CN102433467A - Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof - Google Patents
Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof Download PDFInfo
- Publication number
- CN102433467A CN102433467A CN2011103881661A CN201110388166A CN102433467A CN 102433467 A CN102433467 A CN 102433467A CN 2011103881661 A CN2011103881661 A CN 2011103881661A CN 201110388166 A CN201110388166 A CN 201110388166A CN 102433467 A CN102433467 A CN 102433467A
- Authority
- CN
- China
- Prior art keywords
- alloy
- hafnium
- tungsten
- crystal alloy
- nickel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 97
- 239000000956 alloy Substances 0.000 title claims abstract description 97
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 37
- 239000013078 crystal Substances 0.000 title claims abstract description 26
- 229910052735 hafnium Inorganic materials 0.000 title claims abstract description 24
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 title claims abstract description 23
- 229910052759 nickel Inorganic materials 0.000 title abstract description 11
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 21
- 229910052721 tungsten Inorganic materials 0.000 claims description 21
- 239000010937 tungsten Substances 0.000 claims description 21
- 239000010936 titanium Substances 0.000 claims description 15
- 239000010955 niobium Substances 0.000 claims description 13
- 238000005275 alloying Methods 0.000 claims description 12
- 239000000470 constituent Substances 0.000 claims description 9
- 230000007774 longterm Effects 0.000 claims description 5
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 3
- SAYDCILDJUOQGY-UHFFFAOYSA-N [W].[Hf].[Nb] Chemical compound [W].[Hf].[Nb] SAYDCILDJUOQGY-UHFFFAOYSA-N 0.000 claims description 2
- 238000005266 casting Methods 0.000 abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 239000004615 ingredient Substances 0.000 abstract 1
- 229910000601 superalloy Inorganic materials 0.000 description 13
- 239000000463 material Substances 0.000 description 9
- 239000011651 chromium Substances 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 7
- 229910052758 niobium Inorganic materials 0.000 description 7
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 7
- 229910052719 titanium Inorganic materials 0.000 description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 6
- 229910052799 carbon Inorganic materials 0.000 description 6
- 230000000052 comparative effect Effects 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 239000004411 aluminium Substances 0.000 description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 5
- 238000001816 cooling Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 5
- 238000002360 preparation method Methods 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000005496 eutectics Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000005192 partition Methods 0.000 description 4
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 238000007670 refining Methods 0.000 description 3
- 239000000523 sample Substances 0.000 description 3
- 206010050031 Muscle strain Diseases 0.000 description 2
- 239000003963 antioxidant agent Substances 0.000 description 2
- 230000003078 antioxidant effect Effects 0.000 description 2
- 235000006708 antioxidants Nutrition 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
- 210000001787 dendrite Anatomy 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012528 membrane Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 229910001011 CMSX-4 Inorganic materials 0.000 description 1
- 229910052684 Cerium Inorganic materials 0.000 description 1
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 238000003723 Smelting Methods 0.000 description 1
- 241001062472 Stokellia anisodon Species 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 229910000905 alloy phase Inorganic materials 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- QDWJUBJKEHXSMT-UHFFFAOYSA-N boranylidynenickel Chemical compound [Ni]#B QDWJUBJKEHXSMT-UHFFFAOYSA-N 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- ZMIGMASIKSOYAM-UHFFFAOYSA-N cerium Chemical compound [Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce] ZMIGMASIKSOYAM-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 210000000795 conjunctiva Anatomy 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 229910052746 lanthanum Inorganic materials 0.000 description 1
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000001376 precipitating effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 229910000753 refractory alloy Inorganic materials 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000007669 thermal treatment Methods 0.000 description 1
- 239000003643 water by type Substances 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a nickel-based isometric crystal alloy, in particular to a hafnium-containing high-tungsten-nickel-based isometric crystal alloy and an application thereof. The hafnium-containing high-tungsten-nickel-based isometric crystal alloy consists of ingredients (in percentage by weight): 0.08 to 0.14 of C, 4.6 to 5.2 of Cr, 5.6 to 6.2 of Al, 0.7 to 1.2 of Ti, 6.0 to 8.0 of Co, 0.7 to 1.2 of Hf, 15.3 to 16.5 of W, 1.6 to 2.1 of Nb, 0.005 to 0.025 of B, 0.005 to 0.03 of Zr and the balance Ni. The alloy has good durability, the creep rupture life is longer than or equal to 40 hours under the conditions of 975 DEG C and 235.2 MPa, the alloy can be directly used for casting, the cost is low, and the production efficiency is high. The alloy can be used for preparing hot end components such as aircraft engines, gas turbine worm wheel blades and the like which can work for a long time at 1100 DEG C. Particularly, when the heat resisting alloy is adopted for manufacturing gas turbine worm wheel blades for electric generation, the work temperature and efficiency of a gas turbine can be obviously improved, and further, the electric generation efficiency is greatly improved.
