CN113234963B - Nickel-chromium-based superalloy for room temperature and low temperature environment and preparation method thereof - Google Patents
Nickel-chromium-based superalloy for room temperature and low temperature environment and preparation method thereof Download PDFInfo
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 40
- 229910018487 Ni—Cr Inorganic materials 0.000 title claims abstract description 29
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 238000002360 preparation method Methods 0.000 title claims abstract description 14
- 239000000956 alloy Substances 0.000 claims abstract description 52
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 51
- 238000010438 heat treatment Methods 0.000 claims abstract description 27
- 230000032683 aging Effects 0.000 claims abstract description 13
- 238000005266 casting Methods 0.000 claims abstract description 5
- 238000005242 forging Methods 0.000 claims description 24
- 238000005097 cold rolling Methods 0.000 claims description 7
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 229910052719 titanium Inorganic materials 0.000 claims description 4
- 238000000265 homogenisation Methods 0.000 claims description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract description 16
- 239000007788 liquid Substances 0.000 abstract description 8
- 229910052757 nitrogen Inorganic materials 0.000 abstract description 8
- 229910018575 Al—Ti Inorganic materials 0.000 abstract description 3
- 238000001556 precipitation Methods 0.000 abstract description 3
- 238000001953 recrystallisation Methods 0.000 abstract description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 11
- 230000007797 corrosion Effects 0.000 description 8
- 238000005260 corrosion Methods 0.000 description 8
- 239000011651 chromium Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- 230000006698 induction Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 229910052759 nickel Inorganic materials 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910052793 cadmium Inorganic materials 0.000 description 2
- BDOSMKKIYDKNTQ-UHFFFAOYSA-N cadmium atom Chemical group [Cd] BDOSMKKIYDKNTQ-UHFFFAOYSA-N 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000013535 sea water Substances 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- JBNOVHJXQSHGRL-UHFFFAOYSA-N 7-amino-4-(trifluoromethyl)coumarin Chemical compound FC(F)(F)C1=CC(=O)OC2=CC(N)=CC=C21 JBNOVHJXQSHGRL-UHFFFAOYSA-N 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009713 electroplating Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 238000010587 phase diagram Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000001771 vacuum deposition Methods 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
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- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
Abstract
The invention discloses a nickel-chromium-based superalloy used in room temperature and low temperature environments and a preparation method thereof, wherein the superalloy is a Ni-Cr-Co-Al-Ti quinary alloy. The superalloy has a thermodynamically stable two-phase at the mid-temperature zone. The alloy is prepared by casting, cold deformation and low-temperature aging heat treatment, wherein under the conditions of cold deformation and low-temperature aging heat treatment, the prepared alloy has a double heterogeneous microstructure consisting of discontinuous precipitation of a precipitated phase and incomplete recrystallization, and under the condition of room temperature, the tensile plasticity of the prepared alloy reaches more than 10 percent, the yield strength can reach 1.7GPa, and the tensile strength can reach 1.75 GPa; under the condition of liquid nitrogen temperature, the tensile plasticity reaches more than 20 percent, the yield strength reaches 1.85GPa, and the tensile strength reaches more than 2.0 GPa.
Description
Technical Field
The invention belongs to the field of preparation of nickel-chromium-based alloy materials, and particularly provides a corrosion-resistant high-strength and high-toughness nickel-chromium-based superalloy used in room-temperature and low-temperature environments and a preparation method thereof.
