CN1022848C - Deformation high-temp. alloy based on iron nickel and chromium - Google Patents
Deformation high-temp. alloy based on iron nickel and chromium Download PDFInfo
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- CN1022848C CN1022848C CN 90110284 CN90110284A CN1022848C CN 1022848 C CN1022848 C CN 1022848C CN 90110284 CN90110284 CN 90110284 CN 90110284 A CN90110284 A CN 90110284A CN 1022848 C CN1022848 C CN 1022848C
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 41
- 239000000956 alloy Substances 0.000 title claims abstract description 41
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 title claims description 3
- 229910052804 chromium Inorganic materials 0.000 title claims description 3
- 239000011651 chromium Substances 0.000 title claims description 3
- UGKDIUIOSMUOAW-UHFFFAOYSA-N iron nickel Chemical compound [Fe].[Ni] UGKDIUIOSMUOAW-UHFFFAOYSA-N 0.000 title claims description 3
- 238000001816 cooling Methods 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 230000032683 aging Effects 0.000 claims abstract description 4
- 229910000601 superalloy Inorganic materials 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 7
- 238000003723 Smelting Methods 0.000 claims description 5
- 238000005242 forging Methods 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 4
- 238000007669 thermal treatment Methods 0.000 claims description 4
- 239000004615 ingredient Substances 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 2
- 238000002791 soaking Methods 0.000 claims description 2
- 235000019628 coolness Nutrition 0.000 claims 1
- 238000005728 strengthening Methods 0.000 abstract description 14
- 229910018487 Ni—Cr Inorganic materials 0.000 abstract description 6
- 239000012535 impurity Substances 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000003754 machining Methods 0.000 abstract 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract 1
- 239000010936 titanium Substances 0.000 description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 7
- 229910052799 carbon Inorganic materials 0.000 description 7
- 230000000694 effects Effects 0.000 description 6
- 239000010955 niobium Substances 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- 239000013078 crystal Substances 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 3
- 238000001556 precipitation Methods 0.000 description 3
- 238000005204 segregation Methods 0.000 description 3
- 208000037656 Respiratory Sounds Diseases 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 241001062472 Stokellia anisodon Species 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
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910021386 carbon form Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
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- Heat Treatment Of Steel (AREA)
Abstract
The present invention relates to Fe-Ni-Cr base high-temperature deformation alloy. The present invention is mainly characterized in that the Fe-Ni-Cr base high-temperature deformation alloy comprises the components: 0.04 to 0.11 wt% of C, 0.30 to 0.80 wt% of Al, 0.80 to 1.30 wt% of Ti, 2.50 to 3.50 wt% of W, 35.00 to 40.00 wt% of Ni, 20.00 to 23.00 wt% of Cr, 0.003 to 0.01 wt% of B, 0.05 wt% of Ce (the adding amount) and Fe as the rest, wherein the content of Si as an impurity is less than or equal to 0.08, the content of Mn as an impurity is less than or equal to 0.07, the content of S as an impurity is less than or equal to 0.02 and the content of P as an impurity is less than or equal to 0.03. The heat machining technology comprises that the heating temperature is from 1000 to 1170 DEG C, the holding time is from 1 to 2 hours, the forge starting temperature is more than or equal to 1000 DEG C and the forge stop temperature is more than 930 DEG C; the heat treatment technology comprises that the solution strengthening temperature is from 1000 to 1120 DEG C, the water cooling is carried out for 2 to 4 hours, the aging strengthening temperature is from 680 to 800 DEG C, and the air cooling is carried out for 16 hours.
Description
The present invention system belongs to the superalloy field, and a kind of have high strength, Fe-Ni-Cr base wrought superalloy and preparation method thereof that plasticity is good promptly are provided.
Load ring on the aircraft engine requires σ b 〉=590MPa, σ 0.2 〉=345MPa, δ 〉=30%.700 ℃ of ψ 〉=35% high-temperature and durable, 195MPa stress following creep rupture life of T 〉=50h.It seems that from the high temperature alloy that uses at present none can satisfy above-mentioned requirements both at home and abroad, once be used for the GH of above-mentioned parts
35Alloy also is difficult to reach above-mentioned service requirements, and this is because GH
35Al in the alloy after smelting, has not had or has not had enough Al units usually to form precipitation strength phase r as detrimental impurity control
1, therefore, the intensity of this alloy and the stability of long-term behaviour are not very good.In addition, GH
35Carbon content in the alloy is higher, makes this alloy form a large amount of MC carbide, thereby The amount of inclusions is increased, and has so not only consumed more strengthening element titanium, and provides some fragility phase and crackle to form the source.In addition, the process of thermal treatment system is also not too reasonable, so also influenced intensity and the plasticity and the toughness thereof of alloy.
The purpose of this invention is to provide a kind of good Fe-Ni-Cr base wrought superalloy that can satisfy the materials for aeroengines service requirements of high strength, plasticity that has.
The present invention selected for use with Fe-Ni-Cr be base the suitable adjustment of superalloy C, Al, Ti, the content of elements such as B and Si, Mn, S, the content of the impurity element of P, by suitable smelting, hot-work, system of heat treatment process obtain to satisfy the wrought superalloy of above-mentioned performance requriements.
