WO2024120733A1 - Nickel based superalloy, raw material, component and method - Google Patents
Nickel based superalloy, raw material, component and method Download PDFInfo
- Publication number
- WO2024120733A1 WO2024120733A1 PCT/EP2023/081291 EP2023081291W WO2024120733A1 WO 2024120733 A1 WO2024120733 A1 WO 2024120733A1 EP 2023081291 W EP2023081291 W EP 2023081291W WO 2024120733 A1 WO2024120733 A1 WO 2024120733A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- molybdenum
- nickel
- based superalloy
- zirconium
- boron
- Prior art date
Links
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 72
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 31
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims description 7
- 239000002994 raw material Substances 0.000 title claims description 7
- 239000010936 titanium Substances 0.000 claims abstract description 32
- 239000011651 chromium Substances 0.000 claims abstract description 31
- 239000010955 niobium Substances 0.000 claims abstract description 29
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 21
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 20
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 20
- 239000011733 molybdenum Substances 0.000 claims abstract description 20
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 18
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 18
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 16
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052796 boron Inorganic materials 0.000 claims abstract description 16
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 16
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 15
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 15
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 15
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 15
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 14
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims abstract description 13
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000010937 tungsten Substances 0.000 claims abstract description 13
- 239000010941 cobalt Substances 0.000 claims abstract description 12
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 12
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 12
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 8
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 8
- 239000010703 silicon Substances 0.000 claims abstract description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 15
- 239000000956 alloy Substances 0.000 claims description 15
- 229910052715 tantalum Inorganic materials 0.000 claims description 8
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims description 7
- 239000002245 particle Substances 0.000 claims description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 5
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 5
- 229910052717 sulfur Inorganic materials 0.000 claims description 5
- 239000011593 sulfur Substances 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 2
- 239000000843 powder Substances 0.000 claims 2
- 239000011230 binding agent Substances 0.000 claims 1
- 239000000919 ceramic Substances 0.000 claims 1
- 239000013078 crystal Substances 0.000 claims 1
- 238000005728 strengthening Methods 0.000 description 9
- 238000005260 corrosion Methods 0.000 description 8
- 230000007797 corrosion Effects 0.000 description 8
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical compound O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 description 8
- 230000003647 oxidation Effects 0.000 description 8
- 238000007254 oxidation reaction Methods 0.000 description 8
- 230000015572 biosynthetic process Effects 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 5
- 238000005266 casting Methods 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000001627 detrimental effect Effects 0.000 description 3
- 238000001556 precipitation Methods 0.000 description 3
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- CNJLMVZFWLNOEP-UHFFFAOYSA-N 4,7,7-trimethylbicyclo[4.1.0]heptan-5-one Chemical compound O=C1C(C)CCC2C(C)(C)C12 CNJLMVZFWLNOEP-UHFFFAOYSA-N 0.000 description 1
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 1
- 230000001464 adherent effect Effects 0.000 description 1
- 239000002551 biofuel Substances 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 239000003518 caustics Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000000356 contaminant Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 230000004941 influx Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 230000003389 potentiating effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 229910052702 rhenium Inorganic materials 0.000 description 1
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 1
- 235000002639 sodium chloride Nutrition 0.000 description 1
- 239000011780 sodium chloride Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- 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%
Definitions
- the invention relates to a Nickel based superalloy, a raw material, a component and method to cast it.
- the general rule of thumb for good hot corrosion resistance is to have a nominal composition with at least about 12 wt% Chromium (Cr), at most about 2 wt% Molybdenum (Mo) and no Vanadium (V).
- Molybdenum (Mo) and no Vanadium (V) can react with and accelerate the attack from corrosive agents.
- Oxidation is normally not a major issue in the later stage blades since the metal temperatures are moderate by the standards of gas turbine hot stage components. Later stage blades typically operate in the 600 to 800°C range. It is then sufficient to have the ability to form a continuous and adherent Cr 2 O 3 layer.
- IN792 with a nominal composition, in wt%, of Ni-8.5Co-12.5Cr-1 ,8Mo-4W-3.4AI-4Ti-4Ta- 0.08C-0.02Zr-0.015B has a good combination of creep and hot corrosion resistance, a gamma prime particle content of about 50mol%, and is extensively used for later stage blades and other turbine components.