Background
Before the middle of the 70 s, the standard fastener for aerospace adopts H-11 alloy (AMS6408), which is a variant of hot-work die steel, has tensile strength of more than 1500MPa on the premise of meeting the plasticity (tensile elongation not less than 8%) required by safe use of the fastener, can reach the strength level of 1800MPa at most, and meets the performance requirements of the fields of aerospace and the like on the fastener at that time. However, this series of alloys is essentially an iron-based alloy, and the chromium content is controlled to 5.0 mass% or less in order to achieve a high strength level, and therefore the series of alloys is inferior in corrosion resistance. In order to improve the corrosion resistance of the fastener, the low-brittleness cadmium fluoborate process is generally adopted for electroplating, and for the fastener requiring higher strength level, the vacuum deposition of cadmium or even the diffusion of nickel-cadmium is adopted, thereby greatly increasing the manufacturing cost. Even so, the protective effect of the coating on stress corrosion is poor, and pitting corrosion is easy to occur locally to become a cracked crack nucleation source, so that great potential safety hazard is brought. In addition, the treated fastener is not suitable for a seawater environment, and the seawater can damage the cadmium coating of the protective layer, thereby greatly limiting the application of the material in the field of fasteners.
In order to improve the service performance of a fastener, in the 80 s, the fastener industry began to develop a new generation of high-performance fastener material by using nickel-based superalloy with better corrosion resistance, GH4169 alloy with the most outstanding hardening capacity is selected to meet the requirement on high strength of the material, and the selected strengthening and toughening process is cold deformation with controllable strain capacity and low-temperature aging heat treatment, however, while the plasticity (tensile elongation not less than 8%) of the fastener is met, the tensile strength only reaches the level of 1500MPa, and only reaches the lower limit of the strength level of the fastener prepared from AMS6408 alloy. Therefore, the alloy system can only replace AMS6408 to prepare low-end fasteners of 1500MPa grade.
In order to meet the requirements of aerospace and high-performance missile development, cobalt-based alloys with higher performance are developed successively, wherein the representative alloys are multiphase MP35N and MP159, the alloys are strengthened by martensite phase transformation generated by cold deformation, and a special strengthening mechanism enables the alloys to obtain the tensile strength of more than 1800MPa while retaining good toughness. Of these, MP159 is the alloy used in the highest-grade aerospace fasteners today, and is the cobalt-based multi-phase alloy most widely used since the eighties. However, due to the special strengthening mechanism of the alloy, the pressure processing control requirement is very strict, and the processability of the material is poor. In addition, the nominal cobalt content of the alloy is 35.7 at.%, which is the highest content of elements in the alloy, and greatly increases the manufacturing cost of the alloy. Therefore, this alloy is limited to the manufacture of fasteners that are environmentally harsh.
In conclusion, the high-performance alloy which is moderate in cost, good in corrosion resistance (has corrosion resistance per se) and equivalent to AMS6408 alloy in strength is developed to expand the application of the high-performance alloy in the field of fasteners, and the high-performance alloy has important economic and academic values.
Disclosure of Invention
In view of the above, the present invention aims to provide a nickel-chromium-based superalloy used in room temperature and low temperature environments and a preparation method thereof, so as to improve the comprehensive mechanical properties of the nickel-based superalloy and achieve the level of AMS6408 series alloys.
The invention provides a nickel-chromium-based superalloy used in room temperature and low temperature environments, which comprises the following components in atomic percentage: cr: 24-26%, Co: 4.5-6%, Al: 3.0-3.5%, Ti: 3.0 to 3.5 percent, and the balance of Ni.
The invention also provides a preparation method of the nickel-chromium-based superalloy for the room temperature and low temperature environment, which comprises the following steps:
(1) preparing an alloy according to the components and the atomic percentages thereof in claim 1 and casting the alloy into an ingot;
(2) homogenizing the cast ingot, and then carrying out hot forging to obtain a forging piece;
(3) carrying out solution heat treatment on the forging to obtain an alloy with an FCC single phase;
(4) carrying out cold deformation with the deformation amount of 80-90% on the forge piece after the solution heat treatment;
(5) and carrying out low-temperature aging heat treatment on the forged piece after cold deformation to obtain the nickel-chromium-based superalloy for the room-temperature and low-temperature environment.
Preferably, in the step (2), the temperature of the homogenization treatment is 1150-1200 ℃, and the time is 10-12 h.