Description
Technical field
The present invention relates to Ni-based equiax crystal alloy, be specially a kind of contain Ni-based equiax crystal alloy of the high tungsten of hafnium and application thereof.
Background technology
Along with the raising of fuel gas inlet temperature, the holding warm ability and can not meet the demands of wrought superalloy turning vane.Cast superalloy has the higher warm ability of holding, and can reach 1000～1100 ℃, thereby the development of cast superalloy has received extensive attention.Since the forties in 20th century, cast superalloy came out; Tempo is very fast; To 20th century the fifties end; Develop the alloy of many excellent performances such as IN100, Ж С 6 К, B1900 and Mar-M200 successively, domesticly also develop and produced a series of cast superalloys such as K403 and K417G in succession.
No matter be English, U.S.A or Russia; Aircraft engine turning vane material adopts nickel base superalloy; Famous Ж С 6y, the Ж С 6 К nickel base superalloys of Russia are mainly used in the preparation turning vane; A Л-31 Ф mover high and low pressure turbine and four kinds of blades of turning vane of third generation fighter Soviet Union 27 equipments all adopt the preparation of Ж С 6y alloy, and American-European developed country adopts the nickel-based monocrystal turning vane in a large number.U.S. PWA1480 monocrystalline is on active service in the turning vane material of JT9D-7R4 aircraft engine for first, and the F100-PV-229 type aircraft engine firsts and seconds turning vane of F15 that the U.S. is famous and F16 fighter equipment also all adopts this alloy preparation.
Development of Aeroengines depends on the development of material and manufacturing technology to a great extent.For rigidity and the resistance to air loss that improves guides, the caused warpage forward of the load of abated effect on individual blade reduces because the caused blade crackle of vibration is dangerous, and third generation aircraft engine adopts conjuncted built-up type turning vane.At present, turning vanes such as two conjuncted, triplet and tetrad are arranged.For example, A Л-31 Ф mover high and low pressure turning vane is the hollow airfilm cooling blade of triplet; The thrust-weight ratio that China produces is that 8 aircraft engine high pressure turning vane is two conjuncted hollow airfilm cooling blades.
External aircraft engine industry when improving structure, also seek that initial melting temperature height, cost are low, use characteristics and the good superalloy of comprehensive mechanical property.In development casting cold blade (Castcool), casting laminate (Lamilloy) cooling blade, also developed the advanced blade material that CMSX-4 single crystal alloy etc. matches like the Ai Lixun company of the U.S..
The K403 alloy is a domestic application nickel base cast turning vane alloy the most widely, and it successively is used as turning vane on 37 kinds of different models of 20 kinds of movers.The K441 alloy of Metal Inst., Chinese Academy of Sciences's development is used for turbo-jet engine and makes the one-level turning vane, has produced 19 movers from year July in June, 1997 to 1999, has 13 movers to participate in taking a flight test examination, has dropped into batch production at present.In addition, certain model turbo-jet engine one-level turborotor adopts the preparation of DZ404 directional columnargrain alloy, and the turbofan engine low pressure I and II turborotor of certain model adopts K417G equiax crystal alloy to process.
In a word, nickel base superalloy is that performance is the most superior so far, and purposes is the most extensive.The upper limit of this alloy use temperature has approached the fusing point of alloy, but still is that withstand temp is the highest in the present advanced mover, the preferred material of the key part that stress-loaded is maximum.
Summary of the invention
The object of the present invention is to provide a kind of contain Ni-based equiax crystal alloy of the high tungsten of hafnium and application thereof, make alloy have preferable enduring quality, can be used for preparing the hot-end component such as aircraft engine and turbine blade of gas turbine of 1100 ℃ of long term operations.
