EP3329025A1 - A nickel-based alloy - Google Patents
A nickel-based alloyInfo
- Publication number
- EP3329025A1 EP3329025A1 EP16744473.6A EP16744473A EP3329025A1 EP 3329025 A1 EP3329025 A1 EP 3329025A1 EP 16744473 A EP16744473 A EP 16744473A EP 3329025 A1 EP3329025 A1 EP 3329025A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- nickel
- weight percent
- based alloy
- rhenium
- 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 239
- 239000000956 alloy Substances 0.000 title claims abstract description 239
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 107
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 53
- 239000000203 mixture Substances 0.000 claims abstract description 76
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 62
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 55
- 229910052702 rhenium Inorganic materials 0.000 claims abstract description 51
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims abstract description 51
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 47
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 46
- 239000010937 tungsten Substances 0.000 claims abstract description 46
- KJTLSVCANCCWHF-UHFFFAOYSA-N Ruthenium Chemical compound [Ru] KJTLSVCANCCWHF-UHFFFAOYSA-N 0.000 claims abstract description 41
- 229910052707 ruthenium Inorganic materials 0.000 claims abstract description 41
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 37
- 239000004411 aluminium Substances 0.000 claims abstract description 36
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 36
- 239000011651 chromium Substances 0.000 claims abstract description 24
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 24
- 239000010941 cobalt Substances 0.000 claims abstract description 24
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 24
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 21
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 16
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 15
- 239000011733 molybdenum Substances 0.000 claims abstract description 15
- 239000010936 titanium Substances 0.000 claims abstract description 15
- 239000010955 niobium Substances 0.000 claims abstract description 13
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 12
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 11
- 239000012535 impurity Substances 0.000 claims abstract description 10
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 10
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 9
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims abstract description 8
- 239000005864 Sulphur Substances 0.000 claims abstract description 8
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 7
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 7
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052796 boron Inorganic materials 0.000 claims abstract description 6
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 6
- 239000010703 silicon Substances 0.000 claims abstract description 6
- 229910052684 Cerium Inorganic materials 0.000 claims abstract description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 4
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 4
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 4
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 4
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims abstract description 3
- 239000013078 crystal Substances 0.000 claims description 31
- 230000003647 oxidation Effects 0.000 description 29
- 238000007254 oxidation reaction Methods 0.000 description 29
- 238000007792 addition Methods 0.000 description 26
- 238000013461 design Methods 0.000 description 24
- 230000000694 effects Effects 0.000 description 22
- 238000010438 heat treatment Methods 0.000 description 15
- 238000000034 method Methods 0.000 description 14
- 229910000601 superalloy Inorganic materials 0.000 description 12
- 230000015572 biosynthetic process Effects 0.000 description 10
- 238000004364 calculation method Methods 0.000 description 10
- 239000000463 material Substances 0.000 description 9
- 238000005266 casting Methods 0.000 description 8
- 238000012545 processing Methods 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 7
- 230000002829 reductive effect Effects 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 5
- 230000002939 deleterious effect Effects 0.000 description 5
- 239000011572 manganese Substances 0.000 description 5
- 238000000638 solvent extraction Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 4
- 125000004122 cyclic group Chemical group 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 239000002244 precipitate Substances 0.000 description 4
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 229910052748 manganese Inorganic materials 0.000 description 3
- 238000005192 partition Methods 0.000 description 3
- 230000001681 protective effect Effects 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- 229910001027 TMS-162 Inorganic materials 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 238000004090 dissolution Methods 0.000 description 2
- 239000000374 eutectic mixture Substances 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 238000010587 phase diagram Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000003775 Density Functional Theory Methods 0.000 description 1
- 208000016311 Freckling Diseases 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 229910002064 alloy oxide 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
- 238000012512 characterization method Methods 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- -1 for example Inorganic materials 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000010561 standard procedure Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000036962 time dependent Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000000844 transformation Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
Definitions
- the present invention relates to a nickel-based single crystal superalloy composition designed for high performance jet propulsion applications.
- the alloy - a fourth generation single crystal nickel-based superalloy - exhibits a combination of creep resistance and oxidation resistance which is comparable or better than equivalent grades of alloy.
- the density, cost, processing and long term stability of the alloy have also been considered in the design of the new alloy.
- Table 1 Examples of typical compositions of fourth generation nickel-based single crystal superalloys are listed in Table 1. These alloys may be used for the manufacture of rotating/stationary turbine blades used in gas turbine engines.
- Table 1 Nominal composition in wt. % of commercially used fourth generation single crystal turbine blade alloys.
- It is an aim of the invention is to provide an alloy which has similar or improved high temperature behaviour in comparison to the fourth generation alloys listed in Table 1.