Further preferably, in the step (2), the temperature of the hot forging is 1000-1100 ℃, and the deformation amount of the forging is 50-60%.
Further preferably, in the step (3), the temperature of the solution heat treatment is 1150-1200 ℃, and the time is 2-4 h.
Further preferably, in the step (4), the cold deformation is performed by cold rolling or rotary forging at room temperature.
Further preferably, in the step (5), the temperature of the low-temperature aging heat treatment is 600-620 ℃, and the time is 24-28 h.
The nickel-chromium-based superalloy for room temperature and low temperature environments provided by the invention can obtain matrix grain structures and precipitate equal double uneven structures through the reasonable design of the components of Ni-Co-Cr-Al-Ti and the preparation process, so that the alloy can obtain excellent mechanical properties at room temperature and liquid nitrogen temperature. The alloy section can be processed into products in various forms, and has wide application in the production of fasteners used in the fields of aerospace, navigation and the like. The use of Ni, Cr, Al, Ti and a small amount of Co makes the alloy relatively cheap and the material preparation process simple. The industrial investment is low.
Drawings
The invention is described in further detail below with reference to the following figures and embodiments:
FIG. 1 is a phase diagram of a nickel-chromium-based superalloy for use in room temperature and low temperature environments provided by the present invention;
FIG. 2 is a structural diagram of grain inhomogeneity obtained by low temperature aging heat treatment of a nickel-chromium-based superalloy for use in room temperature and low temperature environments according to the present invention;
FIG. 3 is a diagram of the mechanical properties of the nickel-chromium-based superalloy for room temperature and low temperature environments provided by the present invention during the stretching process at room temperature and liquid nitrogen temperature.
Detailed Description
Conventional nickel-base superalloys are strengthened and strengthened mainly by deformation strengthening and precipitation strengthening, and have a significant trade-off effect between toughness and strength, so that the ability to increase strength while maintaining a certain plasticity is limited. In order to comprehensively improve the toughness of metal alloys, a 'preparation heterostructure engineering' is proposed in recent years, and a concept of 'back stress toughening' is introduced, namely a heterostructure with larger performance difference is prepared by adjusting the components of the alloy and controlling the preparation process of the alloy, extra geometrical necessary dislocation is generated by local non-uniform deformation in the deformation process, the strain hardening rate is improved by increasing the dislocation density, and further the comprehensive toughening in the deformation process is realized.
Based on the above concept, the invention provides a nickel-chromium-based superalloy used in room temperature and low temperature environments and a preparation method thereof.
The nickel-chromium-based superalloy used in the room temperature and low temperature environment comprises the following components in atomic percentage: cr: 24-26%, Co: 4.5-6%, Al: 3.0-3.5%, Ti: 3.0 to 3.5 percent, and the balance of Ni.
The preparation method of the nickel-chromium-based superalloy for the room temperature and low temperature environment comprises the following steps:
(1) preparing an alloy according to the components and the atomic percentages thereof in claim 1 and casting the alloy into an ingot;
(2) homogenizing the cast ingot, and then performing hot forging to obtain a forging, wherein preferably, the temperature of the homogenizing treatment is 1150-1200 ℃, the time is 10-12h, the temperature of the hot forging is 1000-1100 ℃, and the deformation of the forging is 50-60%;
(3) carrying out solution heat treatment on the forging to obtain an alloy with an FCC single phase, preferably, the temperature of the solution heat treatment is 1150-1200 ℃, and the time is 2-4 h;
(4) carrying out cold deformation with the deformation amount of 80-90% on the forge piece after the solution heat treatment, wherein the cold deformation is realized by cold rolling or rotary forging at room temperature;
(5) and (3) carrying out low-temperature aging heat treatment on the forged piece after cold deformation to obtain the nickel-chromium-based superalloy for the room-temperature and low-temperature environments, preferably, the temperature of the low-temperature aging heat treatment is 600-620 ℃, and the time is 24-28 h.