Technical scheme of the present invention is:
A kind of Ni-based equiax crystal alloy of the high tungsten of hafnium that contains, its alloying constituent (weight percent) be as follows:
C 0.08～0.14, and Cr 4.6～5.2, and Al 5.6～6.2, and Ti 0.7～1.2, and Co 6.0～8.0, and Hf 0.7～1.2, W15.3～16.5, and Nb 1.6～2.1, and B 0.005～0.025, and Zr 0.005～0.03, and Ni is surplus.
Among the present invention, can also on above-mentioned alloying constituent basis, add Ce 0.005～0.02, La 0.005～0.02; Be preferably: Ce:0.01～0.02, La:0.01～0.02.
Among the present invention, aluminium titanium content 6.5wt%＜Al+Ti＜8.0wt%.
Among the present invention, tungsten niobium hafnium content W+Nb+Hf＞18wt%.
The described Ni-based equiax crystal alloy of the high tungsten of hafnium that contains is used to prepare the aircraft engine of 1100 ℃ of long term operations and the hot-end component of turbine blade of gas turbine, 975 ℃ with 235.2MPa condition following creep rupture life >=40 hours.
The present invention has following advantage:
1, alloy of the present invention has preferable enduring quality, 975 ℃ with 235.2MPa condition following creep rupture life >=40 hours.
2, alloy of the present invention can directly be cast use, and cost is low, and production efficiency is high.
3, the anti-oxidant and excellent thermal corrosion resistance of alloy high-temp of the present invention is promptly thermally-stabilised good.
In a word; The Ni-based equiax crystal alloy of the present invention has remarkable hot strength and holds warm ability and good casting technique performance; This alloy not only the aluminium titanium content high (Al+Ti＞6.5wt%), and high-meltiing alloy element total content (W+Nb+Hf) also higher (＞18wt%); Wherein the W upper content limit reaches 16.5wt%, and the Hf upper content limit reaches 1.2wt%.Just because of this alloy has the mentioned component characteristics, thereby has outstanding hot strength and high high-temp stability, be suitable for preparing the hot-end components such as engine turbine blade of 1100 ℃ of long term operations.
Description of drawings
Fig. 1 is the strong parametric synthesis curve of heat of alloy of the present invention and comparative alloy.Wherein, the strong parameter P=T (20+lgt) * 10 of heat
-3, T represents probe temperature, K; T represents duration, hour.
Fig. 2 is the creep curve of alloy differing temps of the present invention.Wherein, (a) figure is 800 ℃; (b) figure is 900 ℃; (c) figure is 975 ℃; (d) figure is 1050 ℃.
Embodiment
Through instance the present invention is detailed below.
Embodiment 1
Adopt Germany to produce the 500Kg vacuum induction furnace smelting experiment mother alloy of ALD, smelt crucible and select alumina crucible for use, temp measuring system is W-Re galvanic couple and JH-5 type infrared ray optical direction temperature/vacuum degree measuring instrument, and the thermometric protective casing is the outer ZrO of coating
2The Mo-Al of (CeO is stable) and BN
2O
3Metal ceramic tube, vacuum tightness should keep≤and 10
-1The Pa order of magnitude.Operating process is: alloying elements such as carbon, nickel boron master alloy, chromium, tungsten, niobium, hafnium, cobalt, zirconium and nickel plate are packed in the crucible; Vacuumize, (90kw～100kw) gas is adhered in the eliminating of baking crucible, when vacuum tightness reaches 10 to give smaller power
-3During a, increase the power melted alloy; It is abundant to change material initial stage assurance reaction between carbon and oxygen, changes the high temperature refining of clear back, guarantees that alloying constituent is even; At 1600 ℃ of refining 5～7min, refining finishes the back cooling, and power failure, conjunctiva, rupture of membranes add Al and Ti and mishmetal RE (cerium, lanthanum); Back power failure cooling is stirred in high-power then stirring; Adding temperature and the add-on of strict control Al can effectively be removed to guarantee the impurity that fuses in the alloy.It is more high-power that (200kw～240kw) impact rupture of membranes is cast into master alloy ingot at 1450 ℃.