- the present invention provides a nickel-based alloy composition consisting, in weight percent, of: between 3.5 and 6.5% chromium, between 0.0 and 12.0% cobalt, between 4.5 and 11.5% tungsten, between 0.0 and 0.5% molybdenum, between 3.5 and 7.0% rhenium, between 1.0 and 3.7% ruthenium, between 3.7 and 6.8% aluminium, between 5.0 and 9.0% tantalum, between 0.0 and 0.5% hafnium, between 0.0 and 0.5% niobium, between 0.0 and 0.5% titanium, between 0.0 and 0.5% vanadium, between 0.0 and 0.1% silicon, between 0.0 and 0.1%) yttrium, between 0.0 and 0.1% lanthanum, between 0.0 and 0.1% cerium, between 0.0 and 0.003%) sulphur, between 0.0 and 0.05% manganese, between 0.0 and 0.05% zirconium, between 0.0 and 0.005% boron, between 0.0 and 0.01% carbon, the balance being nickel and incidental impurities.
- the nickel-based alloy composition provides a good balance between cost, density and creep and oxidation resistance.
- the nickel-based alloy composition consists, in weight percent, of between 4.0 and 5.0% chromium. Such an alloy is particularly resistant to TCP formation whilst still having good oxidation resistance.
- the nickel-based alloy composition contains at least 0.1 wt% cobalt to increase creep resistance and lower the ⁇ ' solvus temperature thereby to increase the solutioning window.
- the nickel-based alloy composition consists, in weight percent, of between 7.0 and 1 1.0% cobalt.
- Such an alloy has improved resistance to creep deformation with a limited level of creep anisotropy (orientation dependence) being observed and has increased ease of processing due to a reduced ⁇ ' solvus temperature.
- a maximum amount of cobalt of 10.9%) further limits creep anisotropy.
- the nickel-based alloy composition consists, in weight percent, of between 7.0 and 9.5% tungsten. This composition strikes a compromise between reduced cost, low weight and creep resistance. In an embodiment, the nickel-based alloy composition consists, in wt%>, of at least 7.1% tungsten in order to achieve high creep resistance.
- the nickel-based alloy composition consists, in weight percent, of between 3.7 and 6.6% aluminium, preferably between 5.1 and 6.6% aluminium, or more preferably 5.5 and 6.6%> aluminium. This composition achieves high creep resistance and reduced density alongside increased oxidation resistance.
- the nickel-based alloy composition consists, in weight percent, of between 5.0 and 9.0% tantalum. This provides a balance between creep resistance, ease of manufacture (based upon solutioning window) and density and/or prevents the possibility of formation of the Eta ( ⁇ ) phase Ni 3 Ta.
- the alloy consists of between 5.0 and 7.3% tantalum. This reduces the cost and density of the alloy further, increases the solutioning window as well as the propensity for ⁇ phase formation.
- the nickel-based alloy composition consists, in weight percent, of 0.1%) or more molybdenum. This is advantageous for improved creep resistance.
- the nickel-based alloy composition consists, in weight percent of, between 4.5 and 6.0% rhenium, or more preferably 5.3 and 6.0% rhenium. This composition provides a good balance of creep resistance, density, resistance to TCP formation and cost.
- the nickel-based alloy composition consists, in weight percent of, between 2.0 and 3.0% ruthenium. This composition provides a good balance of creep resistance and cost. An even better compromise is provided in the range of 2.1 and 2.9% ruthenium.
- the nickel-based alloy composition consists, in weight percent, of between 0.0 and 0.2% hafnium. This is optimum for tying up incidental impurities in the alloy, for example, carbon.
- the nickel-based alloy composition is such that the following equation is satisfied in which ⁇ ⁇ and WAI are the weight percent of tantalum and aluminium in the alloy respectively 33 ⁇ ⁇ ⁇ + 5.1 WAI ⁇ 39. This is advantageous as it allows a suitable volume fraction ⁇ ' to be present.
- the nickel-based alloy composition is such that the following equation is satisfied in which Wi a and WAI are the weight percent of tantalum and aluminium in the alloy respectively 2.2 ⁇ 5.15 WAI - 0.5 WAI 2 -W Ta ; preferably 2.9 ⁇ 5.15 WAI - 0.5 WAI 2 -Wia. This is advantageous as it allows a suitable solutioning window for the alloy to allow for heat-treatment processes.
- the nickel-based alloy composition is such that the following equation is satisfied in which WR u and WR e are the weight percent of ruthenium and rhenium in the alloy respectively 4.5 > W Ru + 0.225 W Re ; preferably 3.9 > W Ru + 0.225 W Re . This is advantageous as it results in an alloy with a relatively low cost.
- the nickel-based alloy composition is such that the following equation is satisfied in which WR e and Ww are the weight percent of rhenium and tungsten in the alloy respectively 15.8 > 1.13 W Re + W W; preferably 14.4 > 1.13 W Re + Ww. This is advantageous as it results in an alloy with a relatively low density.
- the nickel-based alloy composition is such that the following equation is satisfied in which WR e , WMO and Ww are the weight percent of rhenium, molybdenum and tungsten in the alloy respectively 21.9 ⁇ 2.92 WR e + (WW + WMO); preferably 24.6 ⁇ 2.92 WR e + (Ww + WMO).
