CN115821181A - Thermal mechanical treatment method of nickel-chromium-cobalt alloy - Google Patents
Thermal mechanical treatment method of nickel-chromium-cobalt alloy Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 36
- 229910000531 Co alloy Inorganic materials 0.000 title claims abstract description 24
- SZMZREIADCOWQA-UHFFFAOYSA-N chromium cobalt nickel Chemical compound [Cr].[Co].[Ni] SZMZREIADCOWQA-UHFFFAOYSA-N 0.000 title claims abstract description 22
- 238000010438 heat treatment Methods 0.000 claims abstract description 39
- 238000001816 cooling Methods 0.000 claims abstract description 29
- 238000005266 casting Methods 0.000 claims abstract description 20
- 230000032683 aging Effects 0.000 claims abstract description 16
- 238000001953 recrystallisation Methods 0.000 claims abstract description 12
- 239000006104 solid solution Substances 0.000 claims abstract description 10
- 239000013078 crystal Substances 0.000 claims abstract description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 8
- 230000000930 thermomechanical effect Effects 0.000 claims description 12
- 239000000126 substance Substances 0.000 claims description 10
- 239000000243 solution Substances 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 2
- 239000011651 chromium Substances 0.000 claims description 2
- 239000012535 impurity Substances 0.000 claims description 2
- 229910052750 molybdenum Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 7
- 239000000956 alloy Substances 0.000 abstract description 7
- 229910052759 nickel Inorganic materials 0.000 abstract description 3
- 238000005242 forging Methods 0.000 description 40
- 238000007599 discharging Methods 0.000 description 12
- 239000000463 material Substances 0.000 description 5
- 239000000203 mixture Substances 0.000 description 4
- 239000002244 precipitate Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Abstract
The invention relates to a thermal mechanical treatment method of a nickel-chromium-cobalt alloy, belonging to the technical field of nickel-based high-temperature alloys. The method comprises the following steps: (1) hot processing: heating the casting blank to 1120 +/-10 ℃, and carrying out thermal processing deformation with the deformation amount of 10-15%; (2) and (3) recrystallization: heating the blank to 1160 +/-10 ℃ along with the furnace, and carrying out recrystallization treatment to obtain a blank with ASTM 3-5 grade crystal grains; (3) thermal deformation: deforming at 1110 +/-20 deg.c to total deformation of 70-90%, and air cooling to room temperature; (4) solid solution aging treatment: keeping the temperature at 1100 +/-10 ℃ for 8-9 h, quickly cooling to 860 +/-10 ℃ and keeping the temperature for 15-16 h, and then cooling in air. The nickel-chromium-cobalt alloy obtained by the invention has good plasticity and higher strength at room temperature and high temperature, and has better durability and creep resistance.
Description
Technical Field
The invention belongs to the technical field of nickel-based high-temperature alloys, and relates to a thermal mechanical treatment method of a nickel-chromium-cobalt alloy.
Background
The nickel-based high-temperature alloy has excellent service performance and is widely applied to key parts of an aeroengine, such as a combustion chamber, a turbine disc, a blade and the like. In recent years, with the continuous development of the aviation industry in China, the requirement on the high-temperature performance of the aviation material is increasingly improved, the material is required to have certain endurance strength, creep strength, thermal fatigue strength and corresponding toughness at high temperature, the high-temperature physical and chemical properties are closely related to the composition phase and the precipitate of the material, and the deformation and heat treatment process determine the composition phase and the precipitate of the material.
The conventional processing method of nickel-base high-temperature alloy is that casting blank is homogenized, rolled (forged), and subjected to solid solution and aging (depending on components) to reach the use standard, and the process is long and the cost is high. In fact, the steps of homogenization, rolling (forging), and the like are all performed at high temperatures, so that a thermomechanical treatment method can be designed to accomplish the strengthening process by skillfully controlling the dislocation substructure formed during deformation.