Example 1
Is prepared into Ni64Cr25Co5Al3Ti3(at.%) alloy is cast into 18Kg ingot by vacuum induction furnace, then the ingot is homogenized at 1200 ℃/12h, then hot forged at about 1000 ℃ to obtain forged piece, wherein the deformation of the forged piece is about 50%, then the forged piece is solution heat treated at 1200 ℃/2h to obtain (FCC) single-phase alloy with face-centered cubic structure, then the forged piece after solution heat treatment is cold deformed at 80% (cold rolling or rotary forging at room temperature), and finally the forged piece after cold deformation is low-temperature aged heat treated at 600 ℃/24h to obtain the nickel-chromium-based superalloy sample (sheet or bar) for room-temperature and low-temperature environment.
At 10-3s-1The obtained superalloy sample is stretched at the stretching rate, the stretching plasticity reaches more than 10 percent, the yield strength reaches more than 1700MPa, and the tensile strength reaches 1750GPa under the room temperature condition; under the condition of liquid nitrogen, the tensile plasticity reaches more than 20 percent, the yield strength reaches more than 1.85GPa, and the tensile strength reaches more than 2.0 GPa. The mechanical property is equivalent to AMS6408 series alloy.
Example 2
Is prepared into Ni62Cr25.5Co5.5Al3.5Ti3.5(at.%) alloy is cast into 18Kg ingot by vacuum induction furnace, then the ingot is homogenized at 1150 ℃/12h, then hot forged at about 1050 ℃ to obtain forged piece, wherein the deformation of the forged piece is about 60%, then the forged piece is solution heat treated at 1150 ℃/2h to obtain (FCC) single-phase alloy with face-centered cubic structure, then the forged piece after solution heat treatment is cold deformed at 90% (cold rolling or rotary forging at room temperature), and finally the forged piece after cold deformation is low-temperature aged heat treated at 610 ℃/26h to obtain the nickel-chromium-based superalloy sample (sheet or bar) for room-temperature and low-temperature environment.
At 10-3s-1The obtained superalloy sample is stretched at the stretching rate, the stretching plasticity reaches more than 10 percent, the yield strength reaches more than 1700MPa, and the tensile strength reaches 1750GPa under the room temperature condition; under the condition of liquid nitrogen, the tensile plasticity reaches more than 20 percent, the yield strength reaches more than 1.85GPa, and the tensile strength reaches more than 2.0 GPa. The mechanical property is equivalent to AMS6408 series alloy.
Example 3
Is prepared into Ni65Cr24.5Co4.5Al3Ti3(at.%) alloy is cast into 18Kg ingot by vacuum induction furnace, then the ingot is homogenized at 1200 ℃/12h, then hot forged at about 1000 ℃ to obtain forged piece, wherein the deformation of the forged piece is about 50%, then the forged piece is solution heat treated at 1200 ℃/2h to obtain (FCC) single-phase alloy with face-centered cubic structure, then the forged piece after solution heat treatment is cold deformed at 85% (cold rolling or rotary forging at room temperature), and finally the forged piece after cold deformation is low-temperature aged heat treated at 620 ℃/24h to obtain the nickel-chromium-based superalloy sample (sheet or bar) for room-temperature and low-temperature environment.
At 10-3s-1The obtained superalloy sample is stretched at the stretching rate, the stretching plasticity reaches more than 10 percent, the yield strength reaches more than 1700MPa, and the tensile strength reaches 1760 GPa; under the condition of liquid nitrogen, the tensile plasticity reaches more than 20 percent, the yield strength reaches more than 1.86GPa, and the tensile strength reaches more than 2.0 GPa. The mechanical property is equivalent to AMS6408 series alloy.
