of Mo and W is 5.5-7.5%; the mass fraction ratio of W to Mo is 1-1.8.
The invention also provides a preparation method of the deformed superalloy for the turbine disk, which comprises the following steps:
(1) Mixing materials according to the deformation high-temperature alloy components for the turbine disc, and smelting to obtain an ingot;
(2) Carrying out high-temperature homogenization heat treatment on the cast ingot, and then cogging and forging to obtain a blank; the blank is die-formed and then subjected to solution heat treatment and aging heat treatment.
In a specific embodiment of the present invention, the solution heat treatment includes: heat preservation at 1110-1160 deg.c and cooling. Further, the heat preservation treatment time is 2-6 hours.
In a specific embodiment of the present invention, in the solution heat treatment, the cooling includes any one of oil cooling, air cooling, or high pressure gas quenching.
In a specific embodiment of the present invention, the aging heat treatment includes: and (3) after heat preservation treatment at 760-830 ℃, cooling. Further, the heat preservation treatment time is 4-16 hours.
In a specific embodiment of the present invention, in the aging heat treatment, the cooling includes air cooling.
In the specific embodiment of the invention, the temperature of the high-temperature homogenizing heat treatment is 1100-1200 ℃, and the heat preservation time is more than or equal to 12 hours. Further, the high temperature homogenizing heat treatment includes: heat preservation is carried out for at least 12h at 1100-1170 ℃, and then heat preservation is carried out for at least 12h at 1170-1200 ℃.
In a specific embodiment of the invention, the cogging is performed in a constraint upsetting manner; the forging is performed by adopting a 3D forging mode or a multidirectional forging mode.
In a specific embodiment of the present invention, the die forging forming comprises hot forging and/or isothermal forging.
In a specific embodiment of the present invention, the temperature of the die forging forming is 1080-1140 ℃.
In a specific embodiment of the present invention, the γ' phase exhibits a trimodal distribution in the deformed superalloy for a turbine disk. Further, in the deformed superalloy for turbine discs, the primary gamma' -phase volume fraction is about 10% -15%, and the size is 0.3-7 μm; the volume fraction of the secondary gamma' phase is about 18-25%, and the size is 40-300 nm; the volume fraction of the tertiary gamma' phase is about 3-8%, and the size is smaller than 40nm.
In a specific embodiment of the present invention, the deformed superalloy for a turbine disk further includes an η phase. Further, the volume fraction of the eta phase is about 8 to 14 percent and the size is 0.3 to 5 mu m.
In a specific embodiment of the present invention, in the deformed superalloy for a turbine disk, a grain structure is 6 to 9 grades.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the invention, a certain alloy composition is adopted, the content and the proportion of the strengthening phase elements are regulated, more volume fractions of the strengthening phase are obtained, the content and the proportion of the solid solution strengthening elements are reasonably regulated and controlled, the precipitation of uneven large-size brittle phases is avoided, the gamma 'phase is in three-mode distribution in cooperation with corresponding solid solution and aging heat treatment conditions, the grain size is controlled by compounding the primary gamma' phase and the eta phase, a 6-9-grade grain structure is obtained, and the strengthening phase is subjected to compound strengthening by the secondary gamma 'phase, the tertiary gamma' phase and the eta phase, so that excellent comprehensive performance, especially high-temperature performance, is obtained;
(2) The deformed superalloy can meet the requirements of hot end rotating parts such as a turbine disk of a domestic aviation and aerospace engine on high-temperature creep strength resistance, excellent comprehensive performance, high homogeneity and low cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a physical diagram of a turbine disk forging prepared in example 1 of the present invention;
FIG. 2 is an electron back scattering diffraction image of a turbine disk forging prepared in example 1 of the present invention;
fig. 3 is an optical microscope image of the structure of the turbine disk forging prepared in example 1 of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings and detailed description, but it will be understood by those skilled in the art that the examples described below are some, but not all, examples of the present invention, and are intended to be illustrative of the present invention only and should not be construed as limiting the scope of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. The specific conditions are not noted in the examples and are carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or apparatus used were conventional products commercially available without the manufacturer's attention.
The deformation superalloy for the turbine disk comprises the following components in percentage by mass:
17 to 20 percent of Co, 10 to 13 percent of Cr, 2.5 to 4 percent of Mo, 2.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 0.7 to 2 percent of Nb, 2.5 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.005 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni.