Disclosure of Invention
In order to solve the technical problems, the invention provides a thermal mechanical treatment method of a nickel-chromium-cobalt alloy, which is used for improving the strength and the fatigue life of the material.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows: a nickel chromium cobalt alloy thermal mechanical treatment method comprises the working procedures of hot working, recrystallization, thermal deformation and solution aging treatment;
(1) A hot processing procedure: heating the casting blank to 1120 +/-10 ℃, and performing hot working deformation, wherein the total deformation amount is 10-15%;
(2) A recrystallization step: charging the blank subjected to hot processing deformation into a furnace while the blank is hot, heating to 1160 +/-10 ℃ along with the furnace, and preserving heat for 20-50 h to obtain a blank of ASTM 3-5 grade crystal grains;
(3) A thermal deformation process: thermally deforming the blank at 1110 +/-20 ℃ until the total deformation is 70-90%, and then air-cooling to room temperature;
(4) Solid solution aging treatment: heating the blank to 1110 +/-10 ℃, preserving heat for 8-9 h, quickly cooling to 860 +/-10 ℃, preserving heat for 15-16 h, and finally air cooling to room temperature.
In the hot processing procedure, the casting blank is heated to 760 +/-10 ℃ and is kept warm for 2-4 h, then is heated to 1120 +/-10 ℃ at the speed of 1-2 ℃/min and is kept warm for [ (3-5) x the diameter or thickness (mm) ] min.
In the solution and aging treatment process, the blank is heated to 760 +/-10 ℃ and is kept warm for 1-2 h, and then is heated to 1110 +/-10 ℃ at a speed of 5 ℃/min.
In the solution aging treatment process, the time for rapidly cooling the blank from 1110 +/-10 ℃ to 860 +/-10 ℃ is 0.5-1 h.
The nickel-chromium-cobalt alloy comprises the following chemical components in percentage by mass: 0.05 to 0.10 percent of C, less than or equal to 0.25 percent of Mn, less than or equal to 0.25 percent of Si, less than or equal to 0.006 percent of S, less than or equal to 0.010 percent of P, 18 to 20 percent of Cr, 17 to 19 percent of Co, 3.7 to 4.2 percent of Mo, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, and the balance of Ni and inevitable impurities.
The nickel-chromium-cobalt alloy obtained by the method meets the requirement of tensile strength sigma under the normal temperature condition b :1146 to 1486MPa, yield strength sigma 0.2 :786 to 1045MPa and the impact toughness of 186 to 245a K /kJ/m 2 (ii) a Tensile strength sigma at 600 deg.C b : 1053-1380 MPa, yield strength sigma 0.2 :737 to 963MPa; the creep property is 0.8-1.4% under the condition of 750 ℃ and 375MPa and the creep time is 300 h.
Adopt the produced beneficial effect of above-mentioned technical scheme to lie in: the invention can lead the nickel-chromium-cobalt high-temperature alloy matrix to have good tissue morphology, the alloy deforms under the process and can slide uniformly and dispersedly, and finally a polygon dislocation substructure is formed, thus greatly improving the room temperature and high temperature performance of the alloy.
Detailed Description
Example 1
The chemical components and mass percentages of the nickel-chromium-cobalt alloy electroslag ingot with the diameter of 350 × 1200mm in the embodiment are shown in table 7, and the thermo-mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating the casting blank to 760 ℃ for 3h, preserving heat for 3h, heating the casting blank to 1130 ℃ for 4h, and preserving heat for 1400min; discharging from a furnace and forging, wherein the finish forging temperature is 1110 ℃, and forging into square billets with the specification of 290 x 290mm after 4-fire forging, wherein the total deformation is 10%;
2) And (3) recrystallization: putting a 290mm square billet into a furnace while the square billet is hot, heating to 1160 ℃, and preserving heat for 32 hours to obtain ASTM grade 4 crystal grains;
3) Thermal deformation: discharging 290 x 290mm square billets out of a furnace, forging at 1090-1130 ℃, forging by 14 fire to obtain a plurality of round rods with the specification of phi 100 x 1500mm, wherein the total deformation is 70 percent, and cooling in air to room temperature;
4) Solid solution aging treatment: charging round bar stock into a furnace, heating to 760 ℃ within 2h, preserving heat for 1.5h, heating to 1110 ℃ and preserving heat for 8h, cooling to 860 ℃ within 45min, preserving heat for 15.5h, and finally air cooling.
