CN115747577A - Deformed high-temperature alloy for turbine disc and preparation method thereof - Google Patents
Deformed high-temperature alloy for turbine disc and preparation method thereof Download PDFInfo
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- 238000002360 preparation method Methods 0.000 title abstract description 9
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- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 17
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 17
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 14
- 229910052742 iron Inorganic materials 0.000 claims abstract description 12
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Abstract
The invention relates to the technical field of nickel-based high-temperature alloys, in particular to a deformed high-temperature alloy for a turbine disc and a preparation method thereof. The deformed high-temperature alloy for the turbine disc 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 wrought high-temperature alloy can meet the requirements of high-temperature creep resistance strength, excellent comprehensive performance, high homogeneity and low cost of hot-end rotating parts such as turbine disks of domestic aviation and aerospace engines.
Description
Technical Field
The invention relates to the technical field of nickel-based high-temperature alloys, in particular to a deformed high-temperature alloy for a turbine disc and a preparation method thereof.
Background
The future generation of aerospace turbine engines requires excellent service performance and high temperature durability. The materials of the air compressor and the turbine disc can bear higher rotating 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, from the rim through to the hub, require long periods of high temperature stress, require higher strength, high temperature creep resistance, thermal mechanical fatigue properties, and excellent notch low cycle fatigue properties.
The long-term use temperature of the existing nickel-based turbine disk wrought alloy is limited within the range of 600-750 ℃, so that the development of an aerospace turbine engine is limited.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a deformed high-temperature alloy for a turbine disc, 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 for preparing a wrought superalloy for turbine disks.
In order to achieve the above purpose of the present invention, the following technical solutions are adopted:
the wrought 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 wrought superalloy for the turbine disk 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 mass fractions of B, zr and C satisfy: the ratio of (B + Zr)/C is 3-7. Namely, the ratio of the sum of the mass fractions of the B and the Zr to the mass fraction of the C element is 3 to 7.
In an embodiment of the present invention, hf is not included in the wrought superalloy for turbine disks.
In a specific embodiment of the present invention, the sum of the mass fractions of Al, ti, nb and Ta is 10% to 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 fractions of Ta and Ti is 1 to 1.7.
In the specific implementation mode 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 wrought superalloy for the turbine disc, which comprises the following steps:
(1) Preparing materials according to the deformed 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 carrying out cogging and forging to obtain a blank; and carrying out die forging forming on the blank, and then carrying out solution heat treatment and aging heat treatment.
In a specific embodiment of the present invention, the solution heat treatment comprises: preserving heat at 1110-1160 ℃ and then cooling. Further, the time of the heat preservation treatment is 2-6 h.
In a specific embodiment of the present invention, the solution heat treatment, wherein the cooling includes any one of oil cooling, air cooling, or high-pressure air quenching.
In a specific embodiment of the present invention, the aging heat treatment comprises: and (3) carrying out heat preservation treatment at 760-830 ℃, and then cooling. Further, the time of the heat preservation treatment is 4-16 h.
In a specific embodiment of the present invention, the cooling comprises air cooling in the aging heat treatment.
In the specific embodiment of the invention, the temperature of the high-temperature homogenization heat treatment is 1100-1200 ℃, and the holding time is more than or equal to 12h. Further, the high-temperature homogenization heat treatment includes: the heat preservation treatment is carried out for not less than 12 hours at 1100-1170 ℃, and then the heat preservation treatment is carried out for not less than 12 hours at 1170-1200 ℃.
In a particular embodiment of the invention, said cogging is performed by means of constrained upsetting; the forging is performed by means of 3D forging or multidirectional forging.
In a specific embodiment of the present invention, the die forging includes hot die forging and/or isothermal forging.
In a specific embodiment of the present invention, the temperature for the die forging is 1080-1140 ℃.
In a specific embodiment of the present invention, in the wrought superalloy for a turbine disk, a γ' phase exhibits a trimodal distribution. Furthermore, in the deformed high-temperature alloy for the turbine disc, the volume fraction of the primary gamma' phase is about 10-15%, and the size is 0.3-7 mu m; the volume fraction of the secondary gamma' phase is about 18-25%, and the size is 40-300 nm; the volume fraction of the third gamma' phase is about 3-8%, and the size is less than 40nm.