The invention is based on the turbine disk alloy requirements of higher temperature bearing capacity and higher creep resistance, adopts large-atom Ta to strengthen and improve the element content, adjusts the strengthening phase element content and the proportion thereof to obtain more strengthening phase volume fraction, reasonably adjusts and controls the solid solution strengthening element content and the proportion thereof, avoids the precipitation of uneven large-size brittle phase, and obtains excellent comprehensive performance, especially high-temperature performance. Ta enters a gamma ' phase on one hand, the volume fraction of the gamma ' phase is improved to a certain extent, the diffusion rate of elements in the gamma ' phase is reduced, and the high-temperature creep resistance is improved; on the other hand, a small amount of Ta is dissolved in the alloy matrix in a solid way; in addition, when the Ta content is further increased, a certain amount of eta phases are precipitated to realize the strengthening of the alloy. But Ta content is not higher than 5%, otherwise density increase is higher, cost increase, and performance improvement is limited.
In addition, less B element is added into the alloy, so that the initial melting point of the alloy is further prevented from being reduced, large-size boride is prevented from being formed, and the segregation degree of the alloy is prevented from being increased. Excessive B element can cause the plasticity of the alloy to be poor and the mechanical property to be unstable.
As in the various embodiments, the mass fractions of the components may be as follows:
the mass fraction of Co may be 17%, 17.5%, 18%, 18.5%, 19%, 19.5%, 20%, etc.;
the mass fraction of Cr may be 10%, 10.5%, 11%, 11.5%, 12%, 12.5%, 13%, etc.;
mo may be 2.5%, 2.8%, 3%, 3.2%, 3.5%, 3.8%, 4%, etc.;
the mass fraction of W may be 2.5%, 2.8%, 3%, 3.2%, 3.5%, 3.8%, 4%, 4.5%, etc.;
the mass fraction of Al may be 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc.;
the mass fraction of Ti may be 2.5%, 2.6%, 2.7%, 2.8%, 2.9%, 3%, 3.1%, 3.2%, 3.3%, 3.4%, 3.5%, etc.;
the mass fraction of Nb may be 0.7%, 0.8%, 1%, 1.2%, 1.4%, 1.5%, 1.6%, 1.8%, 2%, etc.;
the mass fraction of Ta may be 2.5%, 3%, 3.5%, 4%, 4.5%, 5%, etc.;
the mass fraction of B may be 0.01%, 0.012%, 0.014%, 0.015%, 0.016%, 0.018%, 0.02%, etc.;
the mass fraction of C may be 0.005%, 0.008%, 0.01%, 0.015%, 0.02%, 0.025%, 0.03%, 0.035%, 0.04%, etc.;
the mass fraction of Zr may be 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, etc.;
the mass fraction of Fe may be 0%, 0.05%, 0.1%, 0.2%, 0.3%, 0.4%, 0.5%, etc.
In a specific embodiment of the invention, the deformation superalloy for turbine discs comprises the following components in percentage by mass:
17 to 19 percent of Co, 11 to 13 percent of Cr, 2.5 to 3.5 percent of Mo, 2.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 1 to 1.8 percent of Nb, 3 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.01 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni.
In a specific embodiment of the invention, the deformation superalloy for turbine discs comprises the following components in percentage by mass:
18.5 to 19.5 percent of Co, 11 to 11.8 percent of Cr, 2.5 to 2.8 percent of Mo, 3.5 to 4.5 percent of W, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, 1 to 1.8 percent of Nb, 4.85 to 5 percent of Ta, 0.01 to 0.02 percent of B, 0.01 to 0.04 percent of C, 0.03 to 0.07 percent of Zr, 0 to 0.5 percent of Fe and the balance of Ni.
The invention particularly improves the content of W, reduces the content of Cr, and can effectively improve the high-temperature creep property of the alloy by matching with other components.
In a specific embodiment of the present invention, the mass fractions of B, zr and C satisfy: (B+Zr)/C is 3 to 7. Namely, the ratio of the sum of the mass fractions of B and Zr to the mass fraction of C element is 3-7.
As in the various embodiments, (b+zr)/C may be 3, 3.5, 4, 4.5, 5, 5.5, 6, 6.5, 7, etc. In addition, by proper amount of Zr and B content, the grain boundary can be purified to improve crack propagation resistance, too much Zr and B easily cause segregation, reduce hot workability and creep property.
In a specific embodiment of the present invention, the deformation superalloy for a turbine disc does not include Hf. In the high-temperature alloy, hf is not added, so that large-size carbide is avoided, the casting performance of the alloy is improved, the segregation degree is reduced, and the risk of primary melting of the alloy during forging is eliminated; meanwhile, the mixture ratio of the other components is matched, so that the high-temperature performance of the alloy is ensured.
