CN1718803A - Nickel-based casting high-temperature alloy for high-temperature die - Google Patents
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- CN1718803A CN1718803A CN 200510084011 CN200510084011A CN1718803A CN 1718803 A CN1718803 A CN 1718803A CN 200510084011 CN200510084011 CN 200510084011 CN 200510084011 A CN200510084011 A CN 200510084011A CN 1718803 A CN1718803 A CN 1718803A
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 81
- 239000000956 alloy Substances 0.000 title claims abstract description 81
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 37
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 18
- 238000005266 casting Methods 0.000 title claims abstract description 13
- 239000000126 substance Substances 0.000 claims abstract description 6
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 4
- 229910052715 tantalum Inorganic materials 0.000 claims description 8
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 239000004615 ingredient Substances 0.000 claims description 5
- 229910052758 niobium Inorganic materials 0.000 claims description 5
- 229910052721 tungsten Inorganic materials 0.000 claims description 5
- 229910052727 yttrium Inorganic materials 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 16
- 230000003647 oxidation Effects 0.000 abstract description 12
- 238000007254 oxidation reaction Methods 0.000 abstract description 12
- 238000012545 processing Methods 0.000 abstract description 4
- 229910000601 superalloy Inorganic materials 0.000 abstract description 4
- 229910052719 titanium Inorganic materials 0.000 abstract description 3
- 230000003078 antioxidant effect Effects 0.000 description 16
- 239000010955 niobium Substances 0.000 description 8
- 239000011651 chromium Substances 0.000 description 7
- 238000000465 moulding Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 5
- 229910052804 chromium Inorganic materials 0.000 description 5
- 238000010275 isothermal forging Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 239000003963 antioxidant agent Substances 0.000 description 4
- 235000006708 antioxidants Nutrition 0.000 description 4
- 230000006698 induction Effects 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 239000000843 powder Substances 0.000 description 4
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 3
- 241001062472 Stokellia anisodon Species 0.000 description 3
- 239000011733 molybdenum Substances 0.000 description 3
- 238000007670 refining Methods 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 229910010038 TiAl Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000003756 stirring Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 210000000795 conjunctiva Anatomy 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- YGANSGVIUGARFR-UHFFFAOYSA-N dipotassium dioxosilane oxo(oxoalumanyloxy)alumane oxygen(2-) Chemical compound [O--].[K+].[K+].O=[Si]=O.O=[Al]O[Al]=O YGANSGVIUGARFR-UHFFFAOYSA-N 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910052627 muscovite Inorganic materials 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention relates to a nickel-based casting superalloy for a high-temperature die, which is characterized in that: the alloy comprises the following chemical components in percentage by mass: 9.0-12.0% of Co; 5.0-6.5% of Al; 2.5-3.5% of Cr; 0.5 to 1.5 percent of Ti; 13.0-14.5% of W; 1.5-2.5% of Mo; 0.8-1.5% of Nb; ta 2.0-5.0%; 0.3 to 1.5 percent of Hf; 0.07-0.18% of C; b, 0.01-0.02%; y is less than or equal to 0.01 percent, and the balance is nickel, the nickel-based cast superalloy for the high-temperature mold has good high-temperature strength and plasticity, excellent high-temperature oxidation resistance, thermal fatigue performance and good high-temperature structure stability, and simultaneously has excellent processing and forming performance, and can be used as a large-scale high-temperature mold or other high-temperature structural materials.
Description
Technical field
The present invention is a kind of nickel base casting high temperature alloy for high temperature mould, belongs to metal material field
Background technology
Deng warm deformation is the main moulding process of high-temperature structural material product, and one of gordian technique of isothermal forging process is a moulding stock.The nickel base powder superalloy, as the texturing temperature of alloys such as Rene ' 95, Rene ' 88DT, CH-98 all more than 1050 ℃, and the texturing temperature of more advanced intermetallic compound (TiAl etc.) is more than 1100 ℃, so the research of the isothermal forging moulding stock that temperature more than 1050 ℃ is used is the direction of domestic and international relevant speciality common concern with using.