- Molybdenum (Mo) and no Vanadium (V) are used to strengthen the gamma matrix while Titanium (Ti) and Tantalum (Ta) are used to strengthen the gamma prime particles.
- a blade alloy having creep and corrosion resistance on the IN792 level and a reduced density would enable higher performance. It is accordingly the aim of the invention to provide an alloy with IN792 level creep and corrosion resistance and a reduced density. Relative to IN792, the levels of the strengthening elements are reduced, which is detrimental for the creep strength but will reduce the density. Al is increased which will further reduce the density and increase the gamma prime particle content which is beneficial for the creep strength. Ta is replaced by Nb which will further reduce the density. Si is included at a low measured level while nominally set to zero in most specifications for IN792.
- Hafnium (Hf) up to about 2.0 wt% is included by some casting vendors to improve the casting yield. Whether Hafnium (Hf) is an advantage, and if so at what level, depends on the component geometry, and, the specific casting methodology, mold materials and rigs used by the vendor. When Hafnium (Hf) is added, the levels of one or more of the other alloy elements are reduced somewhat to ensure that this does not cause an increased propensity for precipitation of unwanted phases such as Laves and Sigma. Tantalum (Ta) is often added for oxidation resistance as well as strength in alloys made for hot stage blades while Niobium (Nb) provides the same strengthening effect per at% but does not boost the oxidation resistance. Hence a replacement of Tantalum (Ta) by Niobium (Nb) is beneficial in later stage blades where a reduced density at the cost of some oxidation resistance is a reasonable bargain.
- the inventive Nickel based alloy has following composition: comprising (in wt%) Nickel based superalloy, comprising (in wt%) 3,0% - 9,0% Cobalt (Co), especially 4,0% - 9,0% Cobalt (Co), 11 ,0% - 14,0% Chromium (Cr), especially 11 ,5% - 13,5% Chromium (Cr), very especially 12,0% - 13,0% Chromium (Cr), 1 ,0% - 3,5% Molybdenum (Mo), especially 1 ,5% - 3,5% Molybdenum (Mo), 4,0% - 6,0% Aluminum (Al), especially 4,5% - 6,0% Aluminum (Al), very especially 5,0% Aluminum (Al), 2,7% - 4,0% Titanium (Ti), especially 3,0% - 4,0% Titanium (Ti), very especially 3,5% Titanium (Ti), 0,03% - 0,15% Carbon (C), especially 0,08% - 0,15% Carbon (C), 0,005% - 0,030% Boron (B), especially 0,008% - 0,020%
- Niobium Niobium
- Nb Niobium
- Nion Nion
- Si Silicon
- up to to 2,0% Hafnium (Hf) especially 0,5% to 1.5% Hafnium (Hf)
- up to 5 wt% Iron Fe
- up to 3,0wt% Iron Fe
- Ni-5Co-12.5Cr-2Mo-2W-5AI-3.5Ti-1.5Nb- 0.12C-0.015B-0.01Zr has a density in the 7.8 to 8kg/dm3 range and a gamma prime particle content (at 850C) of 67mol%
- the alloy is free of Rhenium (Re) and Tantalum (Ta) , two elements which are commonly used in modern Nickel base superalloys, but which unfortunately significantly increase their densities.
- Boron (B), Carbon (C) and Zirconium (Zr) are used for grain boundary strengthening and are included at normal values for high strength Nickel base gamma prime strengthened superalloys.
- the alloy should furthermore preferably be cast with a clean process such that e.g., the resulting sulfur content is below 5 ppm.
- Sulfur (S) can severely reduce the protective capability and adherence of the Cr 2 O 3 layer, hence a strict cap on this element is prudent despite the moderate service temperatures.
- Ni-5Co-12.5Cr-1.8Mo-2.2W-5AI-3.5Ti- 1.5Nb-0.1C-0.015B-0.01Zr-0.01Si has a predicted density of about 7.9 kg/dm 3 using the extended Caron formula below, and, a predicted gamma prime particle content, at 850°C, of 67mol% based on ThermoCalc with TTNi8 as data base.