The distinguishing feature of alloying constituent of the present invention contains the hafnium about 1.2wt.% exactly.Hf is strong positive segregation element, significantly promotes γ+γ ' eutectic to form.Zr is also the same with Hf, promotes γ+γ ' eutectic to form, and when adding equal in quality fractional Hf and Zr, the influence of Zr is bigger.The solubleness of Zr in eutectic is lower than Hf, and when Hf was identical with Zr content, the Hf content of γ ' doubled than Zr in the eutectic, and this shows that Zr is not so good as Hf aspect the effect of strengthening γ '.
In the alloy of the present invention, contain the W about 16wt.%.Tungsten can improve interatomic bond power after adding alloy, improves diffusion activation energy, makes diffusion process slack-off, improves recrystallization temperature simultaneously, thereby improves the mechanical behavior under high temperature of alloy.Tungsten γ and γ ' mutually in partition ratio approximate 1.Therefore, the W content height can significantly increase γ ' phase amount, improves the alloy thermostability.In nickel-base casting alloy, the tungsten precedence partition is on the dendrite axle, and then precedence partition is in crystal boundary and dendrite circle for hafnium, so tungsten, hafnium add simultaneously alloy property is played the multiple strengthening effect.But compound N i between excess tungsten meeting precipitating metal
4The proneness of the harmful phase of TCP phase (mainly being the μ phase) is separated out in W and increase.In addition, tungsten is carbide forming element, promotes M
6The C carbide forms.And one of vital role of hafnium is exactly to suppress M
23C
6Or M
6The C carbide is separated out along crystal boundary in a large number, can decompose with MC and the carbon that emit forms stable tiny, the dispersion of secondary, irregular MC (mainly being HfC) particle.Carbide is one of strengthening phase important in the superalloy, its size, and form and distribution have material impact to the mechanical property of alloy.
Among the present invention, a large amount of aluminium and titanium (the Al+Ti sum is 7.4wt.% the most nearly) have also been added.Aluminium and titanium are alloying elements the most basic in the nickel base superalloy, and why nickel-base alloy can become the superalloy of not replacing is exactly because there is γ ' strengthening phase, and aluminium is γ ' main forming element mutually with titanium.Simultaneously, titanium still is the MC carbide forming element, can form more stable TiC.Niobium can be replaced a part of aluminium and got into γ ' mutually with titanium.The partition ratio of niobium in γ/γ ' is about 1:＜0.05, promptly most niobiums except that with nearly all get into γ ' mutually carbon combines.Niobium and carbon have very big avidity, can form stable NbC, thus crystal grain thinning effectively.Niobium dissolves in γ ' phase, gets into carbide, thereby improves the thermostability of these phases, delays the gathering growth process of γ ' phase, improves the intensity index of alloy.
Table 1 alloy element component (wt.%)
| C | Cr | Co | Nb | Al | W | Ti | Hf | B | Zr | Ce | La | Ni |
| 0.11 | 4.90 | 6.77 | 2.08 | 5.87 | 16.5 | 1.02 | 1.01 | 0.013 | 0.01 | 0.01 | 0.01 | Surplus |
Table 2 linear expansivity and temperature relation
Can find out that from table 2 along with the rising of temperature, the linear expansivity of alloy obviously increases; Comparative alloy K417G (Chinese aeronautical material handbook second edition second volume P640～609) linear expansivity Changing Pattern is same with alloy phase of the present invention, but linear expansivity is apparently higher than alloy of the present invention, and this deflection that shows alloy temperature influence of the present invention is less.
Table 3 Young's modulus (GPa) and temperature relation
Can find out that from table 3 along with the rising of temperature, the Young's modulus of alloy decreases; But compare with comparative alloy K417G (the same), the Young's modulus decline scope is maximum.Data K417G alloy Young's modulus is generally all greater than alloy of the present invention in the table.Engineering materials generally all hopes to have less Young's modulus.
The present invention mainly is that (Al+Ti＜8wt.%) γ ' of formation high-volume fractional improves its intensity to the more aluminium of adding mutually with titanium elements; The content of maintenance chromium can make alloy high-temp reach complete anti-oxidant level greater than the ratio of 4.5wt.% and Al/Ti greater than 2.5: 1; Can further increase γ ' phase amount through adding niobium and hafnium, improve the lattice misfit degree of γ-γ ', strengthen the strengthening effect of γ ' phase, also form γ simultaneously and " strengthen its room temperature and middle temperature mechanical property mutually; Add a certain amount of carbon, strengthen crystal boundary on the one hand, come reinforced alloys with more carbide of formation such as hafnium, niobium, chromium on the other hand; Alloying element such as tungsten, cobalt mainly plays the vital role of solid solution strengthened alloy, and W+Hf+Nb content is the important parameter that increases creep life, along with the increase of their content increases creep life thereupon.Co is little to the influence of the heat resistance of alloy, but can significantly improve the plasticity of alloy, and Co can improve the creep life under heavily stressed.Alloy sample of the present invention adopts current in the world vacuum casting furnace preparation, waters the sample that outpours and foundry goods without thermal treatment, can directly use, thereby cost is low the efficient height.