- WR e , WMO and Ww are the weight percent of rhenium, molybdenum and tungsten in the alloy respectively 21.9 ⁇ 2.92 WR e + (WW + WMO); preferably 24.6 ⁇ 2.92 WR e + (Ww + WMO).
- the sum of the elements niobium, titanium and vanadium, in weight percent is less than 1%, preferably 0.5% or less. This means that those elements do not have too much of a deleterious effect on environmental resistance of the alloy.
- the sum of the elements niobium, titanium, vanadium and tantalum is between 5.0 - 9.0 wt.%, preferably 5.0 - 7.3 wt.%. This results in a preferred volume fraction of ⁇ ' and APB energy.
- the nickel-based alloy composition has between 60 and 70% volume fraction ⁇ '.
- a single crystal article is provided, formed of the nickel-based alloy composition of any of the previous embodiments.
- a turbine blade for a gas turbine engine is provided, formed of an alloy according to any of the previous embodiments.
- a gas turbine engine comprising the turbine blade of the previous embodiment is provided.
- Figure 1 shows the partitioning coefficient for the main components in the alloy design space
- Figure 2 is a contour plot showing the effect of ⁇ ' forming elements aluminium and tantalum on volume fraction of ⁇ ' for alloys within the alloy design space, determined from phase equilibrium calculations conducted at 900°C;
- Figure 3 is a contour plot showing the effect of elements aluminium and tantalum on anti-phase boundary energy, for alloys with a volume fraction of ⁇ ' between 60-70%) at 900°C;
- Figure 4 is a contour plot showing the effect of elements aluminium and tantalum on the solutioning window for alloys with a volume fraction of ⁇ ' between 60-70%) at 900°C
- Figure 5 is a contour plot showing the effect of rhenium and ruthenium content on raw elemental cost, for alloys with a volume fraction of ⁇ ' between 60-70% at 900°C with tantalum between 5 - 9 wt.%;
- Figure 6 is a contour plot showing the effect rhenium and tungsten on density, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5 - 9 wt.%;
- Figure 7 is a contour plot showing the effect of elements rhenium and tungsten on the creep resistance, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5-9 wt.%, which contain 0 wt.% ruthenium;
- Figure 8 is a contour plot showing the effect of elements rhenium and tungsten on the creep resistance, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5-9 wt.%, which contain 1 wt.% ruthenium;
- Figure 9 is a contour plot showing the effect of elements rhenium and tungsten on the creep resistance, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5-9 wt.%, which contain 2 wt.% ruthenium;
- Figure 10 is a contour plot showing the effect of elements rhenium and tungsten on the creep resistance, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5-9 wt.%, which contain 3 wt.% ruthenium;
- Figure 11 is a contour plot showing the effect of elements chromium and tungsten on microstructural stability, for alloys with a volume fraction of ⁇ ' between 60-70%> at 900°C with tantalum between 5-9 wt.% and between 1-3 wt.% ruthenium, which contain 4 wt.% rhenium;
- Figure 12 is a contour plot showing the effect of elements chromium and tungsten on microstructural stability, for alloys with a volume fraction of ⁇ ' between 60-70%) at 900°C with tantalum between 5-9 wt.% and between 1-3 wt.% ruthenium, which contain 5 wt.% rhenium;
- Figure 13 is a contour plot showing the effect of elements chromium and tungsten on microstructural stability, for alloys with a volume fraction of ⁇ ' between 60-70%) at 900°C with tantalum between 5-9 wt.% and between 1-3 wt.% ruthenium, which contain 6 wt.% rhenium;
- Figure 14 is a contour plot showing the effect of elements chromium and tungsten on microstructural stability, for alloys with a volume fraction of ⁇ ' between 60-70%) at 900°C with tantalum between 5-9 wt.% and between 1-3 wt.% ruthenium, which contain 7 wt.% rhenium;
- Figure 15 is a contour plot showing the effect of cobalt on the ⁇ ' solvus temperature for alloys with different ratios of aluminium to tantalum, where the alloys have a volume fraction of ⁇ ' between 60-70% at 900°C with tantalum between 5 - 9 wt.%;
- Figure 16 shows the time to 1% creep strain for alloy ABD-2 of the present invention (circles) compared with the fourth generation single crystal turbine blade alloy TMS-138A (triangles);
- Figure 17 shows the time to rupture for alloy ABD-2 of the present invention (circles) compared with the fourth generation single crystal turbine blade alloy TMS-138A (triangles); and Figure 18 is a plot of measured weight change for the fourth generation single crystal turbine blade alloy TMS-138A (triangles) and alloy ABD-2 of the present invention (circles) when oxidised in air at 1000°C.
- nickel-based superalloys have been designed through empiricism. Thus their chemical compositions have been isolated using time consuming and expensive experimental development, involving small-scale processing of limited quantities of material and subsequent characterisation of their behaviour. The alloy composition adopted is then the one found to display the best, or most desirable, combination of properties. The large number of possible alloying elements indicates that these alloys are not entirely optimised and that improved alloys are likely to exist.
- superalloys generally additions of chromium (Cr) and aluminium (Al) are added to impart resistance to oxidation, cobalt (Co) is added to improve resistance to sulphidisation.
- molybdenum (Mo), tungsten (W), Co, rhenium (Re) and sometimes ruthenium (Ru) are introduced, because these retard the thermally-activated processes - such as, dislocation climb - which determine the rate of creep deformation.
- aluminium (Al), tantalum (Ta) and titanium (Ti) are introduced as these promote the formation of the precipitate hardening phase gamma-prime ( ⁇ '). This precipitate phase is coherent with the face-centered cubic (FCC) matrix phase which is referred to as gamma (y).
- ABS Alloys-By-Design
- the first step in the design process is the definition of an elemental list along with the associated upper and lower compositional limits.
- the compositional limits for each of the elemental additions considered in this invention - referred to as the "alloy design space" - are detailed in Table 2.
- the second step relies upon thermodynamic calculations used to calculate the phase diagram and thermodynamic properties for a specific alloy composition. Often this is referred to as the CALPHAD method (CALculate PHAse Diagram). These calculations are conducted at the service temperature for the new alloy (900°C), providing information about the phase equilibrium (microstructure).
- CALPHAD method CALculate PHAse Diagram
- These calculations are conducted at the service temperature for the new alloy (900°C), providing information about the phase equilibrium (microstructure).
- a third stage involves isolating alloy compositions which have the desired microstructural architecture. In the case of single crystal superalloys which require superior resistance to creep deformation, the creep rupture life is maximised when the volume fraction of the precipitate hardening phase ⁇ ' lies between 60%-70%.
- the lattice misfit ⁇ is defined as the mismatch between ⁇ and ⁇ ' phases, and is determined according to
- ⁇ — ⁇ 7 - (1) a y , + a r
- a y and ⁇ ⁇ ⁇ are the lattice parameters of the ⁇ and ⁇ ' phases.
- Rejection of alloy on the basis of unsuitable microstructural architecture is also made from estimates of susceptibility to topologically close-packed (TCP) phases.
- TCP topologically close-packed
- the present calculations predict the formation of the deleterious TCP phases sigma ( ⁇ ), P and mu ( ⁇ ) using CALPHAD modelling.
- ⁇ deleterious TCP phases
- P and mu ⁇
- the model isolates all compositions in the design space which are calculated to result in a volume fraction of ⁇ ' of between 60 and 70%, which have a lattice misfit ⁇ ' of less than a predetermined magnitude and have a total volume fraction of TCP phases below a predetermined magnitude.
- merit indices are estimated for the remaining isolated alloy compositions in the dataset. Examples of these include: creep-merit index (which describes an alloy's creep resistance based solely on mean composition), anti-phase boundary (APB) energy, density, cost and solutioning window.
- creep-merit index which describes an alloy's creep resistance based solely
- the calculated merit indices are compared with limits for required behaviour, these design constraints are considered to be the boundary conditions to the problem. All compositions which do not fulfil the boundary conditions are excluded. At this stage, the trial dataset will be reduced in size quite markedly.
- the final, sixth stage involves analysing the dataset of remaining compositions. This can be done in various ways. One can sort through the database for alloys which exhibit maximal values of the merit indices - the lightest, the most creep resistant, the most oxidation resistant, and the cheapest for example. Or alternatively, one can use the database to determine the relative trade-offs in performance which arise from different combination of properties.
- the first merit index is the creep-merit index.
- time-dependent deformation i.e. creep
- dislocation creep time- dependent deformation of a single crystal superalloy occurs by dislocation creep with the initial activity being restricted to the ⁇ phase.
- the rate-controlling step is then the escape of trapped configurations of dislocations from ⁇ / ⁇ ' interfaces, and it is the dependence of this on local chemistry which gives rise to a significant influence of alloy composition on creep properties.
- a physically-based microstructure model can be invoked for the rate of accumulation of creep strain ⁇ when loading is uniaxial and along the (00l) crystallographic direction.
- the equation set is where P m is the mobile dislocation density, ⁇ ⁇ is the volume fraction of the ⁇ ' phase, and ⁇ is width of the matrix channels.
- O and T are the applied stress and temperature, respectively.
- b and k are the Burgers vector and Boltzmann constant, respectively.
- the term ⁇ + 2 ⁇ ⁇ ⁇ 3 / 3 ⁇ 3 ⁇ (1— ⁇ p 1/3 ) is a constraint factor, which accounts for the close proximity of the cuboidal particles in these alloys.
- Equation 3 describes the dislocation multiplication process which needs an estimate of the multiplication parameter C and the initial dislocation density.
- D eS is the effective diffusivity controlling the climb processes at the particle/matrix interfaces. Note that in the above, the composition dependence arises from the two terms ⁇ ⁇ and
- the second merit index is for anti-phase boundary (APB) energy.
- APB anti-phase boundary
- Increasing the APB energy has been found to improve mechanical properties including, tensile strength and resistance to creep deformation.
- the APB energy was studied for a number of Ni-Al-X systems using density functional theory. From this work the effect of ternary elements on the APB energy of the ⁇ ' phase was calculated, linear superposition of the effect for each ternary addition was assumed when considering complex multicomponent systems, resulting in the following equation,
- YAPB 195— 1.7x Cr — 1.7x Mo + 4.6x w + 27.1x Ta + 21Ax Nb + lSx Ti (5)
- xc r , XMO, XW, ⁇ , xm and xn represent the concentrations, in atomic percent, of Cr, Mo, W, Ta, Nb and Ti in the ⁇ ' phase, respectively.
- the composition of the ⁇ ' phase is determined from phase equilibrium calculations.
- the third merit index is density.
- the density, p was calculated using a simple rule of mixtures and a correctional factor, where, p ( is the density for a given element and Xi is the atomic fraction of the alloy element.
- the fourth merit index was cost.
- Xj weight fraction of the alloy element
- a fifth merit index is the solutioning window.
- CALPHAD thermodynamic modelling
- the temperature at which completed dissolution of the ⁇ ' phase (known as the ⁇ ' solvus temperature) occurs must be known, as must the solidus temperature.
- the difference between the solidus temperature and the ⁇ ' solvus temperature will give the solutioning window. So the solutioning window index calculates as the difference between the solidus temperature and the ⁇ ' solvus temperature.
- the ABD method described above was used to isolate the inventive alloy composition.
- the design intent for this alloy was to isolate the composition of a fourth generation single crystal nickel-based superalloy that exhibits a combination of creep resistance and oxidation resistance which is comparable or better than equivalent grades of alloy.
- the density, cost, processing and long term stability of the alloy have also been considered in the design of the new alloy.
- the material properties - determined using the ABD method - for the commercially used fourth generation single crystal turbine blade alloys are is listed in Table 3.
- the design of the new alloy was considered in relation to the predicted properties listed for these alloys.
- the calculated material properties for an alloy ABD-2 with a nominal composition according to Table 4 and in accordance with the present invention are also given.
- Table 3 Calculated phase fractions and merit indices made with the " Alloy s-by-Design " software. Results for fourth generation single crystal turbine blades listed in Table 1 and the nominal composition of the new alloy ABD-2 listed in Table 4.
- Optimisation of the alloy's microstructure - primarily comprised of an austenitic face centre cubic (FCC) gamma phase ( ⁇ ) and the ordered Ll 2 precipitate phase ( ⁇ ') - was required to maximise creep resistance.
- a volume fraction of the ⁇ ' phase between 60-70% is generally regarded as optimum as this microstructure is known to provide the maximum level of creep resistance in single crystal blade alloys.
- a volume fraction ⁇ ' of between 60 and 70% was the target for the present alloy but the inventive alloy may deviate from this target.
- the partitioning coefficient for each element included in the alloy design space was determined from phase equilibrium calculations conducted at 900°C, Figure 1.
- a partitioning coefficient of unity describes an element with equal preference to partition to the ⁇ or ⁇ ' phase.
- a partitioning coefficient less than unity describes an element which has a preference for the ⁇ ' phase, the closer the value to zero the stronger the preference. The greater the value above unity the more an element prefers to reside within the ⁇ phase.
- the partitioning coefficients for aluminium and tantalum show that these are strong ⁇ ' forming elements.
- aluminium and tantalum partition most strongly to the ⁇ ' phase. Hence, aluminium and tantalum levels were controlled to produce the desired ⁇ ' volume fraction.
- Figure 2 shows the effect the elements which are added to form the ⁇ ' phase - predominantly aluminium and tantalum - have on the fraction of ⁇ ' phase in the alloy at the operation temperature, 900°C in this instance.
- this alloy compositions which result in a volume fraction of ⁇ ' between 60-70% were considered. Hence between 3.7 and 6.8 weight percent (wt.%) of aluminium was required.
- Optimisation of aluminium and tantalum levels was also required to increase the antiphase boundary (APB) energy of the ⁇ ' phase.
- the APB energy is strongly dependent upon the chemistry of the ⁇ ' phase.
- Figure 3 shows the influence of aluminium and tantalum on the APB energy.
- the preferred minimum levels of tantalum ensure a higher APB energy for any given amount of aluminium and a level of at least 270 mJ/m 2 in the range of aluminium for the alloy. From Figure 2 it is seen that in particular for higher lower levels of tantalum, concentrations of aluminium of 5.1 wt.% or more, preferably 5.5 wt.% or more produce the desired volume fraction of ⁇ '.
- Niobium, titanium, vanadium elements behave in a similar way to that of tantalum i.e. they are gamma prime forming elements which increase anti-phase boundary energy. These elements can optionally be added to the alloy. The benefits of this may include lower cost and density in comparison to tantalum. However, additions of these elements must be limited as they can have a negative impact on the environmental resistance of the alloy. Therefore, those elements can each be present in an amount of up to 0.5 wt.%>.
- those elements are substituted for tantalum meaning that the sum of the elements consisting of niobium, titanium, vanadium and tantalum is preferably limited to 5.0-9.0 wt.%>, more preferably 5.0-7.3 wt.%> which are the preferred ranges for tantalum.
- the sum of the elements consisting of niobium, titanium and vanadium is preferably limited to below 1.0 wt.%> and preferably below 0.5 wt.%> so as to avoid reduction in environmental resistance of the alloy.
- the balance of aluminium and tantalum can be adjusted such that there is a balance between desired target volume fraction of ⁇ ' as well as a sufficiently high APB energy.
- consideration must also be given to the processing of the alloy.
- One such consideration is the solutioning window; there should exist a sufficient temperature range window, below the melting temperature of the alloy, across which only the ⁇ phase is stable.
- the solutioning window depends upon the dissolution of the ⁇ ' phase it is strongly influenced by ⁇ ' chemistry, hence, aluminium and tantalum content. This solutioning heat treatment is used to remove any residual microsegregation and eutectic mixtures rich in ⁇ ' which might occur during the casting processes used to produce the single crystal alloy.
- the solutioning window is greater than 50°C to allow for conventional processing methods.
- Figure 4 shows the solutioning window magnitude (in °C) for varying wt%> Al and Ta with a volume fraction ⁇ ' of 60-70%). From this Figure it can be seen that limiting the tantalum content to 9.0 wt.% ensures that the alloy has a suitable solutioning window.
- the tantalum content is limited to 7.3 wt.% as this produces an alloy with a solutioning window greater than 60°C further improving the processing of the alloy.
- APB energy greater than 270mJ/m 2 , solutioning window greater than 50°C the levels of refractory elements were determined for creep resistance and oxidation performance.
- the ruthenium content is limited to 3.0 wt.%) or less to ensure an optimal balance between cost and creep resistance.
- additions of ruthenium and rhenium preferably adhere to the following Equation,
- / ⁇ Cost W RU + 0.225V Re
- /(Cost) is a numerical value which is less than or equal to 4.5 to produce an alloy with a cost of 300$/lb or less and WR U and Wn e is the weight percent of ruthenium and rhenium in the alloy respectively.
- the numerical value for /(Cost) is less than or equal to 3.9 as this produces an alloy with a lower cost of 260$/lb or less .
- the additions of the elements tungsten, rhenium and ruthenium are optimised in order to design an alloy which is highly resistant to creep deformation.
- the creep resistance was determined by using the creep merit index model. It is desirable to maximise the creep merit index as this is associated with an improved creep resistance.
- the influence which tungsten, rhenium and ruthenium have on creep resistance is presented in Figures 7-10. It is seen that increasing the levels of tungsten, rhenium and ruthenium improve creep resistance. However, the quantities of tungsten and rhenium required mean that they have a strong influence on alloy density, Figure 6.
- the calculations to produce the graphs of Figures 6-10 are done such that the ⁇ ' volume fraction at 900°C is between 60 and 70%. Therefore the trade-off between creep resistance and alloy density must be balanced.
- f(Desnity) 1.13W Re + W w
- /(Density) is a numerical value which is less than or equal to 15.8 to produce an alloy with a density of 9.0 g/cm 3 or less
- Ww is the weight percent of tungsten in the alloy.
- the numerical value for /(Density) is less than or equal to 14.4 as this produces an alloy with a density of 8.9 g/cm 3 or less.
- Current fourth generation single crystal alloys have a creep merit index of 12 x 10 "15 m "
- the alloy contains at least 1.0 wt.% of ruthenium.
- the ruthenium content is 2.0 wt.% or greater more preferably 2.1 wt% or greater as this produces even higher creep resistance.
- Ruthenium is preferably limited to 3.0 wt.% as this gives the preferred balance between cost and creep resistance. A more preferred maximum level of ruthenium is 2.9 wt% yet further to reduce cost, whilst still benefiting from a high creep merit index. If the tungsten content is limited to 11.5 wt.% or less, the alloy density can be decreased to 9.0 g/cm 3 or less. Preferably the tungsten content is limited to 9.5 wt.% as this produces an alloy with an even lower density ( Figures 6 and 10). Lower levels of tungsten also ensure microstructural stability ( Figures 11- 14).
- a minimum content of rhenium of 3.5 wt.% or more is shown to produce a high creep merit index.
- the rhenium content is greater than 4.5 wt.% as this produces an alloy with a better balance between density ( Figure 6) and creep resistance ( Figure 10).
- Even more preferable is an alloy containing at least 5.3 wt.% of rhenium as this composition produces an alloy with an even better balance of creep resistance, density. In such an alloy cost can also be reduced as lower levels of ruthenium may be required ( Figure 9).
- molybdenum behaves in a similar way to tungsten i.e. this slow diffusing element can improve creep resistance. Therefore, it is preferred that molybdenum is present in an amount of at least 0.1 wt%. However, additions of molybdenum must be controlled as it strongly increases the alloys propensity to form deleterious TCP phases. Therefore, molybdenum is limited to 0.5 wt.% or less.
- a preferred lower limit of cobalt is 7.0 wt.% as this produces an alloy with improved creep resistance and a lower ⁇ ' solvus temperature which is beneficial for heat treatment processes.
- cobalt additions must be limited as high cobalt levels will increase the alloy's creep anisotropy, particularly in primary creep. This makes the creep rate strongly dependent upon orientation of the single crystal.
- An upper limit of 12.0 wt.% cobalt controls the amount of creep anisotropy to an acceptable level.
- a preferred upper limit is 11.0 wt.% as creep anisotropy is even less prevalent.
- a more desirable upper limit is 10.9 wt% even further to decrease the chance of creep anisotropy.
- the minimum chromium content for the present invention is greater than or equal to 3.5 wt.%) and preferably greater than or equal to 4.0wt.%> in order to attain oxidation resistance which is improved in comparison to current fourth generation single crystal alloys which have Cr contents ranging between 2.0-3.2 wt.%>. That is, a higher weight percent of chromium is provided than in the current fourth generation alloys on the basis that this will improve oxidation resistance compared to those alloys.
- the chromium content is limited to 6.5 wt.%> to reduce the propensity for the alloy to form the deleterious TCP phases ( Figures 11-14).
- the chromium content in the alloy is limited to 5.0 wt.%> as this produces an alloy with the best balance between oxidation resistance and microstructural stability.
- the rhenium content in the alloy is limited to 7.0 wt.%> or less (to ensure acceptable microstructural stability, Figure 14) and more preferably 6.0 wt.%> or less as rhenium at a level of between 4.5 wt.% and 6.0 wt.% provides a good balance between density, creep resistance and microstructural stability.
- the minimum tungsten level required for the present invention is 4.5 wt.% or more, as this provides a balance between creep resistance ( Figures 7-10), cost and microstructural stability ( Figures 11-14).
- a preferred minimum level of tungsten is 7.0 wt.%, desirably at least 7.1 wt%.
- impurities may include the elements carbon (C), boron (B), sulphur (S), zirconium (Zr) and manganese (Mn). If concentrations of carbon remain at 100 PPM or below (in terms of mass) the formation of unwanted carbide phases will not occur. Boron content is desirably limited to 50 PPM or less (in terms of mass) so that formation of unwanted boride phases will not occur. Carbide and boride phases tie up elements such as tungsten or tantalum which are added to provide strength to the ⁇ and ⁇ ' phases. Hence, mechanical properties including creep resistance are reduced if carbon and boron are present in greater amounts.
- the elements Sulphur (S) and Zirconium (Zr) preferably remain below 30 and 500 PPM (in terms of mass), respectively.
- Manganese (Mn) is an incidental impurity which is preferably limited to 0.05wt% (500PPM in terms of mass).
- Sulphur above 0.003 wt.% can lead to embrittlement of the alloy and sulphur also segregates to alloy/oxide interfaces formed during oxidation. This segregation may lead to increased spallation of protective oxide scales.
- the levels of zirconium and manganese must be controlled as these may create casting defects during the casting process, for example freckling.
- hafnium of up to 0.5 wt.%, or more preferably up to 0.2wt.% are beneficial for tying up incidental impurities in the alloy, in particular carbon.
- Hafnium is a strong carbide former, so addition of this element is beneficial as it will tie up any residual carbon impurities which may be in the alloy. It can also provide additional grain boundary strengthening, which is beneficial when low angle boundaries are introduced in the alloy.
- La and Cerium (Ce) may be beneficial up to levels of 0.1 wt.% to improve the adhesion of protective oxide layers, such as AI2O3.
- These reactive elements can 'mop-up' tramp elements, for example sulphur, which segregates to the alloy oxide interface weakening the bond between oxide and substrate leading to oxide spallation.
- additions of silicon to nickel based superalloys at levels up to 0.1 wt.% are beneficial for oxidation properties.
- silicon segregates to the alloy/oxide interface and improves cohesion of the oxide to the substrate. This reduces spallation of the oxide, hence, improving oxidation resistance.
- Table 4 Compositional range in wt. % for the newly design alloy.
- alloy ABD-2 was used to validate the key material properties aimed at with the alloy of the invention, mainly sufficient creep resistance and improved oxidation behaviour in comparison to that of a current single crystal alloys used for IGT applications.
- the behaviour of alloy ABD-2 was compared with alloy TMS-138-A, which was tested under the same experimental conditions.
- Single crystal castings of alloy ABD-2 of nominal composition according to Table 4 were manufactured using conventional methods for producing single crystal components.