Example 4
Is prepared into Ni63Cr24Co6Al3.5Ti3.5(at.%) alloy is cast into 18Kg ingot by vacuum induction furnace, then the ingot is homogenized at 1180 ℃/12h, then hot forged at about 1100 ℃ to obtain forged piece, wherein the deformation of the forged piece is about 50%, then the forged piece is subjected to solution heat treatment at 1150 ℃/4h to obtain the alloy with face-centered cubic structureThe method comprises the following steps of (FCC) single-phase alloy forming, cold deformation (cold rolling or rotary forging at room temperature) with the deformation amount of 90% is carried out on the forging after solution heat treatment, and finally, low-temperature aging heat treatment of 600 ℃/28h is carried out on the forging after cold deformation to obtain the nickel-chromium-based superalloy sample (sheet or bar) for room temperature and low temperature environments.
At 10-3s-1The obtained superalloy sample is stretched at the stretching rate, the stretching plasticity reaches more than 10 percent under the room temperature condition, the yield strength reaches more than 1720MPa, and the tensile strength reaches 1770 GPa; under the condition of liquid nitrogen, the tensile plasticity reaches more than 20 percent, the yield strength reaches more than 1.88GPa, and the tensile strength reaches more than 2.0 GPa. The mechanical property is equivalent to AMS6408 series alloy.
The nickel-chromium-based superalloy for room temperature and low temperature environments provided by the invention is a Ni-Cr-Co-Al-Ti quinary alloy. As shown in FIG. 1, the alloy has two thermodynamically stable phases in the intermediate temperature range (the matrix is a ductile phase with a face-centered cubic structure, and the reinforcing phase is L1)2Ordered phases of structure). The alloy is prepared by fusion casting, cold deformation and low temperature aging heat treatment, wherein under the conditions of cold deformation and low temperature aging heat treatment, the prepared alloy has a double heterogeneous microstructure (shown in figure 2) due to discontinuous precipitation of precipitated phases and incomplete recrystallization composition. As shown in FIG. 3, under the condition of room temperature, the prepared alloy has the tensile plasticity of more than 10 percent, the yield strength of 1.7GPa and the tensile strength of 1.75 GPa; under the condition of liquid nitrogen temperature, the tensile plasticity reaches more than 20 percent, the yield strength reaches 1.85GPa, and the tensile strength reaches more than 2.0 GPa. The mechanical property is equivalent to AMS6408 series alloy.
Claims (5)
1. The nickel-chromium-based superalloy used at room temperature and in low-temperature environments is characterized by comprising the following components in atomic percentage: cr: 24-26%, Co: 4.5-6%, Al: 3.0-3.5%, Ti: 3.0-3.5% and the balance of Ni, wherein the preparation method of the nickel-chromium-based superalloy for the room temperature and low temperature environment comprises the following steps:
(1) preparing alloy according to the components and the atomic percentage thereof, and casting the alloy into an ingot;
(2) homogenizing the cast ingot, and then carrying out hot forging to obtain a forging piece;
(3) carrying out solution heat treatment on the forging to obtain an alloy with an FCC single phase;
(4) carrying out cold deformation with the deformation amount of 80-90% on the forge piece after the solution heat treatment;
(5) and carrying out low-temperature aging heat treatment on the forged piece after cold deformation to obtain the nickel-chromium-based superalloy for the room temperature and low-temperature environment, wherein the temperature of the low-temperature aging heat treatment is 600-620 ℃, and the time is 24-28 h.
2. The nickel-chromium-based superalloy for use in ambient and low temperature environments of claim 1, wherein: in the step (2), the temperature of the homogenization treatment is 1150-1200 ℃, and the time is 10-12 h.
3. The nickel-chromium-based superalloy for use in ambient and low temperature environments of claim 1, wherein: in the step (2), the temperature of the hot forging is 1000-1100 ℃, and the deformation of the forging is 50-60%.
4. The nickel-chromium-based superalloy for use in ambient and low temperature environments of claim 1, wherein: in the step (3), the temperature of the solution heat treatment is 1150-1200 ℃, and the time is 2-4 h.
