CN104404348B - A kind of nickel-aluminum base alloy and its preparation method - Google Patents
A kind of nickel-aluminum base alloy and its preparation method Download PDFInfo
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- CN104404348B CN104404348B CN201410720802.XA CN201410720802A CN104404348B CN 104404348 B CN104404348 B CN 104404348B CN 201410720802 A CN201410720802 A CN 201410720802A CN 104404348 B CN104404348 B CN 104404348B
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 71
- 239000000956 alloy Substances 0.000 title claims abstract description 71
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 title claims abstract description 44
- 238000002360 preparation method Methods 0.000 title claims abstract description 16
- 229910052751 metal Inorganic materials 0.000 claims abstract description 35
- 239000002184 metal Substances 0.000 claims abstract description 35
- 238000010792 warming Methods 0.000 claims abstract description 30
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 18
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 16
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 14
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 12
- 229910052796 boron Inorganic materials 0.000 claims abstract description 12
- 229910052702 rhenium Inorganic materials 0.000 claims abstract description 12
- 230000006835 compression Effects 0.000 claims description 25
- 238000007906 compression Methods 0.000 claims description 25
- 238000013019 agitation Methods 0.000 claims description 20
- 230000006698 induction Effects 0.000 claims description 12
- 239000000203 mixture Substances 0.000 claims description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 8
- 238000009413 insulation Methods 0.000 claims description 8
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 4
- 238000005728 strengthening Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000003756 stirring Methods 0.000 abstract 2
- 229910000943 NiAl Inorganic materials 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 208000035126 Facies Diseases 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000407 epitaxy Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Forging (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The present invention discloses a kind of nickel-aluminum base alloy and its preparation method, and preparation process is as follows: Ni, Cr, Co are put into crucible, and Al, Ta, Ni-B, Re are suspended on above crucible, are evacuated to 2��4 �� 10-3Pa; Energising fusing Ni, Cr, Co metal block, is warming up to 1560��1600 DEG C, stirs evenly; Put into Ta, Ni-B, Al, Re metal block respectively, it is warming up to 1560��1600 DEG C, stir evenly; At 1560��1600 DEG C, pouring metal melt is become alloy bar; By alloy bar solution treatment 2 times, obtain nickel-aluminum base alloy. The nickel-aluminum base alloy of the present invention with the addition of B, Ta, Cr, Re and Co as strengthening element, nickel-aluminum base alloy is excellent in the compressive strength of room temperature to 600 DEG C, plasticity and hardness, have a good application prospect, and preparation method's technique of nickel-aluminum base alloy is simple, be easy to realize, it is possible to be applicable to industrial mass manufacture.
Description
Technical field
The present invention relates to alloy field, in particular to a kind of nickel-aluminum base alloy and its preparation method.
Background technology
Intermetallic compound NiAl is desirable high-temperature structural material, the advantage such as antioxidant property with high-melting-point (1640 DEG C), high thermal conductivity (70��80W/m K), low density (5.86g/cm3) and excellence. But, temperature-room type plasticity is poor, room temperature fracture resistance is low and hot strength is not enough and the anti-power of high temperature creep is low etc., and problem governs the practicalization of NiAl for structural component materials always. For many years, people are from alloying, and in preparation, angle that is raw and external matrix material is set out, and adopts the methods such as solution strengthening, second-phase strength, oxide dispersion intensifying (ODS), it is to increase the high temperature resistance intensity of NiAl alloy epitaxy and room temperature compression plasticity.
During room temperature compression experiment, NiAl has the compression true strain of about 0.05, and compressive strength is about 650MPa; Along with the rising of temperature, decrease in intensity, plasticity increases, and 400 DEG C of compressive strengths are about 500MPa, and compression true strain is about 0.15. Adding the compression true strain that 0.5��10at.%Ag, NiAl-Ag have 0.07��0.12, compressive strength is 750��900MPa; Along with the rising of temperature, decrease in intensity, plasticity increases, and 400 DEG C of compressive strengths are about 420��600MPa, and compression true strain is about 0.10��0.15.
The NiAl-Ta system alloy of people's research and development such as Zeumer and Sauthoff of Ma Pu institute of Germany, has good mechanical property, and this alloy has good application prospect, the NiAl-2.5Ta-7.5Cr excellent property that particularly they prepare. But existing complicated process of preparation, cost height.
Summary of the invention
In order to solve the problems of the technologies described above, the present invention provides a kind of and has high compression-strength and the nickel-aluminum base alloy of high compression plasticity, and provides the preparation method of nickel-aluminum base alloy.