In an embodiment of the present invention, the wrought superalloy for a turbine disk further includes an η phase. Furthermore, the volume fraction of the eta phase is about 8-14%, and the size is 0.3-5 μm.
In an embodiment of the present invention, the wrought superalloy for a turbine disk has a grain structure of grade 6 to 9.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention adopts certain alloy composition, adjusts the content and proportion of strengthening phase elements to obtain more strengthening phase volume fractions, reasonably regulates and controls the content and proportion of solid solution strengthening elements, avoids the precipitation of uneven large-size brittle phases, and matches with corresponding conditions of solid solution and aging heat treatment to ensure that a gamma 'phase presents three-modal distribution, a primary gamma' phase and an eta phase are compounded to control the grain size to obtain 6-9-grade grain structures, and the strengthening phase realizes the compound strengthening by a secondary gamma 'phase, a tertiary gamma' phase and the eta phase to obtain excellent comprehensive performance, in particular high-temperature performance;
(2) The wrought superalloy can meet the requirements of high-temperature creep resistance strength, excellent comprehensive performance, high homogeneity and low cost of hot-end rotating parts such as turbine discs of domestic aviation and aerospace engines.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a physical diagram of a turbine disk forging prepared in embodiment 1 of the invention;
FIG. 2 is an electron backscatter diffraction image of a turbine disc forging prepared in example 1 of the present invention;
FIG. 3 is an optical microscope image of the structure of a turbine disk forging prepared in example 1 of the present invention.
Detailed Description
The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings and the detailed description, but those skilled in the art will understand that the following described embodiments are some, not all, of the embodiments of the present invention, and are only used for illustrating the present invention, and should not be construed as limiting the scope of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products available commercially.
The wrought 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.
Based on the turbine disk alloy requirements of higher temperature bearing capacity and higher creep resistance, the invention adopts the large-atom Ta for strengthening, improves the element content, adjusts the element content and the proportion of the strengthening phase, obtains more strengthening phase volume fractions, reasonably regulates and controls the content and the proportion of the solid-solution strengthening element, avoids the precipitation of uneven large-size brittle phase, and obtains excellent comprehensive performance, especially high-temperature performance. On one hand, ta enters a gamma ' phase, so that 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 addition, when the content of Ta is further increased, a certain amount of eta phase is precipitated to strengthen the alloy. But the content of Ta is not higher than 5%, otherwise the density is increased more, the cost is increased, and the 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 different 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.;
the mass fraction of 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 wrought superalloy for the turbine disk 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 wrought superalloy for the turbine disk 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 especially 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 invention, the mass fractions of B, zr and C satisfy: the ratio of (B + Zr)/C is 3-7. Namely the ratio of the sum of the mass fractions of B and Zr to the mass fraction of the element C is 3-7.
As in the different embodiments, (B + Zr)/C may be 3, 3.5, 4, 4.5, 5, 5.5, 6, 6.5, 7, etc. In addition, by means of proper Zr and B content, grain boundary can be purified to improve crack propagation resistance, too much Zr and B easily cause segregation, hot workability is reduced, and creep property is reduced.
In a specific embodiment of the present invention, hf is not included in the wrought superalloy for turbine disks. In the high-temperature alloy, hf is not added, so that large-size carbide is prevented from being formed, the casting performance of the alloy is improved, the segregation degree is reduced, and the risk of forging and primary melting of the alloy is eliminated; meanwhile, the high-temperature performance of the alloy is ensured by matching with the mixture ratio of the other components.
In a specific embodiment of the present invention, the sum of the mass fractions of Al, ti, nb, and Ta is 10% to 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 the sum is more than 13.5%, the casting solidification process performance is deteriorated, and the plasticity of the material is lowered.
As in the different 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%, and so on.
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. If the sum of the mass fractions of Al and Ta is too low, the oxidation resistance of the alloy is poor, and the high-temperature strength is reduced; when the sum of the mass fractions of Al and Ta is too high, the low-temperature strength of the alloy may be insufficient. The sum of the mass fractions of Al and Ta meets the requirements, so that the alloy can be ensured to have excellent high-temperature oxidation resistance at the temperature of 750 ℃ or above, and the ratio of the mass fractions of the Al and Ta meets the requirements, so that the material can be ensured to have excellent high-temperature strength and high-temperature plasticity.