Be that with embodiment 1 difference the alloying constituent of present embodiment sees shown in the table 4 that the pairing alloy tensile property of alloy is as shown in table 5:
Table 4 alloy element component (wt.%)
| C | Cr | Co | Nb | Al | W | Ti | Hf | B | Zr | Ce | La | Ni |
| 0.08 | 5.2 | 8.0 | 1.6 | 5.6 | 15.3 | 1.2 | 1.2 | 0.025 | 0.005 | 0.005 | 0.02 | Surplus |
Table 5 alloy tensile property
Can find out from the alloy tensile property of table 5; Alloy of the present invention is less in room temperature to 800 ℃ tensile strength rangeability, all more than 910MPa, surpasses 800 ℃ of back draft intensity and progressively reduces; But can also reach 600MPa 1000 ℃ of tensile strengths; Tensile strength than most of equiax crystal superalloys is all high, and like K417G and K418 etc., visible this alloy has more excellent high temperature tensile properties.
Embodiment 3:
Be that with embodiment 2 differences the alloying constituent of present embodiment sees shown in the table 6 that the pairing alloy enduring quality of alloy is as shown in table 7:
Table 6 alloy element component (wt.%)
| C | Cr | Co | Nb | Al | W | Ti | Hf | B | Zr | Ce | La | Ni |
| 0.14 | 4.6 | 6.0 | 2.1 | 6.2 | 16.5 | 0.7 | 0.7 | 0.005 | 0.03 | 0.02 | 0.005 | Surplus |
Table 7 alloy representative temperature enduring quality
As shown in Figure 1, can find out that from the strong parametric synthesis curve of heat of alloy of the present invention and comparative alloy alloy of the present invention is along with the raising of the strong parameter of heat, the permanent stress of alloy progressively reduces; Particularly behind the strong parameter P=26 of heat, the permanent stress decline scope is very big.Comparative alloy also has similar rule, but compares with comparative alloy K417G (the same), and alloy enduring quality of the present invention has remarkable advantages.
Embodiment 4
Be that with embodiment 3 differences the alloying constituent of present embodiment sees shown in the table 7 that the pairing alloy creep curve of alloy is as shown in Figure 2.
Table 7 alloy element component (wt.%)
| C | Cr | Co | Nb | Al | W | Ti | Hf | B | Zr | Ce | La | Ni |
| 0.12 | 5.0 | 7.0 | 1.9 | 5.9 | 15.9 | 0.95 | 0.95 | 0.015 | 0.015 | 0.01 | 0.01 | Surplus |
As shown in Figure 2; Never synthermal creep curve can be found out; The creep of this alloy mainly shows as triphasic creeping characteristic, promptly initial (first) stage creep, stable state (second) stage creep and acceleration (the 3rd) creep, and creep speed then demonstrates and reduces the trend that increases again earlier.In the creep fs, the alloy deformation amount is accumulated rapidly.The starting stage creep compliance descends in the back strain rate that acquires a certain degree gradually, and creep begins to get into subordinate phase.Creep stable state (second) stage has occupied most ratio in whole creep life, got into very long platform area at this stage creep curve, and the creep strain amount of alloy does not almost increase.Alloy begins the back strain rate in the creep phase III and increases rapidly, and ruptures at short notice.Under the same test temperature condition, along with the minimizing of stress, obviously improve creep life.
The result shows that the present invention has preferable enduring quality, 975 ℃ with 235.2MPa condition following creep rupture life >=40 hours; Can directly cast use, cost is low, and production efficiency is high, can be used for preparing the hot-end components such as aircraft engine and turbine blade of gas turbine of 1100 ℃ of long term operations.Particularly adopt this refractory alloy to make generating and use turbine blade of gas turbine, can significantly improve gas turbine operation temperature and efficient, and then significantly improve generating efficiency.