Content through repeatedly experiment showed, Al for the most desirable, because the Al element plays in being partially soluble in austenitic matrix the good solution strengthening effect, thereby also need have enough Al content to form the effect that γ ' phase plays precipitation strength at 0.30-0.80%.Along with Al content increases, γ ' phase amount increases, not only make matrix obtain corresponding reinforcement, and room temperature and hot strength all improve a lot, when Al content during at 0.38-0.49%, can obtain σ 0.2 〉=450MPa, if surpassing at 0.80% o'clock, Al content is easy to fold, reduce other Al of alloy property greatly, the Ti phase.In addition, the present invention adopts Ti as strengthening element.And the element nb that does not have employing to use always, this is because Ti is more more remarkable to the strengthening effect of alloy than Nb, the Ti that is same content is more more obvious than Nb strengthening effect, as containing 0.8% Ti in the alloy σ 0.2 is reached more than the 350MPa, and use Nb, need to add 1.2% and can obtain same effect.With regard to its segregation to alloy influenced, the segregation of Nb was also serious than Ti in addition, and when repeatedly experiment showed, Ti content at 0.8-1.30%, strengthening effect is ideal.In addition, the an amount of adding of B, can reduce the velocity of diffusion of element, suppress sheet strip, born of the same parents' shape continuous regime of grain boundary carbide effectively and separate out, thereby improved the crystal boundary state at crystal boundary, improved grain-boundary strength, but excessive B adds affiliation and forms too much boride or eutectic structure, and hot workability is degenerated, and enduring quality is reduced, the present invention is controlled at 0.005-0.01% with the add-on of B.Thereby significantly improve creep rupture life, carbon is when alloy smelting, and except that playing desoxydatoin, remaining carbon forms proeutectoid carbide M in alloy
23C
6, with M
3B
2The common main strengthening phase that forms the alloy crystal boundary, if carbon content is too low, then can not make crystal boundary be even chain tissue, cause reduce creep rupture life, have only the carbon content of working as to be higher than after 0.04%, not only can make reaction between carbon and oxygen more abundant, there are enough amounts to form strengthening phase again, if too high levels, alloy will form a large amount of MC carbide, and The amount of inclusions is increased, not only consumed more strengthening element titanium, and provide some fragility phase and crackle to form the source, therefore, C content range provided by the present invention is at 0.04-0.11%.
Alloy ingredient provided by the present invention following (weight %):
C Al Ti W
0.04-0.11 0.30-0.80 0.80-1.30 2.50-3.5
Ni Cr B Ce Fe
35.00-40.00 it is 20.00-23.00 0.003-0.01 0.05(add-on) surplus.Foreign matter content Si≤0.80 wherein, Mn≤0.70, S≤0.02, P≤0.03
The best composition of above-mentioned alloy is:
C Al Ti W
0.07-0.08 0.6 1.00 3.00
Ni Cr B Ce Fe
37.00 surplus in the of 22.00 0.01 0.05
Foreign matter content Si＜0.46 wherein, Mn,＜0.38, S0.001-0.002 P＜0.006.
Preparation method provided by the present invention is basic identical with the superalloy reparation technology that usually adopts, and the hot-work and the heat treating regime of different is alloy change to some extent.The present invention to the thermal process parameter of alloy is:
Heating temperature: 1000-1170 ℃
Soaking time: 1-2 hour
Open the forging temperature: 〉=1000 ℃
Left alone without help forging temperature:＞930 ℃
Adopt solid solution and the thermal treatment of timeliness secondary in addition, make alloy become solid solution and add the timeliness multiple strengthening by single solution strengthening.The processing condition of solution treatment are: 1000-1120 ℃, and 2 hours-4 hours water-cooleds; Handling the processing condition of strengthening is: 680-800 ℃, and 16 hours, air cooling, above-mentioned optimum process condition is: solution treatment: 1080 ℃, 2 hours, water-cooled, processing were strengthened; 680 ℃, 16 hours, air cooling.
Provide embodiment 1-kind Fe-Ni-Cr base wrought superalloy provided by the present invention below.
One, alloy ingredient
C Mn Si S P Ni Cr W Al Ti B Ce Fe
0.071 surplus in the of 0.38 0.46 0.002 0.006 36.87 23.33 3.06 0.50
Two, the preparation of alloy
Above-mentioned alloy superalloy smelting technology is routinely smelted out.
Three, the hot-work of alloy
By the accompanying drawing curve alloy ESR ingot is carried out the cogging Forge Heating.
Four, heat treatment of alloy
Solution treatment:
1080 ℃, 2 hours, water-cooled.
Ageing treatment:
680 ℃, 16 hours, air cooling.
Five, performance (seeing Table sample No. 1)
Provide embodiment 2,3,4(sequence number 2,3,4 below).