As in the different 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 present 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 alloy high-temperature strength decreases, while when too high, the alloy density becomes too high, and the crack propagation resistance deteriorates. 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 equivalent to or smaller than the grain size, limiting the grain size.
As in various embodiments, the ratio of the mass fractions of Ta and Ti may be 1, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, and so forth.
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 proportion of the two is in the range, so that the high-temperature creep resistance of the alloy can be effectively increased.
As in the different 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 wrought superalloy for the turbine disc, which comprises the following steps:
(1) Mixing the materials according to the components of the deformed high-temperature alloy for the turbine disc, and smelting to obtain an ingot;
(2) Carrying out high-temperature homogenization heat treatment on the cast ingot, and then carrying out cogging and forging to obtain a blank; and carrying out die forging forming on the blank, and then carrying out solution heat treatment and aging heat treatment.
In a specific embodiment of the present invention, the solution heat treatment comprises: preserving heat at 1110-1160 ℃ and then cooling. Further, the heat preservation treatment time is 2-6 h.
As in the different embodiments, the temperature of the solution heat treatment may be 1110 ℃, 1120 ℃, 1130 ℃, 1140 ℃, 1150 ℃, 1160 ℃, etc.; the holding time in the solution heat treatment may be 2h, 3h, 4h, 5h, 6h, or the like.
The invention adopts lower solution heat treatment temperature, uniform fine crystal structure can be obtained, and primary gamma' phase and eta phase existing in the alloy play a role in limiting grain growth and can promote alloy strengthening. However, if the alloy is produced by other solution heat treatment, the crystal grains may grow without limitation, the alloy strength may be lowered, and flaw detection may not be possible.
In a specific embodiment of the present invention, the cooling in the solution heat treatment 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 comprises: after heat preservation treatment at 760-830 ℃, cooling. Further, the time of the heat preservation treatment is 4-16 h.
As in various embodiments, the temperature of the aging heat treatment may be 760 ℃, 770 ℃, 780 ℃, 790 ℃, 800 ℃, 810 ℃, 820 ℃, 830 ℃, etc.; the heat preservation 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, the cooling comprises air cooling in the aging heat treatment.
In particular embodiments of the invention, the melting comprises any one or more of vacuum induction melting, continuous directional solidification with electroslag remelting, and vacuum consumable remelting melting. Further, the smelting comprises: 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 an ingot obtained by the electroslag remelting continuous directional solidification or the vacuum consumable remelting smelting is not more than 320mm.
In the specific embodiment of the invention, the temperature of the high-temperature homogenization heat treatment is 1100-1200 ℃, and the holding time is more than or equal to 12h. Further, the high-temperature homogenization heat treatment includes: the heat preservation treatment is carried out for not less than 12 hours at 1100-1170 ℃, and then the heat preservation treatment is carried out for not less than 12 hours at 1170-1200 ℃.
In an embodiment of the present invention, the high temperature homogenization heat treatment further comprises: after heat preservation treatment, the furnace is cooled to 650 +/-10 ℃ and then air-cooled.
In a particular embodiment of the invention, said cogging is performed by means of constrained upsetting; the forging is performed by means of 3D forging or multidirectional forging.
In actual operation, the cycle number of the 3D forging or multiple forging can be adjusted according to actual needs to prepare a rod blank or a cake blank meeting the requirements, and the like. And then machined and inspected.
In a specific embodiment of the present invention, the die forging includes hot die forging and/or isothermal forging.
In a specific embodiment of the present invention, the temperature of the die forging is 1080-1140 ℃.
As in the various embodiments, the temperature of the swaging may be 1080 ℃, 1090 ℃, 1100 ℃, 1110 ℃, 1120 ℃, 1130 ℃, 1140 ℃ and the like.
In a specific embodiment of the present invention, in the wrought superalloy for a turbine disk, a γ' phase exhibits a trimodal distribution. Furthermore, in the deformed high-temperature alloy for the turbine disc, the volume fraction of the primary gamma' phase is about 10-15%, and the size is 0.3-7 mu m; the volume fraction of the secondary gamma' phase is about 18-25%, and the size is 40-300 nm; the volume fraction of the third gamma' phase is about 3-8%, and the size is less than 40nm.
In an embodiment of the present invention, the wrought superalloy for a turbine disk further includes an η phase. Furthermore, the volume fraction of the eta phase is about 8-14%, and the size is 0.3-5 mu m.