In a specific embodiment of the invention, the sum of the mass fractions of Al, ti, nb and Ta is 10-13.5%. When the sum of the mass fractions of Al, ti, nb and Ta is less than 10%, the tensile strength of the alloy is low, and when it is more than 13.5%, the casting solidification process performance is deteriorated, and the material plasticity is lowered.
As in the various embodiments, the sum of the mass fractions of Al, ti, nb, and Ta may be 10%, 10.5%, 11%, 11.5%, 12%, 12.5%, 13%, 13.5%, etc.
In the specific embodiment of the invention, the sum of the mass fractions of Al and Ta is 6-8.5%; the mass fraction ratio of Al to Ta is 0.6-1. Too low a sum of the mass fractions of Al and Ta can lead to poor oxidation resistance of the alloy and reduced high-temperature strength; and when the sum of the mass fractions of Al and Ta is too high, the alloy may have insufficient low-temperature strength. The sum of the mass fractions of Al and Ta is regulated to meet the requirements, so that the alloy can be ensured to have excellent high-temperature oxidation resistance when the alloy is used at 750 ℃ and above, the mass fraction ratio of the Al and Ta meets the requirements, and the material can be ensured to have excellent high-temperature strength and high-temperature plasticity.
As in the various embodiments, the sum of the mass fractions of Al and Ta may be 6%, 6.5%, 7%, 7.5%, 8%, 8.5%, etc.; the ratio of the mass fractions of Al and Ta may be 0.6, 0.65, 0.7, 0.75, 0.8, 0.85, 0.9, 0.95, 1, etc.
In a specific embodiment of the invention, the ratio of the mass fractions of Ta and Ti is 1 to 1.7, preferably 1.61 to 1.7. When the ratio of the mass fractions of Ta and Ti is too low, the high-temperature strength of the alloy is lowered, and when it is too high, the alloy density is too high, and crack growth resistance is deteriorated. By controlling the ratio of Ta and Ti within the above range, a certain amount of eta phase can be formed, and the size is equal to or smaller than the grain size, limiting the grain size.
As in the various embodiments, the ratio of mass fractions of Ta and Ti may be 1, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, etc.
In a specific embodiment of the invention, the sum of the mass fractions of Mo and W is 5.5-7.5%, preferably 6.5-7.5%; the mass fraction ratio of W to Mo is 1 to 1.8, preferably 1.5 to 1.8. If the sum of the mass fractions of Mo and W is too high, a harmful phase is easily formed; the ratio of the two is in the range, so that the high-temperature creep resistance of the alloy can be effectively increased.
As in the various embodiments, the sum of the mass fractions of Mo and W may be 5.5%, 6%, 6.5%, 7%, 7.5%, etc.; the ratio of the mass fractions of W and Mo may be 1, 1.1, 1.2, 1.3, 1.4, 1.5, etc.
The invention also provides a preparation method of the deformed superalloy for the turbine disk, which comprises the following steps:
(1) Mixing materials according to the deformation high-temperature alloy components for the turbine disc, and smelting to obtain an ingot;
(2) Carrying out high-temperature homogenization heat treatment on the cast ingot, and then cogging and forging to obtain a blank; the blank is die-formed and then subjected to solution heat treatment and aging heat treatment.
In a specific embodiment of the present invention, the solution heat treatment includes: heat preservation at 1110-1160 deg.c and cooling. Further, the heat preservation treatment time is 2-6 hours.
As in the various embodiments, the solution heat treatment temperature may be 1110 ℃, 1120 ℃, 1130 ℃, 1140 ℃, 1150 ℃, 1160 ℃, etc.; the holding time in the solution heat treatment may be 2h, 3h, 4h, 5h, 6h, etc.
The invention adopts lower solution heat treatment temperature, can obtain uniform fine grain structure, and the primary gamma' phase and eta phase of the alloy not only play a role in limiting the growth of crystal grains, but also can promote the strengthening effect of the alloy. If the alloy is prepared by adopting other solution heat treatment, the crystal grains can grow without limit, the alloy strength is reduced, and flaw detection cannot be performed.
In a specific embodiment of the present invention, in the solution heat treatment, the cooling includes any one of oil cooling, air cooling, or high pressure gas quenching.
In a specific embodiment of the present invention, the aging heat treatment includes: and (3) after heat preservation treatment at 760-830 ℃, cooling. Further, the heat preservation treatment time is 4-16 hours.