- Relative to IN792 the levels of the gamma matrix elements Co and W are reduced.
- the reduction in gamma matrix strength is however small since the amount of gamma matrix to be strengthened by Mo and W is reduced relative to IN792.
- Niobium (Nb) corresponds to about 3 wt% Tantalum (Ta) on an at% basis.
- Ti gamma prime strengthening elements
- Tantalum (Ta) and Niobium (Nb) is reduced relative to the very high level of gamma prime strengthening elements used in IN792.
- Al is increased to enable a higher gamma prime content.
- Hafnium (Hf) can be added as required w.r.t. the production process requirements, as done today for IN792, in which case one or more of the alloy elements need to be adjusted by those skilled in the art such that e.g., the propensity for precipitation of unwanted phases does not increase.
- Tungsten (W) in this range provides a useful strengthening effect and low enough to avoid excessive formation of undesired phases.
- Aluminum (Al) is included at between about 4wt% and 6 wt%. In this range it high enough to reduce the risk that the joint should be a weak link w.r.t. oxidation and corrosion, high enough to assist in the formation of gamma prime particles, and low enough to avoid excessive formation of undesired phases.
- Tantalum (Ta) is preferably not included.
- Molybdenum (Mo) is a potent gamma matrix strengthening element with a low diffusivity.
- Carbon (C) is an element with a high diffusivity and can at a first glance be assumed to equilibrate easily with surrounding parts. In-house experience does however sometimes show essentially carbide free joints (which is not useful) when Carbon (C) free BFM’s have been used. Our interpretation is that the carbon close to the joint is at least temporarily bound in carbo-borides as Boron (B) from the joint diffuses from the joint. There should be a lower limit on Carbon (C) to avoid completely Carbon (C) free joints, but too high levels of Carbon (C) implies a risk for formation of embrittling carbide films and elongated carbides. Carbon (C) is included at between 0.03wt% and 0.15 wt%.
- Zirconium is an element which provides grain boundary strengthening and acts as a sulfur gatherer at low measured levels. It needs to be capped at a low level since it tends to segregate which could lead to incipient melting since it is a melt depressant. It is included at between 0.005wt% and 0.03 wt%.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to Nickel based superalloy comprising (in wt%) 4.5% - 5.5% Cobalt (Co) 12% - 13% Chromium (Cr) 1.6% - 2% Molybdenum (Mo) 1.7% - 2.5% Tungsten (W) 10 4.6% - 5.2% Aluminum (Al) 3.1% - 3.7% Titanium (Ti) 1.1% - 1.7% Niobium (Nb) 0.05% - 0.13% Carbon (C) 0.01% - 0.02% Boron (B) 15 0.008% - 0.015% Zirconium (Zr) 0.007% - 0.013% Silicon (Si) up to 0.6% Hafnium (Hf) Nickel (Ni).
Description
Nickel based superalloy, raw material, component and method
The invention relates to a Nickel based superalloy, a raw material, a component and method to cast it.
When later stage blades are designed for aero efficiency and against creep, the design work is constrained by LCF in the disc attachment due to the mass of said blades. A reduced density in the blade alloy will, everything else being equal, enable designs with better aero efficiency and/or allow higher metal temperatures, as it eases the LCF constraint. Improved Aero efficiency and/or increased allowable metal temperatures will e.g., enable an increased thermal efficiency in a combined cycle power plant.
Later stage blades operate at temperatures where hot corrosion agents are particularly aggressive. In order to enable fuel flexibility, including use of corrosive fuels including biofuels and, handle air borne contaminants such as sea salt, it is advantageous to have a good hot corrosion resistance.
The general rule of thumb for good hot corrosion resistance is to have a nominal composition with at least about 12 wt% Chromium (Cr), at most about 2 wt% Molybdenum (Mo) and no Vanadium (V).
About 12 wt% Cr enables formation of a continuous layer of Cr2O3 in the oxide layer to slow down further oxidation, and, to retard the influx of corrosive elements into the alloy. Molybdenum (Mo) and no Vanadium (V) can react with and accelerate the attack from corrosive agents.