In an embodiment of the present invention, the wrought superalloy for a turbine disk has a grain structure of grade 6 to 9.
Example 1
The embodiment provides a wrought superalloy for a turbine disk, which comprises the following components in percentage by mass: 19% of Co; 11% of Cr; 2.5 percent of Mo; 4.5 percent of W; 3.0 percent of Al; 3.0 percent of Ti; 1.5 percent of Nb; ta 4.9%; 0.015 percent of B; 0.020% of C; 0.05 percent of Zr; 0.1 percent of Fe; and the balance of Ni.
The preparation method of the wrought superalloy for the turbine disk comprises the following steps:
(1) Smelting a master alloy electrode bar by using 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 directionally solidified cast ingot: heating to 1130 ℃ along with the furnace, preserving heat for 12h, heating to the homogenization maximum temperature of 1190 ℃ at the speed of 50 ℃/h, preserving heat for 36h, cooling the furnace to 650 ℃, and then air cooling;
(3) Carrying out constrained upsetting and cogging on the cast ingot treated in the step (2) and carrying out 3D forging for 4 cycle times to prepare a bar blank, and then carrying out machining and inspection;
(4) Carrying out hot die forging molding 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 cooling is carried out; and (4) carrying out air cooling under the aging heat treatment condition of 815 ℃/4h, and obtaining the deformed high-temperature alloy forging after the air cooling is finished.
The wrought superalloy forging for the turbine disk manufactured in the embodiment is shown in FIG. 1. The microstructure is shown in FIGS. 2 and 3. FIG. 2 is a back-scattered electron image showing bright white particulate primary carbides, and an off-white dispersion of the eta phase. FIG. 3 is a diagram showing a grain structure of gold phase, grain size of ASTM grade 9, showing primary γ' phase and η phase.
Examples 2 to 8
Method for manufacturing the wrought superalloy for turbine disks of examples 2-8 reference example 1, with the only difference that: the high temperature alloy has different compositions and different part processes.
The compositions of the superalloys of examples 2-8 are shown in Table 1.
TABLE 1 composition (wt%) of the superalloys of examples 2-8
Wherein the aging heat treatment condition of the embodiment 2 is 780 ℃/8h, air cooling is carried out, and a deformed high-temperature alloy forging is obtained after the air cooling is finished;
the solution heat treatment conditions of the embodiment 3 are 1125 ℃/2h, oil cooling; and (4) performing air cooling under the aging heat treatment condition of 780 ℃/8h, and obtaining the deformed high-temperature alloy forging after the air cooling is finished.
Example 9
Method for preparing a wrought superalloy for turbine disks of example 9 referring to example 1, the only difference is that: solution and aging heat treatments differ.
The solution and aging heat treatment of example 9 includes: solid solution at 1190 deg.C/2 hr, aging at 840 deg.C/2 hr, and air cooling at 760 deg.C/8 hr.
The grain structure of the turbine disk forging obtained by the embodiment is coarse, ultrasonic detection cannot be carried out, and the short-time tensile property of the alloy below 800 ℃ is obviously reduced.
Comparative example 1
Comparative example 1 provides a GH4198 alloy turbine disk forging prepared using a deformation process, having the chemical composition: 20.5 percent of Co; 13% of Cr; 3.8 percent of Mo; 2.3 percent of W; 3.4 percent of Al; 3.8 percent of Ti; 1% of Nb; ta 2.5%; 0.015 percent of B; 0.02 percent of C; 0.05 percent of Zr; 0.1 percent of Fe; and the balance of Ni.
The preparation method is as described in example 1 except that the die forging temperature in step (4) is 1100 ℃; and (5) carrying out solid solution and aging heat treatment under the conditions of 1125 ℃/2h, oil cooling +760 ℃/8h, and air cooling.
Comparative example 2
Comparative example 2 reference example 1 with the difference that: the compositions of the superalloys differ.
The superalloy of comparative example 2, comprising the following composition in mass percent: 19% of Co; 11% of Cr; mo is 3 percent; w3%; 3.0 percent of Al; 3.0 percent of Ti; 1.5 percent of Nb; ta 4.9%; 0.010 percent of B; 0.05 percent of C; 0.020% of Zr; 0.1 percent of Fe; and the balance of Ni.