As in the various embodiments, the temperature of the aging heat treatment may be 760 ℃, 770 ℃, 780 ℃, 790 ℃, 800 ℃, 810 ℃, 820 ℃, 830 ℃, and so forth; the holding time in the aging heat treatment can be 4h, 6h, 8h, 10h, 12h, 14h, 16h and the like.
In a specific embodiment of the present invention, in the aging heat treatment, the cooling includes air cooling.
In particular embodiments of the invention, the smelting includes any one or more of vacuum induction smelting, electroslag remelting continuous directional solidification, and vacuum consumable remelting smelting. Further, the smelting includes: vacuum induction melting and electroslag remelting continuous directional solidification, or vacuum induction melting and vacuum consumable remelting melting.
In a specific embodiment of the invention, the diameter of the cast ingot obtained by continuous directional solidification of electroslag remelting or consumable vacuum remelting smelting is not more than 320mm.
In the specific embodiment of the invention, the temperature of the high-temperature homogenizing heat treatment is 1100-1200 ℃, and the heat preservation time is more than or equal to 12 hours. Further, the high temperature homogenizing heat treatment includes: heat preservation is carried out for at least 12h at 1100-1170 ℃, and then heat preservation is carried out for at least 12h at 1170-1200 ℃.
In a specific embodiment of the present invention, the high temperature homogenizing heat treatment further includes: after heat preservation treatment, furnace cooling to 650+/-10 ℃ and air cooling.
In a specific embodiment of the invention, the cogging is performed in a constraint upsetting manner; the forging is performed by adopting a 3D forging mode or a multidirectional forging mode.
In actual operation, the cycle times of the 3D forging or the multiple forging can be adjusted according to actual requirements, so as to prepare a rod blank or a cake blank which meets the requirements, and the like. And then machined and inspected.
In a specific embodiment of the present invention, the die forging forming comprises hot forging and/or isothermal forging.
In a specific embodiment of the present invention, the temperature of the die forging forming is 1080-1140 ℃.
As in various embodiments, the temperature of the die-forging forming may be 1080 ℃, 1090 ℃, 1100 ℃, 1110 ℃, 1120 ℃, 1130 ℃, 1140 ℃, and so forth.
In a specific embodiment of the present invention, the γ' phase exhibits a trimodal distribution in the deformed superalloy for a turbine disk. Further, in the deformed superalloy for turbine discs, the primary gamma' -phase volume fraction is about 10% -15%, and the size is 0.3-7 μm; the volume fraction of the secondary gamma' phase is about 18-25%, and the size is 40-300 nm; the volume fraction of the tertiary gamma' phase is about 3-8%, and the size is smaller than 40nm.
In a specific embodiment of the present invention, the deformed superalloy for a turbine disk further includes an η phase. Further, the eta phase volume fraction is about 8% -14%, and the size is 0.3-5 mu m.
In a specific embodiment of the present invention, in the deformed superalloy for a turbine disk, a grain structure is 6 to 9 grades.
Example 1
The embodiment provides a deformation superalloy for a turbine disk, which comprises the following components in percentage by mass: co 19%; cr 11%; mo 2.5%; w4.5%; al 3.0%; ti 3.0%; nb 1.5%; ta 4.9%; b0.015%; c0.020%; zr 0.05%; fe 0.1%; and Ni balance.
The preparation method of the deformed superalloy for the turbine disc comprises the following steps:
(1) Smelting a master alloy electrode rod by adopting a vacuum induction furnace, and then carrying out electroslag remelting continuous directional solidification smelting to prepare a directional solidification ingot with the diameter of 260mm;
(2) Carrying out high-temperature homogenization heat treatment on the directional solidification cast ingot: heating to 1130 ℃ along with the furnace, preserving heat for 12h, heating to 1190 ℃ of the homogenization highest temperature at a speed of 50 ℃/h, preserving heat for 36h, cooling to 650 ℃ and then cooling by air;
(3) Preparing a bar blank by performing constraint upsetting cogging and 4-cycle 3D forging on the cast ingot processed in the step (2), and then performing machining and inspection;
(4) Carrying out hot die forging on the blank processed in the step (3), wherein the forging temperature is 1110 ℃;
(5) Solid solution and aging heat treatment: the solution heat treatment condition is 1130 ℃/2h, and the oil is cooled; and (3) aging heat treatment conditions are 815 ℃/4h, air cooling is carried out, and the deformed high-temperature alloy forging is obtained after the air cooling is finished.