5. The nickel-chromium-based superalloy for use in ambient and low temperature environments of claim 1, wherein: in the step (4), the cold deformation is realized by cold rolling or rotary forging at room temperature.
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| CN114686664B (en) * | 2022-02-28 | 2023-03-07 | 东北大学 | Composite preparation method of high-strength D6A fine-grained steel |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111036810A (en) * | 2019-12-11 | 2020-04-21 | 贵州航宇科技发展股份有限公司 | High-temperature alloy forging and heat treatment method |
| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
| CN111549259A (en) * | 2020-05-25 | 2020-08-18 | 中国科学院金属研究所 | Nickel-cobalt-based high-temperature alloy turbine disc and preparation method thereof |
| CN111575535A (en) * | 2020-05-14 | 2020-08-25 | 张家港广大特材股份有限公司 | Nickel-based high-temperature alloy and preparation method thereof |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4810695B1 (en) * | 1969-10-11 | 1973-04-06 | ||
| US4140555A (en) * | 1975-12-29 | 1979-02-20 | Howmet Corporation | Nickel-base casting superalloys |
| GB2024858B (en) * | 1978-07-06 | 1982-10-13 | Inco Europ Ltd | Hightemperature nickel-base alloys |
| US4261742A (en) * | 1978-09-25 | 1981-04-14 | Johnson, Matthey & Co., Limited | Platinum group metal-containing alloys |
| JPS6237334A (en) * | 1985-08-12 | 1987-02-18 | Hitachi Ltd | Ni alloy |
| JP2860260B2 (en) * | 1995-01-09 | 1999-02-24 | 株式会社神戸製鋼所 | High corrosion resistance Ni-based alloy |
| US8066938B2 (en) * | 2004-09-03 | 2011-11-29 | Haynes International, Inc. | Ni-Cr-Co alloy for advanced gas turbine engines |
| CN101072887A (en) * | 2004-12-02 | 2007-11-14 | 独立行政法人物质·材料研究机构 | Heat-resistant superalloy |
| FR2886182B1 (en) * | 2005-05-26 | 2009-01-30 | Snecma Services Sa | SUPERALLIAGE POWDER |
| CN102605214A (en) * | 2012-03-27 | 2012-07-25 | 宝山钢铁股份有限公司 | Novel nickel-base alloy for vent valve of combustion engine |
| CN103361518B (en) * | 2013-06-11 | 2015-04-08 | 太原钢铁(集团)有限公司 | Nickel-based seamless pipe for ultra supercritical boiler and manufacturing method thereof |
| EP3543369B8 (en) * | 2016-11-16 | 2022-08-03 | Mitsubishi Heavy Industries, Ltd. | Method for producing nickel-based alloy high temperature material |
| CN106623959A (en) * | 2016-12-19 | 2017-05-10 | 西安欧中材料科技有限公司 | Preparation method of Waspalloy spherical powder for additive manufacturing |
| JP6842316B2 (en) * | 2017-02-17 | 2021-03-17 | 日本製鋼所Ｍ＆Ｅ株式会社 | Manufacturing method of Ni-based alloy, gas turbine material and Ni-based alloy with excellent creep characteristics |
| CN111074100A (en) * | 2019-12-31 | 2020-04-28 | 江苏新华合金有限公司 | Nickel-based high-temperature alloy bar and preparation method thereof |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111036810A (en) * | 2019-12-11 | 2020-04-21 | 贵州航宇科技发展股份有限公司 | High-temperature alloy forging and heat treatment method |
| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
| CN111575535A (en) * | 2020-05-14 | 2020-08-25 | 张家港广大特材股份有限公司 | Nickel-based high-temperature alloy and preparation method thereof |
| CN111549259A (en) * | 2020-05-25 | 2020-08-18 | 中国科学院金属研究所 | Nickel-cobalt-based high-temperature alloy turbine disc and preparation method thereof |
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