After the processing of the procedures, the performance of the round bar is detected, and the results are as follows:
tables 1 to 1: example 1 tensile and impact Properties of the test specimens
Tables 1 to 2: EXAMPLE 1 sample durability
Tables 1 to 3: example 1 creep performance of test specimens
Tables 1 to 4: example 1 sample fatigue Properties
Example 2
The chemical components and mass percentages of the nickel-chromium-cobalt alloy electroslag ingot with phi of 220 multiplied by 1500mm in the embodiment are shown in table 7, and the thermo-mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating the casting blank to 770 ℃ for 3h, preserving heat for 2h, heating the casting blank to 1130 ℃ for 3h, and preserving heat for 660min; discharging from a furnace and forging, wherein the finish forging temperature is 1110 ℃, and forging into square billets with the specification of 180 x 180mm after 4-fire forging, wherein the total deformation is 15%;
2) And (3) recrystallization: putting a square billet of 180 x 180mm into a furnace while the billet is hot, heating to 1170 ℃, and preserving heat for 20 hours to obtain ASTM grade 5 crystal grains;
3) Thermal deformation: discharging 180 x 180mm square billets out of a furnace, forging at 1090-1130 ℃, forging into a plurality of round rods with the specification of phi 90 x 1500mm through 12-fire forging, wherein the total deformation is 90%, and air cooling to room temperature;
4) Solid solution aging treatment: charging the round blank into a furnace, heating to 770 ℃ within 2h, preserving heat for 1h, heating to 1100 ℃, preserving heat for 8.5h, cooling to 850 ℃ within 30min, preserving heat for 15h, and finally air cooling.
After the processing of the procedures, the performance of the round bar is detected, and the results are as follows:
table 2-1: example 2 tensile and impact Properties of the test specimens
Tables 2 to 2: EXAMPLE 2 sample durability
Tables 2 to 3: example 2 creep performance of test specimens
Tables 2 to 4: example 2 sample fatigue Properties
Example 3
The chemical components and mass percentages of the nickel-chromium-cobalt alloy electroslag ingot with the diameter of 450 multiplied by 1000mm in the embodiment are shown in table 7, and the thermo-mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating the casting blank to 750 ℃ for 5h, preserving heat for 4h, then heating the casting blank to 1130 ℃ for 5h, and preserving heat for 2250min; discharging from a furnace and forging, wherein the final forging temperature is 1110 ℃, and forging the blank into a square billet with the specification of 380 multiplied by 380mm after 6 fire, wherein the total deformation is 15%;
2) And (3) recrystallization: putting a square billet of 380mm multiplied by 380mm into a furnace while the square billet is hot, heating to 1170 ℃, and preserving heat for 50h to obtain ASTM grade 3 crystal grains;
3) Thermal deformation: discharging a 380 multiplied by 380mm square billet out of a furnace, forging the square billet at the temperature of 1090-1130 ℃, forging the square billet into a 210 multiplied by 210mm billet with the total deformation of 80 percent through 22-fire forging, and cooling the square billet in air to room temperature;
4) Solid solution aging treatment: charging the blank, heating to 750 ℃ within 4h, preserving heat for 2h, heating to 1120 ℃ within 9h, cooling to 870 ℃ within 1h, preserving heat for 16h, and finally air cooling.
After the processing of the procedures, the performance of the round bar is detected, and the results are as follows:
table 3-1: example 3 tensile and impact Properties of the test specimens
Tables 3-2: EXAMPLE 3 sample durability
Tables 3 to 3: example 3 creep Properties of test specimens
Tables 3 to 4: example 3 sample fatigue Properties
Example 4
The chemical components and mass percentages of the 220 × 360 × 1300mm ni-cr-co alloy electroslag ingot of this embodiment are shown in table 7, and the thermo-mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating the casting blank to 760 ℃ for 3h, preserving heat for 3h, heating the casting blank to 1130 ℃ for 4h, and preserving heat for 1440min; discharging from a furnace and forging, wherein the final forging temperature is 1110 ℃, and forging into a flat blank with the specification of 300 multiplied by 220mm after 4-fire forging, wherein the total deformation is 12%;
2) And (3) recrystallization: putting a flat blank with the size of 300 multiplied by 220mm into a furnace while the flat blank is hot, heating to 1150 ℃, and preserving heat for 28 hours to obtain ASTM grade 4 crystal grains;
3) Thermal deformation: discharging a 300 x 220mm flat blank out of a furnace, forging the flat blank at 1090-1130 ℃, forging the flat blank into a plurality of round bars with the specification of phi 100 x 1500mm through 16-fire forging, wherein the total deformation is 75 percent, and cooling the round bars to room temperature;
4) Solid solution aging treatment: charging the round blank into a furnace, heating to 760 ℃ within 2h, preserving heat for 1.5h, heating to 1110 ℃ and preserving heat for 8h, cooling to 860 ℃ within 45min, preserving heat for 16h, and finally air cooling.