The deformed superalloy forging for the turbine disk, which is manufactured in the embodiment, is shown in fig. 1. The microstructure is shown in fig. 2 and 3. Fig. 2 is a back-scattered electron image showing a bright white particulate primary carbide and an off-white dispersed η phase. FIG. 3 is a diagram showing a grain structure, a grain size of ASTM grade 9, showing a primary gamma prime phase and a eta phase.
Examples 2 to 8
The production methods of the deformed superalloy for turbine discs of examples 2 to 8 are different from example 1 only in that: the superalloy has different compositions and different partial processes.
The compositions of the superalloys of examples 2-8 are shown in Table 1.
TABLE 1 composition (wt%) of superalloys of examples 2-8
Wherein, the aging heat treatment condition of the embodiment 2 is 780 ℃/8 hours, air cooling is carried out, and the deformed superalloy forging is obtained after the air cooling is finished;
the solution heat treatment conditions of example 3 were 1125 ℃/2 hours, oil cooled; and (3) aging heat treatment conditions are 780 ℃/8h, air cooling is carried out, and the deformed high-temperature alloy forging is obtained after the air cooling is finished.
Example 9
The method for producing the deformed superalloy for a turbine disk of example 9 is different from example 1 only in that: the solution and aging heat treatments are different.
The solid solution and aging heat treatment of example 9 included: solid solution 1190 ℃/2h oil cooling, aging 840 ℃/2h air cooling, 760 ℃/8h air cooling.
The turbine disc forging piece obtained by the embodiment has coarse grain structure, ultrasonic detection cannot be carried out, and the short-time tensile property of the alloy is obviously reduced below 800 ℃.
Comparative example 1
Comparative example 1 provides a GH4198 alloy turbine disc forging prepared by a deformation process, comprising the following chemical components: 20.5% of Co; cr 13%; mo 3.8%; w2.3%; al 3.4%; ti 3.8%; nb 1%; ta 2.5%; b0.015%; c0.02%; zr 0.05%; fe 0.1%; and Ni balance.
The preparation method is described with reference to example 1, except that the die forging temperature of step (4) is 1100 ℃; the solid solution and aging heat treatment conditions in the step (5) are 1125 ℃/2 hours, oil cooling +760 ℃/8 hours and air cooling.
Comparative example 2
Comparative example 2 referring to example 1, the difference is that: the superalloy composition is different.
The superalloy of comparative example 2 comprises the following components in mass percent: co 19%; cr 11%; mo 3%; w3%; al 3.0%; ti 3.0%; nb 1.5%; ta 4.9%; b0.010%; c0.05%; zr 0.020%; fe 0.1%; and Ni balance.
Experimental example 1
In order to comparatively illustrate the microstructure differences of the alloys prepared in the different examples and comparative examples, the microstructure of the alloys prepared in each example and comparative example was characterized, and the results are shown in table 2.
TABLE 2 microstructure of different alloys
For further comparative illustration of the high temperature creep properties and tensile properties of the alloys of the different examples and comparative examples, the following tests were performed, with reference to HB5151 and HB5195, and the test results are shown in tables 3 to 5, respectively.
TABLE 3 high temperature creep property 750 ℃/620MPa
TABLE 4 high temperature creep property 815 ℃/400MPa
TABLE 5 tensile Property test results
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From the above test results, it is understood that the long-term use temperature of the deformed superalloy for turbine disks of the present invention is raised to 750 ℃ and higher, and the short-term use temperature exceeds 800 ℃. In addition, the invention adopts a deformed high-temperature alloy process route for preparation, has short process flow, high purity, excellent comprehensive performance and acceptable cost.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (14)
1. The deformation superalloy for the turbine disk is characterized by comprising the following components in percentage by mass:
17% -20% of Co, 10% -13% of Cr, 2.5% -4% of Mo, 3% -4.5% of W, 2.5% -3.5% of Al, 2.5% -3.5% of Ti, 0.7% -2% of Nb, 4.85% -5% of Ta, 0.010% -0.020% of B, 0.005% -0.04% of C, 0.03% -0.07% of Zr, 0% -0.5% of Fe and the balance of Ni;
the mass fraction ratio of Ta to Ti is 1.61-1.7; the mass fraction ratio of Al to Ta is 0.6-0.7; the mass fraction ratio of W to Mo is 1.2-1.8;
the deformed superalloy for a turbine disk does not include Hf;
the deformation superalloy for the turbine disc comprises eta phase; the volume fraction of eta phase is 8% -14% and the size is 0.3-5 mu m;
the preparation method of the deformation superalloy for the turbine disc comprises the following steps:
(1) Mixing materials according to the deformation high-temperature alloy components for the turbine disc, and smelting to obtain an ingot;
(2) Carrying out high-temperature homogenization heat treatment on the cast ingot, and then cogging and forging to obtain a blank; performing die forging forming on the blank, and then performing solution heat treatment and aging heat treatment;
the solution heat treatment includes: heat preservation treatment is carried out at 1110-1160 ℃ and then cooling is carried out;
the aging heat treatment comprises: and (5) after heat preservation treatment at 760-830 ℃, cooling.