Oxidation is normally not a major issue in the later stage blades since the metal temperatures are moderate by the standards of gas turbine hot stage components. Later stage blades typically operate in the 600 to 800°C range. It is then sufficient to have the ability to form a continuous and adherent Cr2O3 layer.
IN792 with a nominal composition, in wt%, of Ni-8.5Co-12.5Cr-1 ,8Mo-4W-3.4AI-4Ti-4Ta- 0.08C-0.02Zr-0.015B has a good combination of creep and hot corrosion resistance, a gamma prime particle content of about 50mol%, and is extensively used for later stage blades and other turbine components. Molybdenum (Mo) and no Vanadium (V) are used to strengthen the gamma matrix while Titanium (Ti) and Tantalum (Ta) are used to strengthen the gamma prime particles.
It is therefore the aim of the invention to improve the properties of a nickel-based superalloy.
The problem is solved by an alloy according to claim 1 , by a raw material according to claim 13, a component according to claim 14 and a method according to claim 17.
In the dependent claims further advantageous features are listed which can be combined with each other to yield further advantages.
While an increased gamma prime content above the relatively high level already seen in IN792 can be detrimental to the long-term creep strength as it can exacerbate the longterm coarsening of the gamma prime structure, coarsening is not a critical issue at the metal temperatures associated with later stage blades. While an increased gamma prime content can also be detrimental to all properties as it can exacerbate the tendency for precipitation of unwanted phases such as Laves and Sigma, in the invention the increased gamma prime content is balanced by the reduction in strengthening elements such that the phase stability is retained.
A blade alloy having creep and corrosion resistance on the IN792 level and a reduced density would enable higher performance. It is accordingly the aim of the invention to provide an alloy with IN792 level creep and corrosion resistance and a reduced density. Relative to IN792, the levels of the strengthening elements are reduced, which is detrimental for the creep strength but will reduce the density. Al is increased which will further reduce the density and increase the gamma prime particle content which is beneficial for the creep strength. Ta is replaced by Nb which will further reduce the density. Si is included at a low measured level while nominally set to zero in most specifications for IN792. This inclusion is to avoid the risk for the reduction in oxidation and hot corrosion resistance which might occur if the production process for a component turned out to result in an unusually low level of Silicon (Si) since Silicon (Si) has a beneficial catalytic effect on the selective oxidation of protective Cr2O3 even at low levels. Hafnium (Hf) values from up to 2.0 wt%, the range seen in commercial alloys, can be added as necessary. The higher Hafnium (Hf) values would be used if the alloy is directionally cast.
Hafnium (Hf) up to about 2.0 wt% is included by some casting vendors to improve the casting yield. Whether Hafnium (Hf) is an advantage, and if so at what level, depends on the component geometry, and, the specific casting methodology, mold materials and rigs used by the vendor. When Hafnium (Hf) is added, the levels of one or more of the other alloy elements are reduced somewhat to ensure that this does not cause an increased propensity for precipitation of unwanted phases such as Laves and Sigma.
Tantalum (Ta) is often added for oxidation resistance as well as strength in alloys made for hot stage blades while Niobium (Nb) provides the same strengthening effect per at% but does not boost the oxidation resistance. Hence a replacement of Tantalum (Ta) by Niobium (Nb) is beneficial in later stage blades where a reduced density at the cost of some oxidation resistance is a reasonable bargain.