Experimental example 1
In order to illustrate the microstructure differences of the alloys prepared in the different examples and comparative examples, the microstructures of the alloys prepared in the respective examples and comparative examples were characterized, and the results are shown in Table 2.
TABLE 2 microstructure of different alloys
To further illustrate the high temperature creep properties and tensile properties of the alloys of the various examples and comparative examples, the following tests were conducted, with reference to HB5151 and HB5195, and the results are shown in tables 3-5, respectively.
TABLE 3 high temperature creep behaviour 750 ℃/620MPa
TABLE 4 high temperature creep Performance 815 ℃/400MPa
TABLE 5 tensile Property test results
From the above test results, the long-term service temperature of the wrought superalloy for a turbine disk of the present invention is increased to 750 ℃ or higher, and the short-term service temperature exceeds 800 ℃. In addition, the invention adopts a deformation high-temperature alloy process route for preparation, and has the advantages of short process flow, high purity, excellent comprehensive performance and acceptable cost.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The wrought superalloy for the turbine disk is characterized by comprising 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, 0.010 to 0.020 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.
2. The wrought superalloy for turbine disks according to claim 1, comprising the following components in mass percent:
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, 0.012 to 0.018 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;
preferably, the wrought superalloy for the turbine disk 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.
3. The wrought superalloy for turbine disks according to claim 1, wherein the mass fraction of B, zr, and C satisfies: (B + Zr)/C is 3-7;
and/or, hf is not included in the wrought superalloy for turbine disks.
4. The wrought superalloy for a turbine disk according to claim 1, wherein the sum of mass fractions of Al, ti, nb, and Ta is 10% to 13.5%;
and/or the sum of the mass fractions of Al and Ta is 6-8.5%;
and/or the mass fraction ratio of Al to Ta is 0.6-1;
and/or the mass fraction ratio of Ta and Ti is 1-1.7.
5. The wrought superalloy for a turbine disk according to any one of claims 1 to 4, wherein the sum of the mass fractions of Mo and W is 5.5% to 7.5%, preferably 6.5% to 7.5%;
and/or the mass fraction ratio of W to Mo is 1 to 1.8, preferably 1.5 to 1.8.
6. The method for preparing a wrought superalloy for a turbine disk according to any of claims 1 to 5, comprising the steps of:
(1) Preparing materials according to the deformed 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; and performing die forging forming on the blank, and then performing solution heat treatment and aging heat treatment.
7. The method of making a wrought superalloy for a turbine disk according to claim 6, wherein the solution heat treatment comprises: after heat preservation treatment at 1110-1160 ℃, cooling;
preferably, in the solution heat treatment, the time of the heat preservation treatment is 2-6 h; the cooling comprises any one of oil cooling, air cooling or high-pressure gas quenching;
and/or, the aging heat treatment comprises: after heat preservation treatment at 760-830 ℃, cooling;
preferably, in the aging heat treatment, the heat preservation time is 4-16 h; the cooling includes air cooling.
8. The method for preparing the wrought superalloy for the turbine disc according to claim 6, wherein the temperature of the high-temperature homogenization heat treatment is 1100-1200 ℃, and the holding time is more than or equal to 12 hours;
preferably, the high-temperature homogenization heat treatment includes: the heat preservation treatment is carried out for not less than 12 hours at 1100-1170 ℃, and then the heat preservation treatment is carried out for not less than 12 hours at 1170-1200 ℃.
9. The method of producing a wrought superalloy for a turbine disk according to claim 6, wherein the swaging comprises hot and/or isothermal forging;
and/or the temperature of die forging forming is 1080-1140 ℃.
10. The method for producing a wrought superalloy for a turbine disk according to claim 6, wherein in the wrought superalloy for a turbine disk, a γ' phase exhibits a trimodal distribution;
preferably, in the wrought superalloy for the turbine disc, the volume fraction of the primary gamma' phase is 10-15%, and the size is 0.3-7 μm; the volume fraction of the secondary gamma' phase is 18-25%, and the size is 40-300 nm; the volume fraction of the tertiary gamma' phase is 3-8%, and the size is less than 40nm;
and/or the deformed high-temperature alloy for the turbine disk further comprises an eta phase;
preferably, the volume fraction of the eta phase is 8-14%, and the size is 0.3-5 μm;
preferably, the wrought superalloy for a turbine disk has a grain structure of 6 to 9 grades.
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