After the processing of the procedures, the performance of the round bar is detected, and the results are as follows:
TABLE 4-1: example 4 tensile and impact Properties of the samples
Tables 4-2: EXAMPLE 4 sample durability
Tables 4 to 3: example 4 creep Properties of test specimens
Tables 4 to 4: example 4 sample fatigue Properties
Example 5
The chemical components and the mass percentage content of the nickel-chromium-cobalt alloy electroslag ingot with the diameter phi of 150 multiplied by 800mm in the embodiment are shown in a table 7, and the thermal mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating to 760 ℃ for 3h, preserving heat for 3h, heating to 1120 ℃ for 4h, and preserving heat for 500min; discharging from a furnace and forging, wherein the finish forging temperature is 1110 ℃, and after 3 times of forging, forging into a square billet with the specification of 100 multiplied by 100mm, wherein the total deformation is 14%;
2) And (3) recrystallization: putting a square billet with the diameter of 100 multiplied by 100mm into a furnace while the square billet is hot, heating to 1160 ℃, and preserving heat for 30 hours to obtain ASTM grade 4 crystal grains;
3) Thermal deformation: discharging a square billet of 100 x 100mm out of a furnace, forging the square billet at the temperature of 1090-1130 ℃, forging the square billet into a plurality of round rods with the specification of phi 60 x 800mm through 8-fire forging, wherein the total deformation is 85 percent, and cooling the round rods to room temperature;
4) Solid solution aging treatment: and charging the round bar stock into a furnace, heating to 760 ℃ within 2h, preserving heat for 1h, heating to 1110 ℃ and preserving heat for 9h, cooling to 850 ℃ within 30min, preserving heat for 15h, and finally air cooling.
Table 5-1: example 5 tensile and impact Properties of the test specimens
Tables 5-2: EXAMPLE 5 sample durability
Tables 5 to 3: example 5 creep Performance of test specimens
Tables 5 to 4: example 5 sample fatigue Properties
Example 6
In this embodiment, the chemical compositions and mass percentages of 320 × 500 × 1500mm ni-cr-co alloy electroslag ingot are shown in table 7, and the thermo-mechanical treatment steps are as follows:
1) Hot processing: after the casting blank is put into a furnace, heating to 760 ℃ for 3h, preserving heat for 4h, heating to 1110 ℃ for 4h, and preserving heat for 1560min; discharging from a furnace and forging, wherein the final forging temperature is 1110 ℃, and forging the blank into a flat blank with the specification of 400 multiplied by 300mm after 6 fire, wherein the total deformation is 10%;
2) And (3) recrystallization: putting a flat blank with the size of 400 multiplied by 300mm into a furnace while the flat blank is hot, heating to 1160 ℃, and preserving heat for 35 hours to obtain ASTM grade 5 crystal grains;
3) Thermal deformation: discharging 400 x 300mm flat billets out of a furnace, forging the flat billets at the temperature of 1090-1130 ℃, forging the flat billets into a plurality of round rods with the specification of phi 150 x 1500mm through 22-fire forging, wherein the total deformation is 90 percent, and air cooling the round rods to room temperature;
4) Solid solution aging treatment: charging round bar stock into a furnace, heating to 760 ℃ within 2h, preserving heat for 2h, heating to 1110 ℃ and preserving heat for 8h, cooling to 850 ℃ within 55min, preserving heat for 16h, and finally air cooling.