The inventive Nickel based alloy has following composition: comprising (in wt%) Nickel based superalloy, comprising (in wt%) 3,0% - 9,0% Cobalt (Co), especially 4,0% - 9,0% Cobalt (Co), 11 ,0% - 14,0% Chromium (Cr), especially 11 ,5% - 13,5% Chromium (Cr), very especially 12,0% - 13,0% Chromium (Cr), 1 ,0% - 3,5% Molybdenum (Mo), especially 1 ,5% - 3,5% Molybdenum (Mo), 4,0% - 6,0% Aluminum (Al), especially 4,5% - 6,0% Aluminum (Al), very especially 5,0% Aluminum (Al), 2,7% - 4,0% Titanium (Ti), especially 3,0% - 4,0% Titanium (Ti), very especially 3,5% Titanium (Ti), 0,03% - 0,15% Carbon (C), especially 0,08% - 0,15% Carbon (C), 0,005% - 0,030% Boron (B), especially 0,008% - 0,020% Boron (B), very especially 0,015% Boron (B), 0,005% - 0,03% Zirconium (Zr) , especially 0,008% - 0,012% Zirconium (Zr) , very especially 0,01% Zirconium (Zr), Nickel (Ni) and unavoidable impurities especially consisting of these elements, optionally
1 ,5% - 3,0 % Tungsten (W) , especially 1 ,5% - 2,5% Tungsten (W)
1 ,0% - 2,5% Niobium (Nb), especially 1 ,0% - 2,0% Nion (Nb) ,
0.005% - 0.03% Silicon (Si), up to to 2,0% Hafnium (Hf), especially 0,5% to 1.5% Hafnium (Hf), up to 5 wt% Iron (Fe), especially up to 3,0wt% Iron (Fe), max 5ppm Sulfur (S).
Especially it consists of these elements,
Especially only the elements are used for this alloy.
One possible composition is given, in wt%, by Ni-5Co-12.5Cr-2Mo-2W-5AI-3.5Ti-1.5Nb- 0.12C-0.015B-0.01Zr and has a density in the 7.8 to 8kg/dm3 range and a gamma prime particle content (at 850C) of 67mol%
It can be noted that the alloy is free of Rhenium (Re) and Tantalum (Ta) , two elements which are commonly used in modern Nickel base superalloys, but which unfortunately significantly increase their densities. Boron (B), Carbon (C) and Zirconium (Zr) are used for grain boundary strengthening and are included at normal values for high strength Nickel base gamma prime strengthened superalloys.
The alloy should furthermore preferably be cast with a clean process such that e.g., the resulting sulfur content is below 5 ppm. Sulfur (S) can severely reduce the protective capability and adherence of the Cr2O3 layer, hence a strict cap on this element is prudent despite the moderate service temperatures.
One possible embodiment is given, in wt%, by Ni-5Co-12.5Cr-1.8Mo-2.2W-5AI-3.5Ti- 1.5Nb-0.1C-0.015B-0.01Zr-0.01Si. It has a predicted density of about 7.9 kg/dm3 using the extended Caron formula below, and, a predicted gamma prime particle content, at 850°C, of 67mol% based on ThermoCalc with TTNi8 as data base. Relative to IN792 the levels of the gamma matrix elements Co and W are reduced. The reduction in gamma matrix strength is however small since the amount of gamma matrix to be strengthened by Mo and W is reduced relative to IN792. 1 ,5wt% Niobium (Nb) corresponds to about 3 wt% Tantalum (Ta) on an at% basis. Hence the sum of the gamma prime strengthening elements Titanium (Ti), Tantalum (Ta) and Niobium (Nb) is reduced relative to the very high level of gamma prime strengthening elements used in IN792. Al is increased to enable a higher gamma prime content.
Hafnium (Hf) can be added as required w.r.t. the production process requirements, as done today for IN792, in which case one or more of the alloy elements need to be adjusted by those skilled in the art such that e.g., the propensity for precipitation of unwanted phases does not increase. Relative to IN792, a higher upper limit of 2,0 wt% is chosen to also allow for directional solidification casting. Furthermore, Iron (Fe) can be added as necessary to reduce the gamma prime Solvus in order to increase the heat treatment window, e.g., to manage inclusion of Hafnium (Hf) which tends to reduce the heat treatment window.
Tungsten (W) in this range provides a useful strengthening effect and low enough to avoid excessive formation of undesired phases.
Aluminum (Al) is included at between about 4wt% and 6 wt%. In this range it high enough to reduce the risk that the joint should be a weak link w.r.t. oxidation and corrosion, high enough to assist in the formation of gamma prime particles, and low enough to avoid excessive formation of undesired phases.
Tantalum (Ta) is preferably not included.
Molybdenum (Mo) is a potent gamma matrix strengthening element with a low diffusivity.