Claims (6)
1. one kind contains the Ni-based equiax crystal alloy of the high tungsten of hafnium, it is characterized in that by weight percentage, alloying constituent is following:
C 0.08～0.14, and Cr 4.6～5.2, and Al 5.6～6.2, and Ti 0.7～1.2, and Co 6.0～8.0, and Hf 0.7～1.2, W15.3～16.5, and Nb 1.6～2.1, and B 0.005～0.025, and Zr 0.005～0.03, and Ni is surplus.
2. according to the described Ni-based equiax crystal alloy of the high tungsten of hafnium that contains of claim 1, it is characterized in that on said alloying constituent basis, add Ce 0.005～0.02, La 0.005～0.02.
3. according to the described Ni-based equiax crystal alloy of the high tungsten of hafnium that contains of claim 1, it is characterized in that aluminium titanium content 6.5wt%＜Al+Ti＜8.0wt%.
4. according to the described Ni-based equiax crystal alloy of the high tungsten of hafnium that contains of claim 1, it is characterized in that tungsten niobium hafnium content W+Nb+Hf＞18wt%.
5. according to the described application that contains the Ni-based equiax crystal alloy of the high tungsten of hafnium of claim 1, it is characterized in that the said Ni-based equiax crystal alloy of the high tungsten of hafnium that contains is used to prepare the aircraft engine of 1100 ℃ of long term operations and the hot-end component of turbine blade of gas turbine.
6. according to the described application that contains the Ni-based equiax crystal alloy of the high tungsten of hafnium of claim 5, it is characterized in that, the said Ni-based equiax crystal alloy of the high tungsten of hafnium that contains, 975 ℃ with 235.2MPa condition following creep rupture life >=40 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110388166 CN102433467B (en) | 2011-11-29 | 2011-11-29 | Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110388166 CN102433467B (en) | 2011-11-29 | 2011-11-29 | Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102433467A true CN102433467A (en) | 2012-05-02 |
| CN102433467B CN102433467B (en) | 2013-09-04 |
Family
ID=45981813
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110388166 Active CN102433467B (en) | 2011-11-29 | 2011-11-29 | Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102433467B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105002397A (en) * | 2015-07-29 | 2015-10-28 | 江苏美特林科特殊合金有限公司 | K418 cast superalloy purification smelting method |
| 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 |
| CN110438371A (en) * | 2019-08-06 | 2019-11-12 | 北京科技大学 | A kind of low segregation control of the high cobalt as cast condition nickel alloy of high tungsten and plasticity method for improving |
| CN111148587A (en) * | 2017-09-21 | 2020-05-12 | 国家科学研究中心 | Alloy turbine assembly comprising MAX phases |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11310839A (en) * | 1998-04-28 | 1999-11-09 | Hitachi Ltd | Grain-oriented solidification casting of high strength nickel-base superalloy |
| JP2006045654A (en) * | 2004-08-09 | 2006-02-16 | Hitachi Ltd | Ni-BASED SUPERALLOY FOR UNIDIRECTIONAL SOLIDIFICATION HAVING SUPERIOR STRENGTHS IN SOLIDIFICATION DIRECTION AND OF GRAIN BOUNDARY, CASTING, AND HOT PARTS FOR GAS TURBINE |
-
2011
- 2011-11-29 CN CN 201110388166 patent/CN102433467B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11310839A (en) * | 1998-04-28 | 1999-11-09 | Hitachi Ltd | Grain-oriented solidification casting of high strength nickel-base superalloy |
| JP2006045654A (en) * | 2004-08-09 | 2006-02-16 | Hitachi Ltd | Ni-BASED SUPERALLOY FOR UNIDIRECTIONAL SOLIDIFICATION HAVING SUPERIOR STRENGTHS IN SOLIDIFICATION DIRECTION AND OF GRAIN BOUNDARY, CASTING, AND HOT PARTS FOR GAS TURBINE |
Non-Patent Citations (1)
| Title |
|---|
| 郑运荣等: "《高温合金与钢的彩色金相研究》", 31 July 1999, article "高温合金与钢的彩色金相研究", pages: 6-10 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105002397A (en) * | 2015-07-29 | 2015-10-28 | 江苏美特林科特殊合金有限公司 | K418 cast superalloy purification smelting method |
| CN105002397B (en) * | 2015-07-29 | 2017-09-01 | 江苏美特林科特殊合金有限公司 | K418 cast superalloy sublimate smelting processes |
| 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 |