Table 6-1: EXAMPLE 6 tensile and impact Properties of the test specimens
Tables 6-2: EXAMPLE 6 sample durability
Tables 6 to 3: example 6 creep Performance of test specimens
Tables 6 to 4: example 6 sample fatigue Properties
Table 7: chemical composition and content (wt%) of Ni-Cr-Co alloy in each example
Claims (6)
1. A method for thermo-mechanical treatment of a nickel chromium cobalt alloy is characterized by comprising the following steps: comprises the working procedures of hot working, recrystallization, thermal deformation and solution aging treatment;
(1) A hot processing procedure: heating the casting blank to 1120 +/-10 ℃, and performing hot working deformation, wherein the total deformation amount is 10-15%;
(2) A recrystallization step: charging the blank subjected to hot processing deformation into a furnace while the blank is hot, heating to 1160 +/-10 ℃ along with the furnace, and preserving heat for 20-50 h to obtain a blank of ASTM 3-5 grade crystal grains;
(3) A thermal deformation process: thermally deforming the blank at 1110 +/-20 ℃ until the total deformation is 70-90%, and then air-cooling to room temperature;
(4) Solid solution aging treatment: heating the blank to 1110 +/-10 ℃, preserving heat for 8-9 h, quickly cooling to 860 +/-10 ℃, preserving heat for 15-16 h, and finally air cooling to room temperature.
2. The method of thermomechanical treatment of a nickel chromium cobalt alloy according to claim 1, characterized in that: in the hot processing procedure, the casting blank is heated to 760 +/-10 ℃ and is kept warm for 2-4 h, then is heated to 1120 +/-10 ℃ at the speed of 1-2 ℃/min and is kept warm for [ (3-5) x the diameter or thickness (mm) ] min.
3. The method of thermomechanical treatment of a nickel chromium cobalt alloy according to claim 2, characterized in that: in the solution aging treatment process, the blank is heated to 760 +/-10 ℃ and is kept for 1 to 2 hours, and then is heated to 1110 +/-10 ℃ at the speed of 5 ℃/min.
4. A method for the thermomechanical treatment of a nickel chromium cobalt alloy according to claim 3, characterized in that: in the solution aging treatment process, the time for rapidly cooling the blank from 1110 +/-10 ℃ to 860 +/-10 ℃ is 0.5-1 h.
5. The method for the thermomechanical treatment of a nickel chromium cobalt alloy according to any of claims 1 to 4, characterized in that: the nickel-chromium-cobalt alloy comprises the following chemical components in percentage by mass: 0.05 to 0.10 percent of C, less than or equal to 0.25 percent of Mn, less than or equal to 0.25 percent of Si, less than or equal to 0.006 percent of S, less than or equal to 0.010 percent of P, 18 to 20 percent of Cr, 17 to 19 percent of Co, 3.7 to 4.2 percent of Mo, 2.5 to 3.5 percent of Al, 2.5 to 3.5 percent of Ti, and the balance of Ni and inevitable impurities.
6. The method of claim 5, wherein the thermomechanical treatment of a nickel chromium cobalt alloy is performed by: the nickel-chromium-cobalt alloy obtained by the method meets the tensile strength sigma under the condition of normal temperature b :1146 to 1486MPa, yield strength sigma 0.2 :786 to 1045MPa and the impact toughness of 186 to 245a K /kJ/m 2 (ii) a Tensile strength sigma at 600 deg.C b : 1053-1380 MPa, yield strength sigma 0.2 :737 to 963MPa; the creep property is 0.8-1.4% under the condition of 750 ℃ and 375MPa and the creep time is 300 h.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108893689A (en) * | 2018-06-20 | 2018-11-27 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Inconel718 alloy disc forging homogenizes manufacturing method |
| CN111020298A (en) * | 2019-12-23 | 2020-04-17 | 西部超导材料科技股份有限公司 | GH3039 high-temperature alloy bar and preparation method thereof |
| CN111471897A (en) * | 2020-05-08 | 2020-07-31 | 华能国际电力股份有限公司 | Preparation and forming process of high-strength nickel-based high-temperature alloy |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108893689A (en) * | 2018-06-20 | 2018-11-27 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Inconel718 alloy disc forging homogenizes manufacturing method |
| CN111020298A (en) * | 2019-12-23 | 2020-04-17 | 西部超导材料科技股份有限公司 | GH3039 high-temperature alloy bar and preparation method thereof |
| CN111471897A (en) * | 2020-05-08 | 2020-07-31 | 华能国际电力股份有限公司 | Preparation and forming process of high-strength nickel-based high-temperature alloy |
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