2. The deformed superalloy for a turbine disk according to claim 1, comprising the following components in mass percent:
17% -19% of Co, 11% -13% of Cr, 2.5% -3.5% of Mo, 3% -4.5% of W, 2.5% -3.5% of Al, 2.5% -3.5% of Ti, 1% -1.8% of Nb, 4.85% -5% of Ta, 0.012% -0.018% of B, 0.01% -0.04% of C, 0.03% -0.07% of Zr, 0% -0.5% of Fe and the balance of Ni.
3. The wrought superalloy for a turbine disk according to claim 1, wherein the wrought superalloy for a turbine disk comprises, in mass percent: 18.5% -19.5% of Co, 11% -11.8% of Cr, 2.5% -2.8% of Mo, 3.5% -4.5% of W, 2.5% -3.5% of Al, 2.5% -3.5% of Ti, 1% -1.8% of Nb, 4.85% -5% of Ta, 0.01% -0.02% of B, 0.01% -0.04% of C, 0.03% -0.07% of Zr, 0% -0.5% of Fe and the balance of Ni.
4. The deformed superalloy for a turbine disk according to claim 1, wherein the mass fractions of B, zr and C are: (B+Zr)/C is 3 to 7.
5. The deformed superalloy for a turbine disk according to claim 1, wherein the sum of mass fractions of Al, ti, nb, and Ta is 11% -13.5%;
the sum of the mass fractions of Al and Ta is 7.5% -8.5%.
6. The deformed superalloy for a turbine disk according to any of claims 1 to 5, wherein the sum of mass fractions of Mo and W is 5.5% to 7.5%;
the mass fraction ratio of W to Mo is 1.5-1.8.
7. The deformed superalloy for a turbine disk according to claim 6, wherein the sum of mass fractions of Mo and W is 6.5% -7.5%.
8. The deformed superalloy for a turbine disk according to claim 1, wherein the heat-retaining treatment is performed for 2 to 6 hours in the solution heat treatment; the cooling comprises any one of oil cooling, air cooling or high-pressure gas quenching;
in the aging heat treatment, the heat preservation treatment time is 4-16 hours; the cooling includes air cooling.
9. The deformed superalloy for a turbine disk according to claim 1, wherein the high-temperature homogenizing heat treatment is performed at 1100 to 1200 ℃ for a holding time of 12 hours or longer.
10. The deformed superalloy for a turbine disk according to claim 9, wherein the high temperature homogenizing heat treatment comprises: the heat preservation is carried out for at least 12 hours at the temperature of 1100-1170 ℃, and then the heat preservation is carried out for at least 12 hours at the temperature of 1170-1200 ℃.
11. The deformed superalloy for a turbine disk according to claim 1, wherein the die forging comprises hot die forging and/or isothermal forging;
the die forging forming temperature is 1080-1140 ℃.
12. The deformed superalloy for a turbine disk according to claim 1, wherein the gamma' -phase has a trimodal distribution in the deformed superalloy for a turbine disk.
13. The deformed superalloy for a turbine disk according to claim 12, wherein the deformed superalloy for a turbine disk has a primary gamma' -phase volume fraction of 10% to 15% and a size of 0.3 to 7 μm; the volume fraction of the secondary gamma' -phase is 18% -25%, and the size is 40-300 nm; the volume fraction of the cubic gamma' -phase is 3% -8%, and the size is smaller than 40nm.
14. The wrought superalloy for a turbine disk according to claim 12, wherein the wrought superalloy for a turbine disk has a grain structure of 6 to 9 grades.
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| CN116815077B (en) * | 2023-08-30 | 2023-11-21 | 北京中辰至刚科技有限公司 | Gas quenching aging heat treatment method based on TaHfNbZrTi refractory high-entropy alloy |
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