Sequence number C Al Ti W Ni Cr B Ce Fe
Surplus in the of 2 0.083 0.79 1.15 2.90 37.57 21.43 0.0050＜0.05
Surplus in the of 3 0.083 0.52 1.15 2.95 37.57 21.36 0.009＜0.05
Surplus in the of 4 0.080 0.50 0.80 3.00 37.00 22.00＜0.01＜0.05
Smelt technology routinely, heat processing technique is identical with embodiment 1, and heat treatment process parameter is as follows:
Embodiment 2 is: 1080 ℃, and 2 hours, water-cooled+720 ℃, 16 hours, air cooling.
Embodiment 3 is: 1000 ℃, and 2 hours, water-cooled+680 ℃, 16 hours, air cooling.
Embodiment 4 is: 1120 ℃, and 4 hours, water-cooled+680 ℃, 16 hours, air cooling.
The mechanical property of table 1 alloy
Preface room temperature tensile high-temperature and durable
Number σ bMPa σ 0.2MPa δ % ψ % 700,195MPaT hour
1 865 450 32.0 47.6 600
2 840 480 26.4 45.2 ＞200
3 860 415 31.2 50.4 ＞200
4 860 420 34.5 44.1 ＞204
High temperature alloy provided by the present invention has not only kept the advantage of GH35 alloy, and has had following characteristics:
(1) aluminium is added as alloying element (0.3-0.8%), so not only increased precipitation phase r1Quantity, and improved r1Stability, thereby improved the intensity of alloy and the stability of long-term behaviour;
(2) reduced carbon content, and added B, the trace alloying elements such as Ce have reduced in the alloy The amount of inclusions and have increased significantly grain-boundary strength, thereby increased substantially the creep rupture strength of alloy, and improved hot-working character;
(3) owing to select low titanium, and need not strengthen by high niobium, reduce the segregation of alloy, postponed separating out of TCP phase;
(4) improved heat treating regime, further improved intensity and the plasticity of alloy, made alloy have good obdurability.
Claims (3)
1, a kind of based on iron nickel and chromium wrought superalloy is characterized in that alloy ingredient is as follows: (weight %)
C Al Ti W
0.04-0.11 0.30-0.80 0.80-1.30 2.50-3.5
Ni Cr B Ce Fe
35.00-40.00 20.00-23.00 0.003-0.01 0.05 (add-on) is surplus.
Foreign matter content Si≤0.80 wherein, Mn≤0.70, S≤0.02, P≤0.03
2, by the described superalloy of claim 1, it is characterized in that the best composition of alloy is:
C Al Ti W
0.07-0.08 0.6 1.00 3.00
Ni Cr B Ce Fe
37.00 surplus in the of 22.00 0.01 0.05
Foreign matter content Si＜0.46 wherein, Mn＜0.38, S0.001-0.002P＜0.006.
3, a kind of preparation method that is specifically designed to claim 1,2 described superalloys, it is made up of smelting, hot-work, thermal treatment, it is characterized in that:
(1) described heat processing technique is:
Heating temperature: 1000-1170 ℃
Soaking time: 1-2 hour
Open forging temperature 〉=1000 ℃
Stop forging temperature＞930 ℃
(2) described thermal treatment process is solution treatment and ageing treatment second-stage treatment, and the processing parameter of solution treatment is:
1000-1120 ℃, 2-4 hour water-cooled
The processing parameter of ageing treatment is:
680-800 ℃, 16 hours air coolings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 90110284 CN1022848C (en) | 1990-12-30 | 1990-12-30 | Deformation high-temp. alloy based on iron nickel and chromium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 90110284 CN1022848C (en) | 1990-12-30 | 1990-12-30 | Deformation high-temp. alloy based on iron nickel and chromium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1062929A CN1062929A (en) | 1992-07-22 |
| CN1022848C true CN1022848C (en) | 1993-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 90110284 Expired - Fee Related CN1022848C (en) | 1990-12-30 | 1990-12-30 | Deformation high-temp. alloy based on iron nickel and chromium |
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| CN104263998B (en) * | 2014-09-18 | 2016-06-22 | 中国华能集团公司 | A kind of Technology for Heating Processing of ni-fe-cr-boron system high temperature alloy |
| CN104404349A (en) * | 2014-11-03 | 2015-03-11 | 无锡贺邦金属制品有限公司 | Nickel-chromium alloy die-castings |
| CN104404343A (en) * | 2014-11-04 | 2015-03-11 | 无锡贺邦金属制品有限公司 | Nickel-chromium alloy stamping part |
| CN104404338A (en) * | 2014-11-04 | 2015-03-11 | 无锡贺邦金属制品有限公司 | Nickel-chromium based alloy stamping part |
| CN104405912A (en) * | 2014-12-09 | 2015-03-11 | 兰州高压阀门有限公司 | Incoloy825 alloy hard sealing flat gate valve resistant to high pressure of high-sulfur natural gas and forging process |
| CN105821250A (en) * | 2015-01-06 | 2016-08-03 | 宝钢特钢有限公司 | High-strength nickel-base superalloy and manufacturing method thereof |
| CN105420470A (en) * | 2015-11-04 | 2016-03-23 | 湖南天雁机械有限责任公司 | Surface-hardening treatment method for austenitic steel |
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1990
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| CN1062929A (en) | 1992-07-22 |
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