| CN111148587A (en) * | 2017-09-21 | 2020-05-12 | 国家科学研究中心 | Alloy turbine assembly comprising MAX phases |
| CN111148587B (en) * | 2017-09-21 | 2022-04-12 | 国家科学研究中心 | Alloy turbine assembly comprising MAX phases |
| CN110438371A (en) * | 2019-08-06 | 2019-11-12 | 北京科技大学 | A kind of low segregation control of the high cobalt as cast condition nickel alloy of high tungsten and plasticity method for improving |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102433467B (en) | 2013-09-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9574451B2 (en) | Ni-based superalloy, and turbine rotor and stator blades for gas turbine using the same | |
| RU2433197C2 (en) | Heat-resistant nickel-based alloy, part manufacturing method, and turbomachine part | |
| US8876989B2 (en) | Low rhenium nickel base superalloy compositions and superalloy articles | |
| EP1650319B1 (en) | Ni-Fe based super alloy, process of producing the same, and gas turbine | |
| CN105506387B (en) | A kind of nickel-base high-temperature single crystal alloy of high specific creep intensity and its preparation method and application | |
| US20130230405A1 (en) | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles | |
| CN100482824C (en) | Single crystal high temperature nickel base alloy containing rhenium and its preparing process | |
| CN112981186B (en) | High-temperature alloy with low-layer fault energy, structural component and application thereof | |
| CN102433467B (en) | Hafnium-containing high-tungsten-nickel-based isometric crystal alloy and application thereof | |
| CN102471833A (en) | Ni-based monocrystalline superalloy and turbine blade | |
| EP2537951B1 (en) | Ni-based alloy, and turbine rotor and stator blade for gas turbine | |
| CN107630152A (en) | A kind of nickel-based isometric crystal alloy and its Technology for Heating Processing and application containing yttrium and hafnium | |
| CN104911407A (en) | Re/Ru-containing monocrystal nickel-based superalloy with high temperature resistant capability and high creep resistance | |
| CN101974708A (en) | Hot erosion resisting directionally solidified nickel-based cast superalloy | |
| CN115354195A (en) | Crack-resistant nickel-based high-temperature alloy and preparation method and application thereof | |
| CN116529459A (en) | Nickel-based superalloys with high oxidation resistance, high corrosion resistance and good workability | |
| CN112176224A (en) | High-strength nickel-based single crystal superalloy with excellent comprehensive performance | |
| JP2014051698A (en) | Ni-BASED FORGING ALLOY, AND GAS TURBINE USING THE SAME | |
| CN111254317A (en) | Nickel-based casting alloy and preparation method thereof | |
| CN115572861B (en) | Nickel-based superalloy easy to machine and form and preparation method and application thereof | |
| JP2014005528A (en) | Ni-BASED HEAT-RESISTANT ALLOY AND TURBINE COMPONENT | |
| US20160032426A1 (en) | Optimized nickel alloy and turbine blade made thereof | |
| Wahl et al. | CMSX-4® Plus (SLS): An Improved 3rd Generation Single Crystal Alloy | |
| CN116287867A (en) | Bending crack-free nickel-based superalloy, and preparation method and application thereof | |
| US20190241995A1 (en) | Nickel Based Alloy with High Fatigue Resistance and Methods of Forming the Same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210809 Address after: 110172 block C12, south of Shendong Sixth Road, west of Zhongxing Street, Shenfu new area, Shenyang City, Liaoning Province Patentee after: Liaoning Hongyin Metal Co.,Ltd. Address before: 110016 No. 72, Wenhua Road, Shenhe District, Liaoning, Shenyang Patentee before: INSTITUTE OF METAL RESEARCH CHINESE ACADEMY OF SCIENCES |
|
| TR01 | Transfer of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A high tungsten nickel based equiaxed alloy containing hafnium and its application Effective date of registration: 20220225 Granted publication date: 20130904 Pledgee: Fushun Bank Co.,Ltd. Development Zone sub branch Pledgor: Liaoning Hongyin Metal Co.,Ltd. Registration number: Y2022210000012 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |