CA2387828C - Ni-based single crystal super alloy - Google Patents
Ni-based single crystal super alloy Download PDFInfo
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- CA2387828C CA2387828C CA002387828A CA2387828A CA2387828C CA 2387828 C CA2387828 C CA 2387828C CA 002387828 A CA002387828 A CA 002387828A CA 2387828 A CA2387828 A CA 2387828A CA 2387828 C CA2387828 C CA 2387828C
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- single crystal
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- 239000013078 crystal Substances 0.000 title claims abstract description 43
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 36
- 238000001556 precipitation Methods 0.000 claims abstract description 29
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 19
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 18
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 18
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 16
- 239000000203 mixture Substances 0.000 claims abstract description 16
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 16
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 14
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 14
- 229910052702 rhenium Inorganic materials 0.000 claims abstract description 14
- 229910052707 ruthenium Inorganic materials 0.000 claims abstract description 13
- 239000012535 impurity Substances 0.000 claims abstract description 12
- 239000011159 matrix material Substances 0.000 claims description 21
- 239000002131 composite material Substances 0.000 description 35
- 229910045601 alloy Inorganic materials 0.000 description 33
- 239000000956 alloy Substances 0.000 description 33
- 239000002244 precipitate Substances 0.000 description 7
- 230000035882 stress Effects 0.000 description 5
- 230000032683 aging Effects 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 230000005496 eutectics Effects 0.000 description 3
- 238000004881 precipitation hardening Methods 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000000155 melt Substances 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 101150114464 ATRN gene Proteins 0.000 description 1
- 229910000995 CMSX-10 Inorganic materials 0.000 description 1
- 241000233803 Nypa Species 0.000 description 1
- 235000005305 Nypa fruticans Nutrition 0.000 description 1
- 241001237728 Precis Species 0.000 description 1
- VREFGVBLTWBCJP-UHFFFAOYSA-N alprazolam Chemical compound C12=CC(Cl)=CC=C2N2C(C)=NN=C2CN=C1C1=CC=CC=C1 VREFGVBLTWBCJP-UHFFFAOYSA-N 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010413 gardening Methods 0.000 description 1
- 239000000463 material Substances 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%
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The object of the present invention is to provide an Ni-based single crystal super alloy capable of improving strength by preventing precipitation of a TCP phase at high temperatures. This object is achieved by an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-8.0 wt% Ta, 2.9-4.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% Co and 1.0-4.0 wt% Ru in term of its weight ratio, with the remainder consisting of Ni and unavoidable impurities.
Description
Ni-BASED SINGLE CRYSTAL SUPER ALLOY
BACKGROUND OF THE INVENTTON
Field of the Invention The present invention relates to a Ni-based single crystal super alloy, and more particularly, to a technology employed for improving the creep characteristics of Ni-based single crystal super alloy.
Description of the Related Art An example of the typical composition of Ni-based single crystal super alloy developed for use as a material for moving and stationary blades subject to high temperatures such as those in aircraft and gas turbines is shown in Table 1.
Table I
Alloy Elements (wt%) name Ai Ti Ta Nb Mo W Re C Zr Hf Cr Co Ru Ni TM
CMSX-2 6.0 1.0 6.0 - 1.0 8.0 - - - - 8.0 5.0 - Rem TM
CMSX-0 5.6 1.0 6.5 - 0.6 6.0 3.0 - - - 6.5 9.0 - Rem Rene'N6 6.0 - 7.0 0.3 1.0 6.0 5.0 - - 0.2 4.0 13.0 - Rem CMSX-l OK TM 5.7 0.3 8.4 0.1 0.4 5.5 6.3 - - 0.03 2.3 3.3 - Rem 3B 5.7 0.5 8.0 - - 5.5 6.0 0.05 - 0.15 5.0 12.5 3.0 Rem In the above-mentioned Ni-based single crystal super alloys, after perfotming solution treatment at a prescribed temperature, aging treatment is performed to obtain an Ni-based single crystal super alloy. This alloy is referred to as a so-called precipitation hardened alloy, and has a from in which the precipitation phase in the form of a y' phase is precipitated in a matrix in the form of a y phase.
Among the alloys listed in Table 1, CMSX-2 (Canon-Muskegon, US Patent No.
4,582,548) is a first-generation alloy, CMSX-4 (Canon-Muskegon, US Patent No. 4,643,782) is a second-generation alloy, ReneN6 (General Electric, US Patent No. 5,455,120) and CMSX-10K (Canon-Muskegon, US Patent No. 5,366,695) are third-generartion alloys, and 3B
(General Electric, US
Patent No. 5,151,249) is a fourth-generation alloy.
Although the above-mentioned CMSX-2, which is a first-generation alloy, and CMSX-4, which is a second-generation alloy, have comparable creep strength at low temperatures, since a large amount of the eutectic y' phase remains following high-temperature solution treatment; their creep strength is inferior to third-generation alloys.
In addition, although the third-generation alloys of ReneN6 and CMSX-10 are alloys designed to have improved creep strength at I>igh tempeiatures in comparison with second-generabon alloys, mnoe the composite ratio of Re (5 wt% or more) exceeds the amount of Re that dissolves into the matrix (y phase), the excess Re compounds with other elements and as a result, a so-called TCP (topologically close packed) phase precipitates at high temperatures causing the problem of decreased creep shmgth.
In addition, making the lattice constant of the precipitation phase (Y' phase) slightly smaller than the lattice consant of the matrix (y phase) is effective in improving the creep strength ofNi-based single crystal super alloys. However, since the lattice constant of each phase fluctuates greatly fluctuated according to the composite ratios of the composite elements of the alloy, it is difficult to make fine adjustments in the lattice constant and as a result, there is the problem of considerable ditflculty in improving creep stcength.
1n considetation of the above cirauriqances, the object of the present invention is to provide - a Ni-based single crystal super alloy that makes it possible to improve strength by preventing precipitation of the TCP phase at higli temperature.s..
SUMMARY OF THE INVENTION
The following constitution is employed in the present invention in order to achieve the above object.
According to an aspect of the invention there is provided an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-8.0 wt% Ta, 2.9-4.5 wt%
Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% , Co and 1.0-4.0 wt% Ru in terms of its weight ratio, with the remainder consisting of Ni and unavoidable impurities; and wherein when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, a2 <_ 0.999a1.
BACKGROUND OF THE INVENTTON
Field of the Invention The present invention relates to a Ni-based single crystal super alloy, and more particularly, to a technology employed for improving the creep characteristics of Ni-based single crystal super alloy.
Description of the Related Art An example of the typical composition of Ni-based single crystal super alloy developed for use as a material for moving and stationary blades subject to high temperatures such as those in aircraft and gas turbines is shown in Table 1.
Table I
Alloy Elements (wt%) name Ai Ti Ta Nb Mo W Re C Zr Hf Cr Co Ru Ni TM
CMSX-2 6.0 1.0 6.0 - 1.0 8.0 - - - - 8.0 5.0 - Rem TM
CMSX-0 5.6 1.0 6.5 - 0.6 6.0 3.0 - - - 6.5 9.0 - Rem Rene'N6 6.0 - 7.0 0.3 1.0 6.0 5.0 - - 0.2 4.0 13.0 - Rem CMSX-l OK TM 5.7 0.3 8.4 0.1 0.4 5.5 6.3 - - 0.03 2.3 3.3 - Rem 3B 5.7 0.5 8.0 - - 5.5 6.0 0.05 - 0.15 5.0 12.5 3.0 Rem In the above-mentioned Ni-based single crystal super alloys, after perfotming solution treatment at a prescribed temperature, aging treatment is performed to obtain an Ni-based single crystal super alloy. This alloy is referred to as a so-called precipitation hardened alloy, and has a from in which the precipitation phase in the form of a y' phase is precipitated in a matrix in the form of a y phase.
Among the alloys listed in Table 1, CMSX-2 (Canon-Muskegon, US Patent No.
4,582,548) is a first-generation alloy, CMSX-4 (Canon-Muskegon, US Patent No. 4,643,782) is a second-generation alloy, ReneN6 (General Electric, US Patent No. 5,455,120) and CMSX-10K (Canon-Muskegon, US Patent No. 5,366,695) are third-generartion alloys, and 3B
(General Electric, US
Patent No. 5,151,249) is a fourth-generation alloy.
Although the above-mentioned CMSX-2, which is a first-generation alloy, and CMSX-4, which is a second-generation alloy, have comparable creep strength at low temperatures, since a large amount of the eutectic y' phase remains following high-temperature solution treatment; their creep strength is inferior to third-generation alloys.
In addition, although the third-generation alloys of ReneN6 and CMSX-10 are alloys designed to have improved creep strength at I>igh tempeiatures in comparison with second-generabon alloys, mnoe the composite ratio of Re (5 wt% or more) exceeds the amount of Re that dissolves into the matrix (y phase), the excess Re compounds with other elements and as a result, a so-called TCP (topologically close packed) phase precipitates at high temperatures causing the problem of decreased creep shmgth.
In addition, making the lattice constant of the precipitation phase (Y' phase) slightly smaller than the lattice consant of the matrix (y phase) is effective in improving the creep strength ofNi-based single crystal super alloys. However, since the lattice constant of each phase fluctuates greatly fluctuated according to the composite ratios of the composite elements of the alloy, it is difficult to make fine adjustments in the lattice constant and as a result, there is the problem of considerable ditflculty in improving creep stcength.
1n considetation of the above cirauriqances, the object of the present invention is to provide - a Ni-based single crystal super alloy that makes it possible to improve strength by preventing precipitation of the TCP phase at higli temperature.s..
SUMMARY OF THE INVENTION
The following constitution is employed in the present invention in order to achieve the above object.
According to an aspect of the invention there is provided an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-8.0 wt% Ta, 2.9-4.5 wt%
Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% , Co and 1.0-4.0 wt% Ru in terms of its weight ratio, with the remainder consisting of Ni and unavoidable impurities; and wherein when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, a2 <_ 0.999a1.
According to another aspect of the invention there is provided an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 1.0-4.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% Co, and 1.0-4.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities; and wherein when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, a2 _ 0.999a1.
According to a further aspect of the invention there is provided an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 2.9-4.5 wt% Mo; 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 vvt% Cr, 0.1- 9.5 wt% Co and 1.0-4.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities; and wherein when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, a2 < 0.999a1.
According to the above Ni-based single crystal super alloy, precipitation of the TCP phase, which causes a decrease in creep strmgth, during use at high temperahm is inhibited by the addition of Ru In addition, by setting the composite ratios of other composite elements within their optimum ranges, the lattice constant of the matrix (y phase) and the lattice constant of the precipitation phase (y~ phase) can be made to have optimum values.
Consequently, strength at high temperahxes can be enhanced.
In addition, the Ni-based single crystal -super alloy of the present invention is characterized by having a composition constsbng of 5.9 wt% Al, 5.9 wt'/o Ta, 2.9 wl% Mo, 5.9 wt /a W, 4.9 wt%
Re, 0.10 wl% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt%o Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities, in the Ni-based single crystal super alloys previously described.
According to an Ni-based single crystal super ailoy having this composition, the creep enducance temperature at 137 MPa and 1000 houis can be made to be 1356 K(1083 C).
Moreover, the Ni-based single crystal super alloy of the present invention is characterized by a2 S 0.999a1 when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2 in the Ni-based single crystal super alloys previously described.
3a According to this Ni-based single crystal super alloy, the relationship between a 1 and a2 is such that a2 <_ 0.999a1 when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, and since the lattice constant a2 of the precipitation phase is -0.1 % or less of the lattice constant al of the matrix, the precipitation phase that precipitates in the matrix precipitates so as to extend continuously in the direction ^
perpendicular to the direction of the load. As a result, strength at high tempecatums can be enhaticed without dislocation defects moving within the alloy structure under stress.
DETAILED DLSCRIPTTON OF T.E lE INVF.IVT'ION
The following provides a detailed explanation for canying out the present invention.
The Ni-based single crystal super alloy of the present invention is an alloy comprised of Al, Ta, Mo, W, Re, Hf, Cr, Co, Ru, Ni (remainder) and unavoidable impurities. ' The above Ni-based single crystal super alloy is aza, alloy having a composition consisting of 5.0-7.0 wt io Al, 4.0-8.0 wr/o Ta, 2.9-4.5 wt% Mo, 4.0-8.0 wf/o W, 3.0-6.0 wt"/o Re, 0.01-0.5 wt% .
1-it; 2.0-5_0 vvt% Cr, 0.1-15.0 wt io Co and 1.040 wt% Ru, wi:th the remainder consisting ofNi and unavoidable impurxties.
In addition, the above Ni-based singlc crystal super alloy is an alloy having a composition consiSting of 5.0-7.0 ~uVt% Al, 4.0-6.0 wt% Ta,1.0-4.5 Wt% Mo, 4.0-$.0 WC% W, 3.0-6.0 Vvl% Re, 0_01-0. 5 wt% Hf, 2.0-5.0 wt"/o Cr, 0.1-15.0 wt% Co and 1.0-4.0 wt ia Ru with the recmaizzder consisting of Ni and unavoidable imptuities.
Moreover, ilze above Ni-based single crystal supe[ alloy is an alloy having a CArllposltLon consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 2.94.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.5 wt% H:E', 2.0-5.0 wt% Cr, 0.1-15.0 wt% Co and 1.0-4.0 wt% Ru, with the remainde,~r consisting ofNi and unavoidable itnpurities.
All of the above alloys have an austenite phase in the forrn of a y pbase (matrix) and an intcrmediatc rcgular phase in the form of a y' phase (precipitation phase) that is dispersed and preci.pit<ited -n. tlie m.atrix. T'he y' pbase is mainly composed of an in.termetal.lic compound represented by Ni,Al, and the strength of the Ni-based single crystal super alloy at high temperatures is improved by this y' phase.
Cr is mi elem.ent that bas superi.or oxi,d,adtion. resistance and improves the hi,gh-terzaperutuze corrosion resistance o'f the Ni-based single crystal super alloy. The composite ratio of Cr is preferably within the range of 2.0 wt% or more to 5.0 we/o or less, and znore pr.efezably 2.9 wf/o.
1f the composite ratio of Cr is less than 2.0 wt"/o, the desired high-temperature corrosion resistance cannot be secured, tlzereby rna}:ing this undesuable. I=f the composite ratio of Cr excoeds 5.0 wt%, in addition to precipitation of the y' pbase being inhibited, harmful phases such as a a phase or p phase form that cause a decrw.se in strength at high temperatures, thereby making this undesirable.
In addition to improving strength. at high temperrthuts by dissolving into the matrix ir) the form of the -y pbase in the ptesence of W and Ta, Mo also i.nnproves strength at high temperatures due to precipitation hard.ening. The composite ratio of Mo is preferably wit.biz-, the range of 1.0 Nvt% or more to 4.5 wt% or less, m.oze preferably Nvithin the tange of 2.9 wC'/o or rrxore to 4.5 wt %
or less, and most preferably 2.9 wtolo. Iftbe composite ratio of Mo is less than 1.0 wtolo, strength at high temperatures cannot be maintained at the desised level, thereby making this undesirable. = If the composite rafio of Mo exceeds 4_5 wt%, strength at high temperatures decreases, and corrosion resistance at high temperatures also decreases, thereby making this undesirable_ W improves strength ai high temperatures due to the actions of solution hardening and precipitation hardening in the presence of Mo and Ta as previously rnentioned.
The composite ca.tio of W is preferably 'rvi.thin the range of 4.0 wt;'/o or more to 8.0 wt%
or im, and most pzeferably 5.9 wt%. Yf the composite ratio of W is less tb= 4.0 wt%, strength at high temperatuues cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of W exceeds 8_0 wt%, high-temperahue corrosion resistance decreases, thereby making ehis undesirable.
Ta, improves high-temperature strength due to the actions of solution hardenin.g and precipitation hardening in the presence of Mo and W as pateviously mentioned, and also improves high-tempetature, strength as a result of a portion of the Ta undergoing precipitation hardening relative to the y' phase. The composite ratio of Ta is preferably Nvithin the range of 4.0 rxf/o or more to 8.0 wt /o or less, more preferably within the zange of 4-0 wt% or more to 6.0 wto/a or less, and most preferably 5.9 wt /b. If the composite ratio of Ta is less than 4.0 wt%, strength at high temperatures cannot be rnaintained at the desired level, t1iemby mak.ing this undesirable. Zf the composite ratio of Ta exceeds 8.0 wt%, the 6 phase and phase fozm that cause a dscres_ase in strength at high tsmperatures, ttiereby making this undesirable.
Al improves high-tem.peRatuze strength by compounding with Ni to form an intcrrnetallic compound represented by Nij.A.l, wbicl, composes the y' pha.se that finely and uniforrnly disperses and precipitates in the mat~rix, at a r atio of 60-?0% i.n tem-js of volume percent. The composite Iil'.. ' 21 . '. . .
According to a further aspect of the invention there is provided an Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 2.9-4.5 wt% Mo; 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 vvt% Cr, 0.1- 9.5 wt% Co and 1.0-4.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities; and wherein when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, a2 < 0.999a1.
According to the above Ni-based single crystal super alloy, precipitation of the TCP phase, which causes a decrease in creep strmgth, during use at high temperahm is inhibited by the addition of Ru In addition, by setting the composite ratios of other composite elements within their optimum ranges, the lattice constant of the matrix (y phase) and the lattice constant of the precipitation phase (y~ phase) can be made to have optimum values.
Consequently, strength at high temperahxes can be enhanced.
In addition, the Ni-based single crystal -super alloy of the present invention is characterized by having a composition constsbng of 5.9 wt% Al, 5.9 wt'/o Ta, 2.9 wl% Mo, 5.9 wt /a W, 4.9 wt%
Re, 0.10 wl% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt%o Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities, in the Ni-based single crystal super alloys previously described.
According to an Ni-based single crystal super ailoy having this composition, the creep enducance temperature at 137 MPa and 1000 houis can be made to be 1356 K(1083 C).
Moreover, the Ni-based single crystal super alloy of the present invention is characterized by a2 S 0.999a1 when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2 in the Ni-based single crystal super alloys previously described.
3a According to this Ni-based single crystal super alloy, the relationship between a 1 and a2 is such that a2 <_ 0.999a1 when the lattice constant of the matrix is taken to be al and the lattice constant of the precipitation phase is taken to be a2, and since the lattice constant a2 of the precipitation phase is -0.1 % or less of the lattice constant al of the matrix, the precipitation phase that precipitates in the matrix precipitates so as to extend continuously in the direction ^
perpendicular to the direction of the load. As a result, strength at high tempecatums can be enhaticed without dislocation defects moving within the alloy structure under stress.
DETAILED DLSCRIPTTON OF T.E lE INVF.IVT'ION
The following provides a detailed explanation for canying out the present invention.
The Ni-based single crystal super alloy of the present invention is an alloy comprised of Al, Ta, Mo, W, Re, Hf, Cr, Co, Ru, Ni (remainder) and unavoidable impurities. ' The above Ni-based single crystal super alloy is aza, alloy having a composition consisting of 5.0-7.0 wt io Al, 4.0-8.0 wr/o Ta, 2.9-4.5 wt% Mo, 4.0-8.0 wf/o W, 3.0-6.0 wt"/o Re, 0.01-0.5 wt% .
1-it; 2.0-5_0 vvt% Cr, 0.1-15.0 wt io Co and 1.040 wt% Ru, wi:th the remainder consisting ofNi and unavoidable impurxties.
In addition, the above Ni-based singlc crystal super alloy is an alloy having a composition consiSting of 5.0-7.0 ~uVt% Al, 4.0-6.0 wt% Ta,1.0-4.5 Wt% Mo, 4.0-$.0 WC% W, 3.0-6.0 Vvl% Re, 0_01-0. 5 wt% Hf, 2.0-5.0 wt"/o Cr, 0.1-15.0 wt% Co and 1.0-4.0 wt ia Ru with the recmaizzder consisting of Ni and unavoidable imptuities.
Moreover, ilze above Ni-based single crystal supe[ alloy is an alloy having a CArllposltLon consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 2.94.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.5 wt% H:E', 2.0-5.0 wt% Cr, 0.1-15.0 wt% Co and 1.0-4.0 wt% Ru, with the remainde,~r consisting ofNi and unavoidable itnpurities.
All of the above alloys have an austenite phase in the forrn of a y pbase (matrix) and an intcrmediatc rcgular phase in the form of a y' phase (precipitation phase) that is dispersed and preci.pit<ited -n. tlie m.atrix. T'he y' pbase is mainly composed of an in.termetal.lic compound represented by Ni,Al, and the strength of the Ni-based single crystal super alloy at high temperatures is improved by this y' phase.
Cr is mi elem.ent that bas superi.or oxi,d,adtion. resistance and improves the hi,gh-terzaperutuze corrosion resistance o'f the Ni-based single crystal super alloy. The composite ratio of Cr is preferably within the range of 2.0 wt% or more to 5.0 we/o or less, and znore pr.efezably 2.9 wf/o.
1f the composite ratio of Cr is less than 2.0 wt"/o, the desired high-temperature corrosion resistance cannot be secured, tlzereby rna}:ing this undesuable. I=f the composite ratio of Cr excoeds 5.0 wt%, in addition to precipitation of the y' pbase being inhibited, harmful phases such as a a phase or p phase form that cause a decrw.se in strength at high temperatures, thereby making this undesirable.
In addition to improving strength. at high temperrthuts by dissolving into the matrix ir) the form of the -y pbase in the ptesence of W and Ta, Mo also i.nnproves strength at high temperatures due to precipitation hard.ening. The composite ratio of Mo is preferably wit.biz-, the range of 1.0 Nvt% or more to 4.5 wt% or less, m.oze preferably Nvithin the tange of 2.9 wC'/o or rrxore to 4.5 wt %
or less, and most preferably 2.9 wtolo. Iftbe composite ratio of Mo is less than 1.0 wtolo, strength at high temperatures cannot be maintained at the desised level, thereby making this undesirable. = If the composite rafio of Mo exceeds 4_5 wt%, strength at high temperatures decreases, and corrosion resistance at high temperatures also decreases, thereby making this undesirable_ W improves strength ai high temperatures due to the actions of solution hardening and precipitation hardening in the presence of Mo and Ta as previously rnentioned.
The composite ca.tio of W is preferably 'rvi.thin the range of 4.0 wt;'/o or more to 8.0 wt%
or im, and most pzeferably 5.9 wt%. Yf the composite ratio of W is less tb= 4.0 wt%, strength at high temperatuues cannot be maintained at the desired level, thereby making this undesirable. If the composite ratio of W exceeds 8_0 wt%, high-temperahue corrosion resistance decreases, thereby making ehis undesirable.
Ta, improves high-temperature strength due to the actions of solution hardenin.g and precipitation hardening in the presence of Mo and W as pateviously mentioned, and also improves high-tempetature, strength as a result of a portion of the Ta undergoing precipitation hardening relative to the y' phase. The composite ratio of Ta is preferably Nvithin the range of 4.0 rxf/o or more to 8.0 wt /o or less, more preferably within the zange of 4-0 wt% or more to 6.0 wto/a or less, and most preferably 5.9 wt /b. If the composite ratio of Ta is less than 4.0 wt%, strength at high temperatures cannot be rnaintained at the desired level, t1iemby mak.ing this undesirable. Zf the composite ratio of Ta exceeds 8.0 wt%, the 6 phase and phase fozm that cause a dscres_ase in strength at high tsmperatures, ttiereby making this undesirable.
Al improves high-tem.peRatuze strength by compounding with Ni to form an intcrrnetallic compound represented by Nij.A.l, wbicl, composes the y' pha.se that finely and uniforrnly disperses and precipitates in the mat~rix, at a r atio of 60-?0% i.n tem-js of volume percent. The composite Iil'.. ' 21 . '. . .
ratio of Al is preferably within the range of 5.0 wt% or more to 7.0 wt% or less, and most preferably 5.9 wt%. If the composite ratio of Al is less than 5.0 wt%, the precipitated amouht of the y' phase becomes insufficient, and strength at high temperatures cannot be maintained at the desized level, thereby making this undesirable. I#'the composite ratio of A) exceeds 7.0 wta/o, a large amount of a coatrse 7 pbase refered to as the eutectic y' phase is formed, and this eutectic y' phase prevents salution treatment and rnakes i.t impossible to mainta.in s"ngth az high temper-aiiu-es at a high level, thereby making this undesizable.
14f is an element that segregates at the grain boundary and improves high-tempez-ature s#zength by strengthening the grain boundary as a result of being segregated at the grain boundary between the Y phase and y' pliase. The composite ratio of. Hf is pzeferably within the mge of 0.01 wt% or more to 0.50 wl% or less, and most preferably 0.10 wt%. If the con-tpo5ite r'aiio of Hf is less than 0.01 wt%, the precipitated amount oftk-e y' phase becomes insufficient and stte:ngth at high temperatures cannot be xnain,tained at the desired level, thereby rrmaking this utxdesirable. If the composite ratio of Hf exceeds 0.50 vvr/o, local melting is induced whiclt results in the risk af decreased strength at high temperatures, thereby making this uudesizable.
Co improves strength at high temperatures by increasingthe solution limit at high teTn.peratures relative to the rnatri>: such as Al and Ta, and dispersing and pzecipitafizig a fine y' pbase by heat treatrnenk The composite ratio of Co is preferably within the range of 0.1 wt% or more to 15.0 vvt% or less, and most preferably 5.9 wt%. If the composite ratio of Co is less than 0.1 wC%, the precipitated amount of the y' phase becomes insufficient and the strength at high temperatures cannot be maintained, theteby making this undesirable. If the cornposite ratio of Co exceeds 15.0 wt%, the balance with other elennents such as Al, Ta, Mo, W. Hf and Cr is disturbed resulting in the precipitation of harmful phases that cause a decrcase in strength at high tcmperatures, thereby ma.ciztg tbas undesirable.
Re iznpzvves I,igh-temperatttre suengrth due to solutYon strengthening as a result of dissolving in the matrix in the form ofth;e y plwe_ On t'he other hand, ifa large amount of Re is added, the harmfiil TCP phase precipita.tes at high temperatures, resulting in the rislc of decreased strength at high tempetatures. Thus, tka.e composite ratio of Re is preferably within the range of 3.0 wt /a or more to 6.0 xvt% or less, and most preferably 4.9 wt%. If the composite ratio of Re is less than 3_0 wt%, solutiozz strengthening af th.e y phase becomes insufficierxt and srrength at high tempetatuies cannot be maintained at the desized level, thereby making this undesirable. If the composite ratio of Re exceeds 6.0 wt%, the TCP phase precipitates at high teznpe.razures and strength at high t.ecnperaiures cannot be maintained at a high level, thereby making this undesirable.
Ru improves high-temperature strength by izihibiting precipitation of the TCP
pb.ase. The composite ratio of Ru is preferably witbin the range of 1.0 wt% or more to 4.0 wt% or less, and most preferably 2.0 wt%. If the composite ratio of Ru is less than 1.0 wt%, thc TCP pbase pr.ecipitates at high temperawues and strength at hi.gh temperatun.as camot be maintained at a high level, thereby rnaking this undesirable. If the composite ririo of Ru exceeds 4.0 wi%, the cost increases which is also undesirable.
Particularly in the pzeseant iztvent'ion, by adjusting the composite ratios of Al, Ta, Mo, W, Hf, Cr, Co and Ni to the opt-imuria: mt%os, together with improving s'h=ength at high temperahires by setting the lattice constant of the y phase and the lattzce constant of the -y' pha.se vrithin their optimum ranges, and precipitation of, the TCP phase can be inhibited by adding Ru In addition, in usage cmvironments at a high temperature from 1273 K(1000 C) to 1373K
(1100 C), wlaen the laWce constant of the crystals that compose the matrix in the form of the y phase is taken to be al, and the lattice constant of the crystal.s that coznpose the precipitation phase in the form of the y' Phase is taken to be a2, then tlxe relationship between al and a2 is pieferably such that a2 <_ 0.999a1. Namely, laitice constant a2 of the crystals of the precipitation phase is preferabiy -0.1 /a or less l<.~1tice consiant al. of the crystals of the matrix.
In addition, lattice constant a2 of the crystals of the precipitation phase should be -0.5 .0 or more of lattice constant al of the crystals of the matrix. In the case both, of the lattice constants are in the above relationship, since tb.e precipitation phase precipitates so as to extend continuously in the direction perpendicular to the direction of the load when the precipitation phase precipitates in the mabrix due to heat treatment, creep strength can be enhanc.ed without movement of dislocation defects in the alloy stzucture in the presence of stress.
In order to inake the relationship between lattite constan.t 31 and lattice constant a2 such that a2 ~ 0.999a1, the composition of tlie composite elements that compose die Ni-based sizzgi.e crystal super alloy is sui.tably adjusted.
il a ~
According to the above Ni-based super c[ystal super alloy, prc.cipitation ofthe TCP phase, which causes decreased creep strength, during use at h.i,gh temperatures is inhibited by addition of Ru. In addition, by setting the composite ratios of other composite elements to their optimum ranges, the lattice constant of the matrix (y phase) and the lattice constant of the precipitation phase (: e' phase) can. be made to have optiznum values. As a result, creep strength at high terrxpetatures can be improved.
Embodiments The effect oftlie present invention is showa using following embodiments.
Melts of various Ni-based single crystal super alloys were prepared using a vacuum melting fvmace, and alloy ingots were cast using the alloy melts. The composite rafao of the alloy ingot of the present embodiinent (TMS-138) is shown in Table 2.
Table 2 S~mp1e Elements wt%
(alloy name) Al Ti Ta Nb Mo W Re C Zt Hf Cr Co Ru Ni Ernbodi- 5.9 5.9 2.9 5.9 4.9 0.1 2.9 5.9 2.0 R
ment (TMS-138) Nexc, solution tm.atrn.ent and aging treatment were performed on the alloy, ingots followed by observazion of the state of the alloy strocfiire with a scanning electcon mi.croscope (SEM).
Solution treatment consisted of holding for 1 hour at 1573K (1300 C) followed by heating to 1613K (1340 C) and holding for 5 hours. In addiiion, aging treatment consisted of consccut ively perfonning primary aging treatment consisling of holding for 4 hours at I 150 C and secondary :igiDg treatment consisting ofholding.f.ox20 houss at 870 C.
As a result, a TCP phase wa_s unable to be confirrned in the shructure.
Ne,rct, a creep test was Performed on a sample of the present embodiment (TMS-138) that underwent solution treatment and a{,~ng treatment. The creep test consisted of ineasuring the titne until the sample demonstrated creep rupture as the sample life under each of the temperazuze and stress coDditioDs shown in Table 3.
IL:,. a:. .. .
Table 3 C test conditior~ ture life Sample (alloy 1173K 1273.TC 1373K 1423K 1423K
narne) (900 C) (1000 C) (1100 C) (1150 C) (1150 C) 392 MPa 245 MPa 137 MPa 98 M a 137 Mf'a Eznbodiment 986.88 380.50 412.30 343.25 81.47 (TMS-13S) As is clear from Table 3, the sample of the present errAbodiment Was determined to have high strengtl, even under high tem.peiature conditions of 1273K (1000 C).
In addition, the creep ruptute characteristics (withstand temperatune) were eompared for the alloys of the prior art shown in Table 1(Compatative Examples 1 through 5) and the sample of the present embodirnetat sho'wn in Table 2 (TMS-138). Creep rupture charactecislics were determined either as a result of rneasu.rin.g the temperature un,til the sample ruptured tn-miez conditions of applying shress of 137 MPa for 1000 hours, or converting the ruptute temperature of the sample under those cpnditiom.
Table 4 Sarr-.ple (alloy name) Withstand tem ture C
Corrxpazabive Example 1(CMSX-2) 1289K (1016 C
Comparative Example 2 (CMSX-4) 1306K 1033 C
Comparative ~',~carz-.ple 3 (ReneN6) 1320K (1047 CComparative Example 4(CMSX-X0K) 1345K 1072 C) Compazative Example 5(3B) 1353K 1080 C
Embodiment (TMS-138) 1356K 1083 C
(Cozaverted to 137 NIPa,1000 hours) As is clear from Table 4, the sample of the present embodiment was determined to have a high withstand temperature (1356K (1083 C)) equal to or greater tlaan ComparafivE Examples 1 throtigh 5.
"ihus, this a.lloy has a higher heat resistance temperature than Ni-based single crystal super alloys of the prior art, and was detenr-ined to have high strength even at high temperatures.
1 urthermore, the fatigue stnngth were compared for the alloys of the Compara.tive Example 2 shown in Table 1(CMSX-4) and the sample of the presezat enrabodiment shown in Table 2(TMS-138). ln this case, the high cycle fazigue strength (HCF) and tlie low cycle fatigue strength (LCF) a', . .~, . . . .
were measured as the fatigue strength. For measuring the high cycle fatigue strength, the max stress at hi-a teznpeiabare of 1373K (1100 C) weze measured by controlling a load, and the number of fatigue fiacture cycle (Nfl wem det.emzined as 10`' and 161. For measuring the low cycle fatigue stze.zi,gtlz, the alternative peseudostress at higiteanperature of 1073K (800 C) were measured by controlling the distortion, and tkte number of fatigue fracture cycle (Nf) were detetrnined as 10' and I Oa.
Table 5 HCF(1373K) LCF(1073K) Max Stress (Mpa) A]t. Pseudostress (Mpa) Nf=10l Nf=10' Nf-103 Nf~-10 As is clear fram Table 5, the sample of the present embodiment was deteimined to have a fatigue strength greater than Comparative Example 2.
Therefore, the alloy of, th.e pre.sent invention (TMS-13s) was determined to have a hisrh fatigue strength in addition to the Creep stzmgth at high temperah= compared to the conventional Ni-based single crystal super alloy.
14f is an element that segregates at the grain boundary and improves high-tempez-ature s#zength by strengthening the grain boundary as a result of being segregated at the grain boundary between the Y phase and y' pliase. The composite ratio of. Hf is pzeferably within the mge of 0.01 wt% or more to 0.50 wl% or less, and most preferably 0.10 wt%. If the con-tpo5ite r'aiio of Hf is less than 0.01 wt%, the precipitated amount oftk-e y' phase becomes insufficient and stte:ngth at high temperatures cannot be xnain,tained at the desired level, thereby rrmaking this utxdesirable. If the composite ratio of Hf exceeds 0.50 vvr/o, local melting is induced whiclt results in the risk af decreased strength at high temperatures, thereby making this uudesizable.
Co improves strength at high temperatures by increasingthe solution limit at high teTn.peratures relative to the rnatri>: such as Al and Ta, and dispersing and pzecipitafizig a fine y' pbase by heat treatrnenk The composite ratio of Co is preferably within the range of 0.1 wt% or more to 15.0 vvt% or less, and most preferably 5.9 wt%. If the composite ratio of Co is less than 0.1 wC%, the precipitated amount of the y' phase becomes insufficient and the strength at high temperatures cannot be maintained, theteby making this undesirable. If the cornposite ratio of Co exceeds 15.0 wt%, the balance with other elennents such as Al, Ta, Mo, W. Hf and Cr is disturbed resulting in the precipitation of harmful phases that cause a decrcase in strength at high tcmperatures, thereby ma.ciztg tbas undesirable.
Re iznpzvves I,igh-temperatttre suengrth due to solutYon strengthening as a result of dissolving in the matrix in the form ofth;e y plwe_ On t'he other hand, ifa large amount of Re is added, the harmfiil TCP phase precipita.tes at high temperatures, resulting in the rislc of decreased strength at high tempetatures. Thus, tka.e composite ratio of Re is preferably within the range of 3.0 wt /a or more to 6.0 xvt% or less, and most preferably 4.9 wt%. If the composite ratio of Re is less than 3_0 wt%, solutiozz strengthening af th.e y phase becomes insufficierxt and srrength at high tempetatuies cannot be maintained at the desized level, thereby making this undesirable. If the composite ratio of Re exceeds 6.0 wt%, the TCP phase precipitates at high teznpe.razures and strength at high t.ecnperaiures cannot be maintained at a high level, thereby making this undesirable.
Ru improves high-temperature strength by izihibiting precipitation of the TCP
pb.ase. The composite ratio of Ru is preferably witbin the range of 1.0 wt% or more to 4.0 wt% or less, and most preferably 2.0 wt%. If the composite ratio of Ru is less than 1.0 wt%, thc TCP pbase pr.ecipitates at high temperawues and strength at hi.gh temperatun.as camot be maintained at a high level, thereby rnaking this undesirable. If the composite ririo of Ru exceeds 4.0 wi%, the cost increases which is also undesirable.
Particularly in the pzeseant iztvent'ion, by adjusting the composite ratios of Al, Ta, Mo, W, Hf, Cr, Co and Ni to the opt-imuria: mt%os, together with improving s'h=ength at high temperahires by setting the lattice constant of the y phase and the lattzce constant of the -y' pha.se vrithin their optimum ranges, and precipitation of, the TCP phase can be inhibited by adding Ru In addition, in usage cmvironments at a high temperature from 1273 K(1000 C) to 1373K
(1100 C), wlaen the laWce constant of the crystals that compose the matrix in the form of the y phase is taken to be al, and the lattice constant of the crystal.s that coznpose the precipitation phase in the form of the y' Phase is taken to be a2, then tlxe relationship between al and a2 is pieferably such that a2 <_ 0.999a1. Namely, laitice constant a2 of the crystals of the precipitation phase is preferabiy -0.1 /a or less l<.~1tice consiant al. of the crystals of the matrix.
In addition, lattice constant a2 of the crystals of the precipitation phase should be -0.5 .0 or more of lattice constant al of the crystals of the matrix. In the case both, of the lattice constants are in the above relationship, since tb.e precipitation phase precipitates so as to extend continuously in the direction perpendicular to the direction of the load when the precipitation phase precipitates in the mabrix due to heat treatment, creep strength can be enhanc.ed without movement of dislocation defects in the alloy stzucture in the presence of stress.
In order to inake the relationship between lattite constan.t 31 and lattice constant a2 such that a2 ~ 0.999a1, the composition of tlie composite elements that compose die Ni-based sizzgi.e crystal super alloy is sui.tably adjusted.
il a ~
According to the above Ni-based super c[ystal super alloy, prc.cipitation ofthe TCP phase, which causes decreased creep strength, during use at h.i,gh temperatures is inhibited by addition of Ru. In addition, by setting the composite ratios of other composite elements to their optimum ranges, the lattice constant of the matrix (y phase) and the lattice constant of the precipitation phase (: e' phase) can. be made to have optiznum values. As a result, creep strength at high terrxpetatures can be improved.
Embodiments The effect oftlie present invention is showa using following embodiments.
Melts of various Ni-based single crystal super alloys were prepared using a vacuum melting fvmace, and alloy ingots were cast using the alloy melts. The composite rafao of the alloy ingot of the present embodiinent (TMS-138) is shown in Table 2.
Table 2 S~mp1e Elements wt%
(alloy name) Al Ti Ta Nb Mo W Re C Zt Hf Cr Co Ru Ni Ernbodi- 5.9 5.9 2.9 5.9 4.9 0.1 2.9 5.9 2.0 R
ment (TMS-138) Nexc, solution tm.atrn.ent and aging treatment were performed on the alloy, ingots followed by observazion of the state of the alloy strocfiire with a scanning electcon mi.croscope (SEM).
Solution treatment consisted of holding for 1 hour at 1573K (1300 C) followed by heating to 1613K (1340 C) and holding for 5 hours. In addiiion, aging treatment consisted of consccut ively perfonning primary aging treatment consisling of holding for 4 hours at I 150 C and secondary :igiDg treatment consisting ofholding.f.ox20 houss at 870 C.
As a result, a TCP phase wa_s unable to be confirrned in the shructure.
Ne,rct, a creep test was Performed on a sample of the present embodiment (TMS-138) that underwent solution treatment and a{,~ng treatment. The creep test consisted of ineasuring the titne until the sample demonstrated creep rupture as the sample life under each of the temperazuze and stress coDditioDs shown in Table 3.
IL:,. a:. .. .
Table 3 C test conditior~ ture life Sample (alloy 1173K 1273.TC 1373K 1423K 1423K
narne) (900 C) (1000 C) (1100 C) (1150 C) (1150 C) 392 MPa 245 MPa 137 MPa 98 M a 137 Mf'a Eznbodiment 986.88 380.50 412.30 343.25 81.47 (TMS-13S) As is clear from Table 3, the sample of the present errAbodiment Was determined to have high strengtl, even under high tem.peiature conditions of 1273K (1000 C).
In addition, the creep ruptute characteristics (withstand temperatune) were eompared for the alloys of the prior art shown in Table 1(Compatative Examples 1 through 5) and the sample of the present embodirnetat sho'wn in Table 2 (TMS-138). Creep rupture charactecislics were determined either as a result of rneasu.rin.g the temperature un,til the sample ruptured tn-miez conditions of applying shress of 137 MPa for 1000 hours, or converting the ruptute temperature of the sample under those cpnditiom.
Table 4 Sarr-.ple (alloy name) Withstand tem ture C
Corrxpazabive Example 1(CMSX-2) 1289K (1016 C
Comparative Example 2 (CMSX-4) 1306K 1033 C
Comparative ~',~carz-.ple 3 (ReneN6) 1320K (1047 CComparative Example 4(CMSX-X0K) 1345K 1072 C) Compazative Example 5(3B) 1353K 1080 C
Embodiment (TMS-138) 1356K 1083 C
(Cozaverted to 137 NIPa,1000 hours) As is clear from Table 4, the sample of the present embodiment was determined to have a high withstand temperature (1356K (1083 C)) equal to or greater tlaan ComparafivE Examples 1 throtigh 5.
"ihus, this a.lloy has a higher heat resistance temperature than Ni-based single crystal super alloys of the prior art, and was detenr-ined to have high strength even at high temperatures.
1 urthermore, the fatigue stnngth were compared for the alloys of the Compara.tive Example 2 shown in Table 1(CMSX-4) and the sample of the presezat enrabodiment shown in Table 2(TMS-138). ln this case, the high cycle fazigue strength (HCF) and tlie low cycle fatigue strength (LCF) a', . .~, . . . .
were measured as the fatigue strength. For measuring the high cycle fatigue strength, the max stress at hi-a teznpeiabare of 1373K (1100 C) weze measured by controlling a load, and the number of fatigue fiacture cycle (Nfl wem det.emzined as 10`' and 161. For measuring the low cycle fatigue stze.zi,gtlz, the alternative peseudostress at higiteanperature of 1073K (800 C) were measured by controlling the distortion, and tkte number of fatigue fracture cycle (Nf) were detetrnined as 10' and I Oa.
Table 5 HCF(1373K) LCF(1073K) Max Stress (Mpa) A]t. Pseudostress (Mpa) Nf=10l Nf=10' Nf-103 Nf~-10 As is clear fram Table 5, the sample of the present embodiment was deteimined to have a fatigue strength greater than Comparative Example 2.
Therefore, the alloy of, th.e pre.sent invention (TMS-13s) was determined to have a hisrh fatigue strength in addition to the Creep stzmgth at high temperah= compared to the conventional Ni-based single crystal super alloy.
Claims (6)
1. An Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-8.0 wt% Ta, 2.9-4.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% Co and 1.0-4.0 wt% Ru in terms of its weight ratio, with the remainder consisting of Ni and unavoidable impurities;
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
2. An Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 1.0-4.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1-9.5 wt% Co, and 1.0-4.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities;
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
3. An Ni-based single crystal super alloy having a composition consisting of 5.0-7.0 wt% Al, 4.0-6.0 wt% Ta, 2.9-4.5 wt% Mo, 4.0-8.0 wt% W, 3.0-6.0 wt% Re, 0.01-0.50 wt% Hf, 2.0-5.0 wt% Cr, 0.1- 9.5 wt% Co and 1.0-4.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities;
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
and wherein when the lattice constant of the matrix is taken to be a1 and the lattice constant of the precipitation phase is taken to be a2, a2 <= 0.999a1.
4. The Ni-based single crystal super alloy according to claim 1 that has a composition consisting of 5.9 wt% Al, 5.9 wt% Ta, 2.9 wt% Mo, 5.9 wt% W, 4.9 wt%
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
5. The Ni-based single crystal super alloy according to claim 2 that has a composition consisting of 5.9 wt% Al, 5.9 wt% Ta, 2.9 wt% Mo, 5.9 wt% W, 4.9 wt%
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
6. The Ni-based single crystal super alloy according to claim 3 that has a composition consisting of 5.9 wt% Al, 5.9 wt% Ta, 2.9 wt% Mo, 5.9 wt% W, 4.9 wt%
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
Re, 0.10 wt% Hf, 2.9 wt% Cr, 5.9 wt% Co and 2.0 wt% Ru in terms of weight ratio, with the remainder consisting of Ni and unavoidable impurities.
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| JP2001-161919 | 2001-05-30 | ||
| JP2001161919 | 2001-05-30 | ||
| JP2002143572A JP3840555B2 (en) | 2001-05-30 | 2002-05-17 | Ni-based single crystal superalloy |
| JP2002-143572 | 2002-05-17 |
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| US (1) | US20030075247A1 (en) |
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| US6966956B2 (en) * | 2001-05-30 | 2005-11-22 | National Institute For Materials Science | Ni-based single crystal super alloy |
| US8968643B2 (en) * | 2002-12-06 | 2015-03-03 | National Institute For Materials Science | Ni-based single crystal super alloy |
| US7273662B2 (en) | 2003-05-16 | 2007-09-25 | Iowa State University Research Foundation, Inc. | High-temperature coatings with Pt metal modified γ-Ni+γ′-Ni3Al alloy compositions |
| JP3944582B2 (en) * | 2003-09-22 | 2007-07-11 | 独立行政法人物質・材料研究機構 | Ni-base superalloy |
| GB0412584D0 (en) * | 2004-06-05 | 2004-07-07 | Rolls Royce Plc | Composition of matter |
| WO2006104138A1 (en) * | 2005-03-28 | 2006-10-05 | National Institute For Materials Science | Heat-resistant member |
| JP5344453B2 (en) * | 2005-09-27 | 2013-11-20 | 独立行政法人物質・材料研究機構 | Ni-base superalloy with excellent oxidation resistance |
| US8123872B2 (en) * | 2006-02-22 | 2012-02-28 | General Electric Company | Carburization process for stabilizing nickel-based superalloys |
| JP4773303B2 (en) * | 2006-08-22 | 2011-09-14 | 株式会社日立製作所 | Nickel-based single crystal superalloy excellent in strength, corrosion resistance, and oxidation resistance and method for producing the same |
| US8771440B2 (en) | 2006-09-13 | 2014-07-08 | National Institute For Materials Science | Ni-based single crystal superalloy |
| EP2128284B1 (en) * | 2007-03-12 | 2015-08-19 | IHI Corporation | Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE VANE USING THE SAME |
| JP5467306B2 (en) | 2008-06-26 | 2014-04-09 | 独立行政法人物質・材料研究機構 | Ni-based single crystal superalloy and alloy member based thereon |
| JP5467307B2 (en) | 2008-06-26 | 2014-04-09 | 独立行政法人物質・材料研究機構 | Ni-based single crystal superalloy and alloy member obtained therefrom |
| US8821654B2 (en) | 2008-07-15 | 2014-09-02 | Iowa State University Research Foundation, Inc. | Pt metal modified γ-Ni+γ′-Ni3Al alloy compositions for high temperature degradation resistant structural alloys |
| US20100135846A1 (en) | 2008-12-01 | 2010-06-03 | United Technologies Corporation | Lower cost high strength single crystal superalloys with reduced re and ru content |
| US20160214350A1 (en) | 2012-08-20 | 2016-07-28 | Pratt & Whitney Canada Corp. | Oxidation-Resistant Coated Superalloy |
| US8858876B2 (en) | 2012-10-31 | 2014-10-14 | General Electric Company | Nickel-based superalloy and articles |
| DE102016203724A1 (en) * | 2016-03-08 | 2017-09-14 | Siemens Aktiengesellschaft | SX-nickel alloy with improved TMF properties, raw material and component |
| TWI663263B (en) * | 2016-11-25 | 2019-06-21 | 國家中山科學研究院 | High creep-resistant equiaxed grain nickel-based superalloy |
| CN112522543A (en) * | 2020-11-18 | 2021-03-19 | 贵州工程应用技术学院 | High-concentration Re/Ru high-temperature-bearing-capacity high-creep-resistance nickel-based single crystal superalloy |
| US12534779B2 (en) | 2022-05-05 | 2026-01-27 | General Electric Company | Nickel-based superalloys and articles |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4719080A (en) * | 1985-06-10 | 1988-01-12 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
| CA1315572C (en) * | 1986-05-13 | 1993-04-06 | Xuan Nguyen-Dinh | Phase stable single crystal materials |
| US5151249A (en) * | 1989-12-29 | 1992-09-29 | General Electric Company | Nickel-based single crystal superalloy and method of making |
| US5482789A (en) * | 1994-01-03 | 1996-01-09 | General Electric Company | Nickel base superalloy and article |
| US6007645A (en) * | 1996-12-11 | 1999-12-28 | United Technologies Corporation | Advanced high strength, highly oxidation resistant single crystal superalloy compositions having low chromium content |
| JPH11256258A (en) * | 1998-03-13 | 1999-09-21 | Toshiba Corp | Ni-based single crystal superalloy and gas turbine parts |
| JPH11310839A (en) * | 1998-04-28 | 1999-11-09 | Hitachi Ltd | High-strength Ni-base superalloy directionally solidified casting |
| FR2780983B1 (en) * | 1998-07-09 | 2000-08-04 | Snecma | SINGLE-CRYSTAL NICKEL-BASED SUPERALLOY WITH HIGHER TEMPERATURE RESISTANCE |
| JP4028122B2 (en) * | 1999-02-25 | 2007-12-26 | 独立行政法人物質・材料研究機構 | Ni-base superalloy, manufacturing method thereof, and gas turbine component |
| US6444057B1 (en) * | 1999-05-26 | 2002-09-03 | General Electric Company | Compositions and single-crystal articles of hafnium-modified and/or zirconium-modified nickel-base superalloys |
| US6673308B2 (en) * | 2000-08-30 | 2004-01-06 | Kabushiki Kaisha Toshiba | Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof |
-
2002
- 2002-05-17 JP JP2002143572A patent/JP3840555B2/en not_active Expired - Lifetime
- 2002-05-29 CA CA002387828A patent/CA2387828C/en not_active Expired - Lifetime
- 2002-05-29 EP EP02253782A patent/EP1262569B1/en not_active Expired - Lifetime
- 2002-05-29 DE DE60203562T patent/DE60203562T2/en not_active Expired - Lifetime
- 2002-05-30 US US10/159,202 patent/US20030075247A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| CA2387828A1 (en) | 2002-11-30 |
| EP1262569A1 (en) | 2002-12-04 |
| EP1262569B1 (en) | 2005-04-06 |
| DE60203562D1 (en) | 2005-05-12 |
| DE60203562T2 (en) | 2006-02-09 |
| JP3840555B2 (en) | 2006-11-01 |
| US20030075247A1 (en) | 2003-04-24 |
| EP1262569A8 (en) | 2003-05-21 |
| JP2003049231A (en) | 2003-02-21 |
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