- the castings were in the form of cylindrical bars of 10 mm diameter and 160 mm in length.
- the cast bars were confirmed to be single crystals with an orientation within 10° from the ⁇ 001> direction.
- the as cast material was given a series of subsequent heat treatments in order to produce the required ⁇ / ⁇ ' microstructure.
- a solution heat treatment was conducted at 1325°C for 6 hours, this was found to remove residual microsegregation and eutectic mixtures.
- the heat treatment window for the alloy was found to be sufficient to avoid incipient melting during the solution heat treatment.
- the alloy was given a two stage ageing heat treatment, the first stage conducted at 1120°C for 2 hours and the second stage conducted at 870°C for 16 hours.
- Creep specimens of 20 mm gauge length and 4 mm diameter were machined from fully heat-treated single crystal bars. The orientation of the test specimens were within 10° from the ⁇ 001> direction. Test temperatures ranging from 800 to 1100°C were used to evaluate the creep performance of the ABD-2 alloy. Cyclic oxidation tests were performed on the fully heat treated material. Cyclic oxidation tests were carried out at 1000°C using 2 hours cycles over a time period of 50 hours.
- a Larson-Miller diagram was used to compare the creep resistance of alloy ABD-2 with alloy TMS-138A.
- Figure 16 a comparison of time to 1% creep strain is presented for both alloys. The time to 1% strain is critical as most gas turbine components are manufactured to tight tolerances to achieve maximum engine performance. After low levels of strain - in the order of a few percent - components will often be replaced. It is seen that alloy ABD-2 is comparable to TMS-138A in time to 1% creep strain.
- Figure 17 shows a comparison of time to creep rupture for both alloys, it is seen that alloy ABD-2 has a rupture life comparable to that of TMS-138A. The oxidation behaviour of alloys ABD-2 and TMS-138A was also compared.
- the alloy ABD-2 was designed such that it would have improved oxidation behaviour relative to current second generation alloys. Cyclic oxidation results for ABD-2 and TMS-138A are presented in Figure 18. A reduction in mass gain with respect to time is evidence of improved oxidation behaviour as the formation of a protective oxide scale has occurred limiting the ingress of oxygen into the substrate material. The ABD-2 alloy shows significantly reduced weight gain with respect to time when compared to TMS-138A, indicative of improved oxidation performance.
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GB1513582.5A GB2540964A (en) | 2015-07-31 | 2015-07-31 | A nickel-based alloy |
PCT/GB2016/052199 WO2017021685A1 (en) | 2015-07-31 | 2016-07-20 | A nickel-based alloy |
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CN108350528B (en) | 2015-09-04 | 2020-07-10 | 思高博塔公司 | Chromium-free and low-chromium wear-resistant alloy |
FR3073526B1 (en) | 2017-11-14 | 2022-04-29 | Safran | NICKEL-BASED SUPERALLOY, SINGLE-CRYSTALLINE BLADE AND TURBOMACHINE |
FR3073527B1 (en) | 2017-11-14 | 2019-11-29 | Safran | SUPERALLIAGE BASED ON NICKEL, MONOCRYSTALLINE AUBE AND TURBOMACHINE |
FR3084671B1 (en) * | 2018-07-31 | 2020-10-16 | Safran | NICKEL-BASED SUPERALLY FOR MANUFACTURING A PART BY POWDER SHAPING |
JP2022505878A (en) | 2018-10-26 | 2022-01-14 | エリコン メテコ(ユーエス)インコーポレイテッド | Corrosion-resistant and wear-resistant nickel-based alloy |
GB2584905B (en) * | 2019-06-21 | 2022-11-23 | Alloyed Ltd | A nickel-based alloy |
TWI748203B (en) * | 2019-07-03 | 2021-12-01 | 中國鋼鐵股份有限公司 | Corrosion resistant high nickel alloy and method for manufacturing the same |
FR3101643B1 (en) * | 2019-10-08 | 2022-05-06 | Safran | AIRCRAFT PART IN SUPERALLOY COMPRISING RHENIUM AND/OR RUTHENIUM AND ASSOCIATED MANUFACTURING METHOD |
CN111254317B (en) * | 2020-01-19 | 2021-04-09 | 北京钢研高纳科技股份有限公司 | Nickel-based casting alloy and preparation method thereof |
CN112877781A (en) * | 2021-01-13 | 2021-06-01 | 中国航发北京航空材料研究院 | Nickel-based single crystal alloy, method for producing same, use thereof and heat treatment method |
CN115044805B (en) * | 2022-05-30 | 2023-04-11 | 北京科技大学 | Nickel-based single crystal superalloy with balanced multiple properties and preparation method thereof |
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US20030041930A1 (en) * | 2001-08-30 | 2003-03-06 | Deluca Daniel P. | Modified advanced high strength single crystal superalloy composition |
US6902633B2 (en) * | 2003-05-09 | 2005-06-07 | General Electric Company | Nickel-base-alloy |
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