Researched and developed a large amount of superalloy moulds both at home and abroad, use temperature is at American-European IN100, MAR-M-200, X-40, Udimet 700, the Inconel713C alloy of having below 1000 ℃, the K3 of Muscovite Ж С 6 К, Ж С 6y, И Щ B-1, И Щ B-2, Л 114 alloys and China, K465 alloy etc.At the die material material more than 1000 ℃, the America and Europe adopts molybdenum base alloy for use temperature, and its texturing temperature can reach 1200 ℃
[4], strain rate is 10
-3-10
-2s
-1, produced the turbine disk in batches based on IN100, Rene ' 95, Rene ' 88DT nickel-base alloy.But molybdenum base alloy (TZM) mould requires vacuum condition, need set up perfect totally-enclosed isothermal forging equipment, invests huge.It is said, the moulding stock that Russia adopts 1050-1200 ℃ of atmosphere to use down, but concrete alloying constituent and mechanical behavior under high temperature do not appear in the newspapers, and as И Щ B-31 alloy, use temperature reaches 1080 ℃, and the average rate of oxidation under this temperature is 0.14g/m
2H; And the use temperature of И Щ B-17 alloy reaches 1150 ℃, and the average rate of oxidation under this temperature is 0.24g/m
2H, its mould are used to make З П 975 powdered alloy dishes.Domestic have only the use temperature of K21 alloy to surpass 1000 ℃ at present, uses under atmosphere, and its ultimate-use temperature is 1050 ℃.
The advanced aircraft engine of China all adopts powder turbine disk route at present, the texturing temperature of domestic s-generation powder metallurgy FGH96 is about 1070 ℃, simultaneously because totally-enclosed isothermal forging equipment manufacturing cost costliness, be not suitable for China's national situation, therefore be badly in need of the die material material that atmosphere uses down more than 1050 ℃, to satisfy the requirement of major diameter powder turbine disk isothermal forging.
Summary of the invention
Purpose of the present invention is just at above-mentioned situation, design provides a kind of die material material that can use under 1050-1100 ℃ of atmosphere, have superior hot strength, antioxidant property and thermal fatigue property simultaneously, to satisfy the needs of the Ni-based turbine disk of powder and more advanced intermetallic compound (TiAl etc.) ausforming.
For the die material material, topmost performance is hot strength and high-temperature oxidation resistance, and secondly thermal fatigue property is also very important, also should possess the good processing performance that shapes simultaneously.At above-mentioned purpose, main technical schemes of the present invention is to take complex alloysization, and the refractory element total amount reaches about 20wt%, adds the elements useful to antioxidant property such as Cr, Ta, Y, so that make alloy have good comprehensive performances.
Technical solution of the present invention realizes by following measure:
This kind nickel base casting high temperature alloy for high temperature mould is characterized in that: the chemical ingredients of its alloy and mass percent thereof are: Co 9.0～12.0%; Al 5.0～6.5%; Cr 2.5～3.5%; Ti0.5～1.5%; W 13.0～14.5%; Mo 1.5～2.5%; Nb 0.8～1.5%; Ta 2.0～5.0%; Hf 0.3～1.5%; C 0.07～0.18%; B 0.01～0.02%; Y≤0.01%, surplus are nickel.On this basis, the mass percent sum W+Mo+Nb+Ta of refractory element W, Mo, Nb, Ta is in this alloy: 18%≤W+Mo+Nb+Ta≤23%.
The microstructure of this alloy is mainly by the nascent M of γ, γ ', MC and minute quantity
6The C phase composite.In mentioned component, high-melting-point element solid solutions such as Mo, W, Nb, Ta strengthen matrix γ mutually with γ ' mutually; Formation γ ' such as Al, Ti, Nb, Ta, Hf reach a spot of carbide mutually and carry out second reinforcement mutually; Element such as C, B carries out grain-boundary strengthening; Al, Cr are most important anti-oxidant elements; Add micro-Y simultaneously with thinning microstructure with improve antioxidant property; Ta is not only also very helpful to improving antioxidant property, and can improve the form of MC carbide; The having to be beneficial to of an amount of Hf improved the alloy casting processing performance; Co is to suppressing the nascent M of bulk
6C is mutually favourable, can improve the microstructure of alloy, and is also beneficial to castability and fatigue property simultaneously.
Show that by experimental study this alloy has good comprehensive performances in the mentioned component scope.1050 ℃ of tensile yield strengths of this alloy are about 500MPa, and unit elongation is more than 4%; 1100 ℃ of tensile yield strengths also reach 390MPa, all apparently higher than K21 alloy (1050 ℃ of tensile yield strength 418MPa are 330MPa in the time of 1100 ℃); 1050 ℃ of compression yield strengths of this alloy reach 690MPa, and 1100 ℃ of compression yield strengths are 600MPa, far above the K21 alloy; This alloy has the good high-temperature enduring quality, and be about 200h the creep rupture life under the 1100 ℃/70MPa, almost exceeds one times than K21 alloy (be about 100 hours the creep rupture life under the 1100 ℃/70MPa); This alloy high-temp antioxidant property is superior, regulation according to HB5258-2000,1050 ℃ of antioxidant properties of this alloy reach complete anti-oxidant level, 1100 ℃ of antioxidant properties are anti-oxidant level, and 1050 ℃ of antioxidant properties of K21 alloy are anti-oxidant level, so 1050 ℃ of antioxidant properties of this alloy are than a high order of magnitude of K21 alloy; 1050 ℃ of thermal fatigue properties of this alloy also obviously are better than the K21 alloy.In addition, this alloy high-temp structure stability is good, and has good casting technique performance and processing characteristics.Therefore this alloy is to be suitable for the moulding stock that uses 1050～1100 ℃ of atmosphere under, and its use temperature is a kind of up-and-coming die material material than about 50 ℃ of the highest moulding stock K21 alloy height of domestic present use temperature.
Embodiment
The chemical ingredients of this kind nickel base casting high temperature alloy for high temperature mould and mass percent thereof are: Co9.0～12.0%; Al 5.0～6.5%; Cr 2.5～3.5%; Ti 0.5～1.5%; W 13.0～14.5%; Mo 1.5～2.5%; Nb 0.8～1.5%; Ta 2.0～5.0%; Hf 0.3～1.5%; C 0.07～0.18%; B 0.01～0.02%; Y 0.001～0.01%, and surplus is a nickel.Concrete scheme as shown in Table 1.And with above-mentioned die material material called after DMO2 alloy.
Table 1: the chemical ingredients (wt%) of DMO2 alloy embodiment of the present invention and comparative alloy K21
| Alloy | Co | Cr | Al | Ti | W | Mo | Nb | Ta | Hf | B | C | Y | Ni | |
| DMO2 | 1 | 9.9 | 3.1 | 5.8 | 1.0 | 13.7 | 2.0 | 1.0 | 3.5 | 0.7 | 0.016 | 0.13 | ≤0.01 | Surplus |
| 2 | 9.9 | 3.1 | 5.8 | 1.0 | 14.5 | 2.0 | 1.0 | 3.5 | 0.7 | 0.016 | 0.11 | ≤0.01 | Surplus | |
| 3 | 9.9 | 3.1 | 5.8 | 1.0 | 13.7 | 2.0 | 1.0 | 3.5 | 0.7 | 0.016 | 0.18 | ≤0.01 | Surplus | |
| 4 | 9.9 | 3.50 | 5.0 | 1.0 | 13.7 | 2.0 | 1.0 | 3.5 | 0.7 | 0.016 | 0.13 | ≤0.01 | Surplus | |
| 5 | 9.9 | 2.50 | 6.5 | 1.0 | 13.7 | 2.0 | 1.0 | 3.5 | 0.7 | 0.016 | 0.13 | ≤0.01 | Surplus | |
| 6 | 9.9 | 3.1 | 5.8 | 1.0 | 13.7 | 2.0 | 1.0 | 2.0 | 0.7 | 0.016 | 0.13 | ≤0.01 | Surplus | |
| 7 | 9.9 | 3.1 | 5.8 | 1.0 | 13.7 | 2.0 | 1.0 | 5.0 | 0.7 | 0.016 | 0.13 | ≤0.01 | Surplus | |
| K21 | 10.1 | 2.9 | 6.0 | / | 17.3 | / | 1.0 | / | / | 0.02 | 0.16 | Zr：0.5 | Surplus | |
Adopt two vacuum induction methods to smelt, at first adopt vacuum induction melting furnace to smelt the qualified mother alloy of composition, this process need is through fusing, and------cooling---alloying---is poured into a mould five steps and is finished in refining.In the fusing step, nickel, cobalt, molybdenum, tungsten, niobium, tantalum, chromium, the carbon crucible of directly packing into is changed more than the clear back refining 30min, and refining finishes violent stirring molten bath, back, and cooling conjunctiva then has a power failure; Energising again adds aluminium, titanium, and melting was stirred after 5 minutes, adds ferro-boron, yttrium and hafnium melting again and stirs after 5 minutes, promotes the homogenizing of composition.At last, the cooling that has a power failure after bath temperature reaches teeming temperature, can be poured into a mould, and cast is answered charged and undertaken by strainer.After the mother alloy composition is qualified, adopt investment cast or lost foam in vacuum induction melting furnace, to be cast as mould or other thermal structure spare.
Adopt above-mentioned technology, on vacuum induction furnace, smelt and poured into a mould the described alloy of 7 stove technical solution of the present invention.1050 ℃ of tensile properties of each stove alloy are as shown in table 2, and 1050 ℃ of static antioxidant properties as shown in Figure 1.In order to contrast, also smelted a stove K21 alloy under the same conditions, its chemical ingredients is also listed in table 1, table 2 and Fig. 1 respectively with relevant performance.
1050 ℃ of high temperature instantaneous stretching performances of table 2 DMO2 alloy of the present invention and comparative alloy K21
| Heat (batch) number | σ b(MPa) | σ 0.2(MPa) | δ(％) | Ψ(％) | |
| DMO2 | 1 | 590 | 515 | 6.0 | 8.0 |
| 2 | 570 | 495 | 4 | 2.5 | |
| 3 | 555 | 500 | 5 | 12.5 | |
| 4 | 570 | 485 | 4.5 | 8.0 | |
| 5 | 570 | 510 | 6.5 | 7.0 | |
| 6 | 585 | 510 | 5.5 | 7.5 | |
| 7 | 540 | 470 | 4.5 | 14 | |
| K21 | 488 | 418 | 3.8 | 5.8 | |
From table 1, table 2 as seen, the variation of W, C, Al, Cr, Ta content makes 1050 ℃ of high temperature tensile properties of DMO2 alloy of the present invention that some fluctuations be arranged, tensile strength changes between 540～590MPa, and yield strength changes between 470～515MPa, and unit elongation is 4.0%～6.5%.The main forming element Al content high temperature tensile properties of DMO2 alloy of the present invention that all makes on the low side of refractory element too high levels or γ ' slightly descends, and this explanation is strengthened excessively or be not enough all unfavorable to the hot strength of alloy.But no matter under which kind of situation, 1050 ℃ of high temperature tensile properties of DMO2 alloy of the present invention all obviously are better than K21 alloy, tensile strength σ
bWith yield strength σ
0.2All more than the high at least 50MPa than K21 alloy, high-temp plastic also obviously is better than the K21 alloy.For the DMO2 alloy of optimal components, its 1050 ℃ of instantaneous stretching intensity σ
bReach 590MPa, yield strength σ
0.2Reach 515MPa, respectively about high 100MPa than K21 alloy; The unit elongation of this alloy also reaches 6.0% simultaneously, apparently higher than the K21 alloy.
From Fig. 1 as seen, in this alloy gold composition scope, the variation of Al, Cr, Ta content is very little to 1050 ℃ of static antioxidant property influences of DMO2 alloy, the oxidation susceptibility of the DMO2 alloy of five kinds of compositions is suitable, all be that in the weightening finish of oxidation 25h rear oxidation slowly the final weightening finish behind the oxidation 100h is 1.00～1.21mg/cm
2And the K21 alloy just reaches 2.50mg/cm 1050 ℃ of oxidation 25h rear oxidation weightening finishes
2, oxidation weight gain still increases comparatively fast thereafter, and its weightening finish reaches 3.57mg/cm behind the oxidation 100h
2, be more than 3 times of DMO2 alloy.Therefore 1050 ℃ of antioxidant properties of DMO2 alloy obviously are better than the K21 alloy.
In sum, the over-all properties of DMO2 alloy obviously is better than the highest moulding stock K21 alloy of domestic present use temperature.It is the die material material that uses under a kind of up-and-coming 1050～1100 ℃ of atmosphere.
Claims (5)
1. nickel base casting high temperature alloy for high temperature mould, it is characterized in that: the chemical ingredients of this alloy and mass percent thereof are: Co 9.0～12.0%; Al 5.0～6.5%; Cr 2.5～3.5%; Ti 0.5～1.5%; W 13.0～14.5%; Mo 1.5～2.5%; Nb 0.8～1.5%; Ta 2.0～5.0%; Hf 0.3～1.5%; C 0.07～0.18%; B 0.01～0.02%; Y≤0.01%; Surplus is a nickel.
2. nickel base casting high temperature alloy for high temperature mould according to claim 1 is characterized in that: the mass percent of Ta is in this alloy: 2.5%～4.5%.
3. nickel base casting high temperature alloy for high temperature mould according to claim 1 is characterized in that: the mass percent of Hf is in this alloy: 0.3%～1.0%.
4. nickel base casting high temperature alloy for high temperature mould according to claim 1 is characterized in that: the mass percent of Y is in this alloy: 0.001～0.01%.
5. nickel base casting high temperature alloy for high temperature mould according to claim 1 is characterized in that: the mass percent sum W+Mo+Nb+Ta of refractory element W, Mo, Nb, Ta is in this alloy: 18%≤W+Mo+Nb+Ta≤23%.
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| CN100396806C CN100396806C (en) | 2008-06-25 |
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Cited By (11)
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| CN102433422A (en) * | 2010-09-29 | 2012-05-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Model correcting method for high-temperature alloy thin-wall casting |
| CN103074524A (en) * | 2013-02-27 | 2013-05-01 | 南京信息工程大学 | Ni-base high-temperature-resistant alloy and preparation method thereof |
| CN103551481A (en) * | 2013-10-24 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Isothermal forging die for intermetallic compound blades and production method thereof |
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| DE19624056A1 (en) * | 1996-06-17 | 1997-12-18 | Abb Research Ltd | Nickel-based super alloy |
| JP2002167636A (en) * | 2000-10-30 | 2002-06-11 | United Technol Corp <Utc> | Low density oxidation resistant superalloy material capable of thermal barrier coating retention without bond coat |
| JP3753143B2 (en) * | 2003-03-24 | 2006-03-08 | 大同特殊鋼株式会社 | Ni-based super heat-resistant cast alloy and turbine wheel using the same |
| JP4449337B2 (en) * | 2003-05-09 | 2010-04-14 | 株式会社日立製作所 | High oxidation resistance Ni-base superalloy castings and gas turbine parts |
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| CN103074524A (en) * | 2013-02-27 | 2013-05-01 | 南京信息工程大学 | Ni-base high-temperature-resistant alloy and preparation method thereof |
| CN103074524B (en) * | 2013-02-27 | 2015-05-13 | 南京信息工程大学 | Ni-base high-temperature-resistant alloy and preparation method thereof |
| CN103551481A (en) * | 2013-10-24 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Isothermal forging die for intermetallic compound blades and production method thereof |
| CN107630152A (en) * | 2016-07-18 | 2018-01-26 | 中国科学院金属研究所 | A kind of nickel-based isometric crystal alloy and its Technology for Heating Processing and application containing yttrium and hafnium |
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| JPWO2019107502A1 (en) * | 2017-11-29 | 2019-12-12 | 日立金属株式会社 | Hot forging molds and methods for manufacturing forged products |
| US11692246B2 (en) | 2017-11-29 | 2023-07-04 | Proterial, Ltd. | Ni-based alloy for hot-working die, and hot-forging die using same |
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