The technical scheme that the present invention solves the problem is: a kind of nickel-aluminum base alloy, its composition is NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re, and namely the atomic percent of Ni, Al, Ta, Cr, Co, B, Re is 32.75:32.75:2.5:7.5:15:2:7.5.
In above-mentioned nickel-aluminum base alloy, under room temperature, the Vickers' hardness of nickel-aluminum base alloy is 650��663HV, and ultimate compression strength is 1300��1390MPa, and true strain is 0.60��0.80; At 300 DEG C, the ultimate compression strength of nickel-aluminum base alloy is 1250��1290MPa, and true strain is 0.25��0.27; At 600 DEG C, the ultimate compression strength of nickel-aluminum base alloy is 1550��1620MPa, and true strain is 0.32��0.38.
A preparation method for nickel-aluminum base alloy, comprises the following steps:
1) melting in vacuum induction furnace, puts into Ni, Cr, Co in the crucible of vacuum induction furnace, and Al, Ta, Ni-B, Re Al silk system is firmly suspended on above crucible, and being evacuated to vacuum tightness in vacuum induction furnace is 2��4 �� 10-3Pa;
2) energising fusing Ni, Cr, Co metal block, the molten metal temperature being warming up to fusing reaches 1560��1600 DEG C, and magnetic agitation makes molten metal composition even;
3) putting into Al silk system Ta metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Ni-B metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Al metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Re metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even;
4) by step 3 at 1560��1600 DEG C of temperature) pouring metal melt of gained becomes alloy bar;
5) alloy bar is put into vacuum molybdenum wire furnace, it is evacuated to 5��8 �� 10-3Pa, is warming up to 1350 DEG C of insulations 12 hours, and heat-up rate is 10��15 DEG C/min, and stove is cold;
6) vacuum molybdenum wire furnace is evacuated to 5��8 �� 10-3Pa, is warming up to 1150 DEG C of insulations 12 hours, and heat-up rate is 10��15 DEG C/min, and stove is cold, obtains nickel-aluminum base alloy.
In the preparation method of above-mentioned nickel-aluminum base alloy, described step 4) in the diameter of alloy bar be 30 millimeters.
The useful effect of the present invention is: the nickel-aluminum base alloy of the present invention with the addition of B, Ta, Cr, Re and Co as strengthening element, nickel-aluminum base alloy is excellent in the compressive strength of room temperature to 600 DEG C, plasticity and hardness, it is have a good application prospect under the applying working condition of stress in load, and preparation method's technique of nickel-aluminum base alloy is simple, be easy to realize, it is possible to be applicable to industrial mass manufacture.
Accompanying drawing explanation
Fig. 1 is tissue topography and the facies analysis figure of nickel-aluminum base alloy, and in figure, a is SEM shape appearance figure, and b is X diffracting spectrum.
Fig. 2 is nickel-aluminum base alloy true stress-true strain analysis chart at room temperature.
Fig. 3 is the true stress-true strain analysis chart of nickel-aluminum base alloy at 300 DEG C.
Fig. 4 is the true stress-true strain analysis chart of nickel-aluminum base alloy at 600 DEG C.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further illustrated.
Embodiment one:
By Ni, Al, Ta, Cr, Co, Ni-B, the Re of high-purity (weight > 99.9%), it is that 32.75:32.75:2.5:7.5:15:2:7.5 prepares nickel-aluminum base alloy by the atomic percent of composition Ni, Al, Ta, Cr, Co, B, Re. The chemical composition of nickel-aluminum base alloy is: NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re, and concrete preparation method is as follows:
1) melting in vacuum induction furnace, puts into Ni, Cr, Co in the crucible of vacuum induction furnace, and Al, Ta, Ni-B, Re Al silk system is firmly suspended on above crucible, and being evacuated to vacuum tightness in vacuum induction furnace is 2��3 �� 10-3Pa;
2) energising fusing Ni, Cr, Co metal block, is warming up to the molten metal temperature after fusing and reaches 1580 DEG C, and magnetic agitation makes molten metal composition even;
3) putting into Al silk system Ta metal block firmly, be warming up to 1580 DEG C, magnetic agitation is even; Putting into Al silk system Ni-B metal block firmly, be warming up to 1580 DEG C, magnetic agitation is even; Putting into Al silk system Al metal block firmly, be warming up to 1580 DEG C, magnetic agitation is even; Putting into Al silk system Re metal block firmly, be warming up to 1580 DEG C, magnetic agitation is even;
4) by step 3 at 1600 DEG C of temperature) pouring metal melt of gained becomes diameter to be the alloy bar of 30 millimeters;
5) alloy bar is put into vacuum molybdenum wire furnace, it is evacuated to 6��7 �� 10-3Pa, is warming up to 1350 DEG C of insulations 12 hours, and heat-up rate is 10 DEG C/min, and stove is cold;
6) vacuum molybdenum wire furnace is evacuated to 6��7 �� 10-3Pa, is warming up to 1150 DEG C of insulations 12 hours, and heat-up rate is 10/min, and stove is cold, obtains nickel-aluminum base alloy.