Carbon (C) is an element with a high diffusivity and can at a first glance be assumed to equilibrate easily with surrounding parts. In-house experience does however sometimes show essentially carbide free joints (which is not useful) when Carbon (C) free BFM’s have been used. Our interpretation is that the carbon close to the joint is at least temporarily bound in carbo-borides as Boron (B) from the joint diffuses from the joint. There should be a lower limit on Carbon (C) to avoid completely Carbon (C) free joints, but too high levels of Carbon (C) implies a risk for formation of embrittling carbide films and elongated carbides. Carbon (C) is included at between 0.03wt% and 0.15 wt%.
Zirconium (Zr) is an element which provides grain boundary strengthening and acts as a sulfur gatherer at low measured levels. It needs to be capped at a low level since it tends to segregate which could lead to incipient melting since it is a melt depressant. It is included at between 0.005wt% and 0.03 wt%.
Further examples of the invention are listed here:
Claims
Claims
1. Nickel based superalloy, comprising (in wt%) 3,0% - 9,0% Cobalt (Co), especially 4,0% - 9,0% Cobalt (Co), 11 ,0% - 14,0% Chromium (Cr), especially 11 ,5% - 13,5% Chromium (Cr), very especially 12,0% - 13,0% Chromium (Cr), 1 ,0% - 3,5% Molybdenum (Mo), especially 1 ,5% - 3,5% Molybdenum (Mo), 4,0% - 6,0% Aluminum (Al), especially 4,5% - 6,0% Aluminum (Al), very especially 5,0% Aluminum (Al), 2,7% - 4,0% Titanium (Ti), especially 3,0% - 4,0% Titanium (Ti), very especially 3,5% Titanium (Ti), 0,03% - 0,15% Carbon (C), especially 0,08% - 0,15% Carbon (C), 0,005% - 0,030% Boron (B), especially 0,008% - 0,020% Boron (B), very especially 0,015% Boron (B), 0,005% - 0,03% Zirconium (Zr) , especially 0,008% - 0,012% Zirconium (Zr) , very especially 0,01 % Zirconium (Zr), Nickel (Ni) and unavoidable impurities especially consisting of these elements, optionally
1 ,5% - 3,0 % Tungsten (W) , especially 1 ,5% - 2,5% Tungsten (W) 1 ,0% - 2,5% Niobium (Nb), especially 1 ,0% - 2,0% Nion (Nb) , 0.005% - 0.03% Silicon (Si), up to to 2,0% Hafnium (Hf), especially 0,5% to 1.5% Hafnium (Hf), up to 5 wt% Iron (Fe), especially up to 3,0wt% Iron (Fe), max 5ppm Sulfur (S).
SUBSTITUTE SHEET (RULE 26)
Nickel based superalloy according to claim 1 , comprising no Tungsten (W) and/or no Tantalum (Ta). Nickel based superalloy according to claim 1 or 2, comprising either Niobium (Nb) or Hafnium (Hf). Nickel based superalloy according to any of claims 1 , 2 or 3, comprising 1 ,5% - 2,5% Molybdenum (Mo), especially 2,0% Molybdenum (Mo). Nickel based superalloy according to any of claims 1 , 2 or 3, comprising 2,5% - 3,5% Molybdenum (Mo), especially 3,0% Molybdenum (Mo). Nickel based superalloy according to any of claims 1 , 2, 3, 4 or 5, comprising (in wt%)
4.5% - 5.5% Cobalt (Co) 12% - 13% Chromium (Cr) 1 .6% - 2% Molybdenum (Mo) 1 .7% - 2.5% Tungsten (W) 4.6% - 5.2% Aluminum (Al) 3.1% - 3.7% Titanium (Ti) 1.1% - 1.7% Niobium (Nb) 0.05% - 0.13% Carbon (C) 0.01% - 0.02% Boron (B) 0.008% - 0.015% Zirconium (Zr) 0.007% - 0.013% Silicon (Si) up to 0.6% Hafnium (Hf) Nickel (Ni). Nickel based superalloy according to any of claims 1 , 2, 3, 4 or 5, comprising (in wt%)
4.5% - 5.5% Cobalt (Co) 12% - 13% Chromium (Cr)
1 .6% - 3.4% Molybdenum (Mo)
4.6% - 5.4% Aluminum (Al)
3.1% - 3.7% Titanium (Ti)
0.07% - 0.15% Carbon (C)
0.01% - 0.02% Boron (B)
0.008% - 0.015% Zirconium (Zr)
Nickel (Ni), optionally
1 .7% - 2.5% Tungsten (W)
1 .0% to 2.0% Hafnium (Hf)
1.1% - 1.7% Niobium (Nb). Nickel based superalloy according to any of claims 1 , 2, 3, 4, 5 or 7, comprising (in wt%)
5% Cobalt (Co)
12.5% Chromium (Cr)
2% Molybdenum (Mo)
2% Tungsten (W)
5% Aluminum (Al)
3.5% Titanium (Ti)
1.5% Niobium (Nb)
0.12% Carbon (C)
0.015% Boron (B)
0.01% Zirconium (Zr) Nickel (Ni). Nickel based superalloy according to any of claims 1 , 2, 3, 4, 5 or 7, comprising (in wt%)
5% Cobalt (Co)
12.5% Chromium (Cr)
2% Molybdenum (Mo)
2% Tungsten (W)
5% Aluminum (Al)
3.5% Titanium (Ti)
1 .5% Hafnium (Hf)
0.12% Carbon (C)
0.015% Boron (B)
0.01% Zirconium (Zr)
Nickel (Ni).
Nickel based superalloy according to any of claims 1 , 2, 3, 4, 5 or 7, comprising (in wt%)
5% Cobalt (Co)
12.5% Chromium (Cr)
3% Molybdenum (Mo)
5% Aluminum (Al)
3.5% Titanium (Ti)
1 .5% Hafnium (Hf)
0.12% Carbon (C)
0.015% Boron (B)
0.01% Zirconium (Zr) Nickel (Ni). Nickel based superalloy according to any of claims 1 , 2, 3, 4, 5 or 6, comprising (in wt%)
5% Cobalt (Co)
12.5% Chromium (Cr)
1 .8% Molybdenum (Mo)
2.2% Tungsten (W)
5% Aluminum (Al)
3.3% Titanium (Ti)
1.4% Niobium (Nb)
0.1% Carbon (C)
0.015% Boron (B)
0.01% Zirconium (Zr)
0.01% Silicon (Si)
0.5% Hafnium (Hf) Nickel (Ni). Nickel based superalloy according to any of claims 1 , 2, 3, 4, 5 or 6, comprising (in wt%)
5% Cobalt (Co)
12.5% Chromium (Cr)
1 .8% Molybdenum (Mo)
2.2% Tungsten (W)
5% Aluminum (Al)
3.5% Titanium (Ti)
1.5% Niobium (Nb)
0.1% Carbon (C)
0.015% Boron (B)
0.01% Zirconium (Zr)
0.01% Silicon (Si)
Nickel (Ni). Raw material comprising a composition according to any of the claims 1 to 12. especially consisting of a composition according to any of the claims 1 to 12, wherein the raw material is a powder, especially a powder comprising binder or ceramic particles or wherein the raw material is in form of a bar, rod or a billet. Component, having a composition according to any of the claims 1 to 12, which is especially a component of a turbine, very especially a blade or a vane. Component according to claim 14, wherein the component is casted, especially in equiaxed microstructure. Component according to claim 14, wherein the component is casted, especially in columnar or single-crystal microstructure. Method to produce a component according to claim 14, 15 o 16, wherein in the alloy is melted, especially casted in equiaxed microstructure or directionally solidified structure.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2218300.8 | 2022-12-06 | ||
| GB2218300.8A GB2625101A (en) | 2022-12-06 | 2022-12-06 | Nickel based superalloy, raw material, component and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2024120733A1 true WO2024120733A1 (en) | 2024-06-13 |
Family
ID=84926712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EP2023/081291 WO2024120733A1 (en) | 2022-12-06 | 2023-11-09 | Nickel based superalloy, raw material, component and method |
Country Status (2)
| Country | Link |
|---|---|
| GB (1) | GB2625101A (en) |
| WO (1) | WO2024120733A1 (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1511999A (en) * | 1976-03-24 | 1978-05-24 | Inco Europ Ltd | Nickel-based alloys |
| US20080240972A1 (en) * | 2006-12-01 | 2008-10-02 | Industria De Turbo Propulsores, S.A. | Low-density directionally solidified single-crystal superalloys |