The mechanical property of Gleeble1500 hot modeling test machine beta alloy, its compressive strain speed is 2 �� 10-3s-1, nickel-aluminum base alloy is of a size of 4 �� 4 �� 6 millimeters, and experimental temperature is room temperature��600 DEG C.
Under room temperature, the Vickers' hardness of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 663HV, and ultimate compression strength is 1384.7MPa, and true strain is 0.775. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 1209.7MPa, and true strain is 0.069. (as shown in Figure 2)
At 300 DEG C, the ultimate compression strength of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 1290MPa, and true strain is 0.26. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 1117.4MPa, and true strain is 0.145.
At 600 DEG C, the ultimate compression strength of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 1612.0MPa, and true strain is 0.380. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 992.2MPa, and true strain is 0.126.
Embodiment two:
By Ni, Al, Ta, Cr, Co, Ni-B, the Re of high-purity (weight > 99.9%), it is that 32.75:32.75:2.5:7.5:15:2:7.5 prepares nickel-aluminum base alloy by the atomic percent of composition Ni, Al, Ta, Cr, Co, B, Re. The chemical composition of nickel-aluminum base alloy is: NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re, and concrete preparation method is as follows:
1) melting in vacuum induction furnace, puts into Ni, Cr, Co in the crucible of vacuum induction furnace, and Al, Ta, Ni-B, Re Al silk system is firmly suspended on above crucible, and being evacuated to vacuum tightness in vacuum induction furnace is 3��4 �� 10-3Pa;
2) energising fusing Ni, Cr, Co metal block, the molten metal temperature being warming up to fusing reaches 1590 DEG C, and magnetic agitation makes molten metal composition even;
3) putting into Al silk system Ta metal block firmly, be warming up to 1590 DEG C, magnetic agitation is even; Putting into Al silk system Ni-B metal block firmly, be warming up to 1590 DEG C, magnetic agitation is even; Putting into Al silk system Al metal block firmly, be warming up to 1590 DEG C, magnetic agitation is even; Putting into Al silk system Re metal block firmly, be warming up to 1590 DEG C, magnetic agitation is even;
4) by step 3 at 1590 DEG C of temperature) pouring metal melt of gained becomes diameter to be the alloy bar of 30 millimeters;
5) alloy bar is put into vacuum molybdenum wire furnace, it is evacuated to 5��6 �� 10-3Pa, is warming up to 1350 DEG C of insulations 12 hours, and heat-up rate is 15 DEG C/min, and stove is cold;
6) vacuum molybdenum wire furnace is evacuated to 5��6 �� 10-3Pa, is warming up to 1150 DEG C of insulations 12 hours, and heat-up rate is 15 DEG C/min, and stove is cold, obtains nickel-aluminum base alloy.
The mechanical property of Gleeble1500 hot modeling test machine beta alloy, its compressive strain speed is 2 �� 10-3s-1, alloy is of a size of 4 �� 4 �� 6 millimeters, and experimental temperature is room temperature��600 DEG C.
Under room temperature, the Vickers' hardness of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 650HV, and ultimate compression strength is 1250MPa, and true strain is 0.65. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 1209.7MPa, and true strain is 0.069.
At 300 DEG C, the ultimate compression strength of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 1280.6MPa, and true strain is 0.267. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 1117.4MPa, and true strain is 0.145. (as shown in Figure 3)
At 600 DEG C, the ultimate compression strength of NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re alloy is 1611.5MPa, and true strain is 0.374. The ultimate compression strength of NiAl-2.5Ta-7.5Cr alloy is 992.2MPa, and true strain is 0.126. (as shown in Figure 4).
Claims (4)
1. a nickel-aluminum base alloy, is characterized in that: its composition is NiAl-2.5Ta-7.5Cr-15Co-2B-7.5Re, and namely the atomic percent of Ni, Al, Ta, Cr, Co, B, Re is 32.75:32.75:2.5:7.5:15:2:7.5.