| CN112921206B (en) * | 2021-01-20 | 2021-12-28 | 北京钢研高纳科技股份有限公司 | High gamma prime content nickel-base superalloy powder for additive manufacturing, method of use thereof, and nickel-base superalloy component |
-
2022
- 2022-12-06 GB GB2218300.8A patent/GB2625101A/en active Pending
-
2023
- 2023-11-09 WO PCT/EP2023/081291 patent/WO2024120733A1/en unknown
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1511999A (en) * | 1976-03-24 | 1978-05-24 | Inco Europ Ltd | Nickel-based alloys |
| US20080240972A1 (en) * | 2006-12-01 | 2008-10-02 | Industria De Turbo Propulsores, S.A. | Low-density directionally solidified single-crystal superalloys |
| CN112921206B (en) * | 2021-01-20 | 2021-12-28 | 北京钢研高纳科技股份有限公司 | High gamma prime content nickel-base superalloy powder for additive manufacturing, method of use thereof, and nickel-base superalloy component |
Also Published As
| Publication number | Publication date |
|---|---|
| GB202218300D0 (en) | 2023-01-18 |
| GB2625101A (en) | 2024-06-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6767155B2 (en) | Articles and methods of forming articles | |
| AU2007345231B2 (en) | Nickel-base alloy for gas turbine applications | |
| JP6514441B2 (en) | Cast nickel base superalloy containing iron | |
| CA2479774C (en) | Ni-base directionally solidified and single-crystal superalloy | |
| JP6796129B2 (en) | Nickel-based alloy | |
| JP5299899B2 (en) | Ni-base superalloy and manufacturing method thereof | |
| JP3892831B2 (en) | Superalloys for single crystal turbine vanes. | |
| KR100954683B1 (en) | High strength, corrosion and oxidation resistant, nickel base superalloy and directionally solidified articles comprising the same | |
| JP2004332061A (en) | HIGHLY OXIDATION RESISTANT Ni BASED SUPERALLOY, AND GAS TURBINE COMPONENT | |
| CN102803528B (en) | Nickel-base single-crystal superalloy and turbine wing using same | |
| JP5024797B2 (en) | Cobalt-free Ni-base superalloy | |
| TWI248975B (en) | Nickel-base superalloy for high temperature, high strain application | |
| JP4266196B2 (en) | Nickel-base superalloy with excellent strength, corrosion resistance and oxidation resistance | |
| CA2612815A1 (en) | Low-density directionally solidified single-crystal superalloys | |
| US20050139295A1 (en) | Method for selecting a reduced-tantalum superalloy composition of matter and article made therefrom | |
| CN109554580B (en) | Nickel-based alloy, preparation method thereof and manufactured article | |
| JP6982172B2 (en) | Ni-based superalloy castings and Ni-based superalloy products using them | |
| JP4911753B2 (en) | Ni-base superalloy and gas turbine component using the same | |
| WO2024120733A1 (en) | Nickel based superalloy, raw material, component and method | |
| US20050067062A1 (en) | Single-crystal Ni-based superalloy with high temperature strength, oxidation resistance and hot corrosion resistance | |
| JPH1121645A (en) | Ni-base superalloy having heat resistance, production of ni-base superalloy having heat resistance, and ni-base superalloy parts having heat resistance | |
| JP4184648B2 (en) | Ni-based single crystal alloy excellent in strength and corrosion resistance and its manufacturing method | |
| JPH0617171A (en) | Alloy for gas turbine blade | |
| KR20110114928A (en) | Ni base single crystal superalloy with good creep property | |
| US11739398B2 (en) | Nickel-based superalloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 23804999 Country of ref document: EP Kind code of ref document: A1 |