2. nickel-aluminum base alloy as claimed in claim 1, it is characterised in that: under room temperature, the Vickers' hardness of nickel-aluminum base alloy is 650��663HV, and ultimate compression strength is 1300��1390MPa, and true strain is 0.60��0.80; At 300 DEG C, the ultimate compression strength of nickel-aluminum base alloy is 1250��1290MPa, and true strain is 0.25��0.27; At 600 DEG C, the ultimate compression strength of nickel-aluminum base alloy is 1550��1620MPa, and true strain is 0.32��0.38.
3. a preparation method for nickel-aluminum base alloy as claimed in claim 2, is characterized in that: comprise the following steps:
1) melting in vacuum induction furnace, puts into Ni, Cr, Co in the crucible of vacuum induction furnace, and Al, Ta, Ni-B, Re Al silk system is firmly suspended on above crucible, and being evacuated to vacuum tightness in vacuum induction furnace is 2��4 �� 10-3Pa;
2) energising fusing Ni, Cr, Co metal block, the molten metal temperature being warming up to fusing reaches 1560��1600 DEG C, and magnetic agitation makes molten metal composition even;
3) putting into Al silk system Ta metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Ni-B metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Al metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even; Putting into Al silk system Re metal block firmly, be warming up to 1560��1600 DEG C, magnetic agitation is even;
4) by step 3 at 1560��1600 DEG C of temperature) pouring metal melt of gained becomes alloy bar;
5) alloy bar is put into vacuum molybdenum wire furnace, it is evacuated to 5��8 �� 10-3Pa, is warming up to 1350 DEG C of insulations 12 hours, and heat-up rate is 10��15 DEG C/min, and stove is cold;
6) vacuum molybdenum wire furnace is evacuated to 5��8 �� 10-3Pa, is warming up to 1150 DEG C of insulations 12 hours, and heat-up rate is 10��15 DEG C/min, and stove is cold, obtains nickel-aluminum base alloy.
4. the preparation method of nickel-aluminum base alloy as claimed in claim 3, it is characterised in that: described step 4) in the diameter of alloy bar be 30 millimeters.
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| CN106676328B (en) * | 2016-12-16 | 2019-03-05 | 中南大学 | A kind of NiAl alloy epitaxy and its preparation method and application for mixing B |
| CN106676330B (en) * | 2016-12-16 | 2019-03-05 | 中南大学 | A kind of NiAl alloy epitaxy and its preparation method and application |
| CN106676329B (en) * | 2016-12-16 | 2019-04-12 | 中南大学 | A kind of NiAl alloy epitaxy of doped rare earth element and its preparation method and application |
| CN112458351B (en) * | 2020-10-22 | 2021-10-15 | 中国人民解放军陆军装甲兵学院 | High compressive strength nickel-cobalt-based high temperature alloy |
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|---|---|---|---|---|
| US5556486A (en) * | 1993-07-12 | 1996-09-17 | Aerospatiale Societe Nationale Industrielle | Composite material having an intermetallic matrix of AlNi reinforced by silicon carbide particles |
| CN101089215A (en) * | 2006-06-16 | 2007-12-19 | 中国科学院金属研究所 | High strength antithermal corrosion low segregation directional high temp alloy |
| CN101148728A (en) * | 2007-10-19 | 2008-03-26 | 北京航空航天大学 | NiAl-Cr(Mo) biphase eutectic crystal intermetallic compound modified by Ta |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3657521B2 (en) * | 2001-01-16 | 2005-06-08 | 独立行政法人科学技術振興機構 | Plastic processing method of NiAl intermetallic compound |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5556486A (en) * | 1993-07-12 | 1996-09-17 | Aerospatiale Societe Nationale Industrielle | Composite material having an intermetallic matrix of AlNi reinforced by silicon carbide particles |
| CN101089215A (en) * | 2006-06-16 | 2007-12-19 | 中国科学院金属研究所 | High strength antithermal corrosion low segregation directional high temp alloy |
| CN101148728A (en) * | 2007-10-19 | 2008-03-26 | 北京航空航天大学 | NiAl-Cr(Mo) biphase eutectic crystal intermetallic compound modified by Ta |
Non-Patent Citations (2)
| Title |
|---|
| 《Microstructural Evolution in Multiphase NiAl-2.5Ta-7.5Cr Alloy during Annealing at Different Temperatures》;Wan Xiaojun,etal.;《Rare Metal Materials and Engineering》;20110531;第40卷(第5期);第0757-0760页 * |
| 《NiAl-2.5Ta-7.5Cr-1B合金的微观组织、力学性能与摩擦磨损特性》;王振生等;《金属学报》;20131130;第49卷(第11期);第1325-1332页 * |
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