CA2612815A1 - Low-density directionally solidified single-crystal superalloys - Google Patents
Low-density directionally solidified single-crystal superalloys Download PDFInfo
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- CA2612815A1 CA2612815A1 CA002612815A CA2612815A CA2612815A1 CA 2612815 A1 CA2612815 A1 CA 2612815A1 CA 002612815 A CA002612815 A CA 002612815A CA 2612815 A CA2612815 A CA 2612815A CA 2612815 A1 CA2612815 A1 CA 2612815A1
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- Prior art keywords
- low
- density
- nickel
- alloy
- heat treatment
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 19
- 239000013078 crystal Substances 0.000 title claims description 16
- 229910052796 boron Inorganic materials 0.000 claims abstract description 12
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 12
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 10
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 10
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 8
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 8
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 7
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000004411 aluminium Substances 0.000 claims abstract description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 7
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 7
- 239000011651 chromium Substances 0.000 claims abstract description 7
- 239000010941 cobalt Substances 0.000 claims abstract description 7
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 7
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 7
- 239000011733 molybdenum Substances 0.000 claims abstract description 7
- 239000010936 titanium Substances 0.000 claims abstract description 7
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 7
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 5
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 5
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims abstract description 4
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 4
- 239000012535 impurity Substances 0.000 claims abstract description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 3
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 3
- 239000010937 tungsten Substances 0.000 claims abstract description 3
- 238000010438 heat treatment Methods 0.000 claims description 15
- 238000005266 casting Methods 0.000 claims description 5
- 238000001556 precipitation Methods 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 description 42
- 239000000956 alloy Substances 0.000 description 42
- 238000004519 manufacturing process Methods 0.000 description 11
- 239000000463 material Substances 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 238000007711 solidification Methods 0.000 description 6
- 230000008023 solidification Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 238000011282 treatment Methods 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 239000002243 precursor 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%
-
- 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
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
Abstract
The present invention relates to a low-density nickel-base superalloy comprising the following elements (percent by weight): 7-13% Chromium, 0-16% Cobalt, 2-5%
Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten, 0-2%
Vanadium, 0-5% Molybdenum, 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02%
Zirconium, nickel and residual impurities, to its use and to the process for obtaining it.
Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten, 0-2%
Vanadium, 0-5% Molybdenum, 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02%
Zirconium, nickel and residual impurities, to its use and to the process for obtaining it.
Description
LOW-DENSITY DIRECTIONALLY SOLIDIFIED SINGLE-CRYSTAL SUPERALLOYS
Field of the Invention The present invention relates to nickel-base superalloys used to manufacture gas turbine blades or vanes by means of directional solidification or in the form of single crystals. The present invention particularly relates to low-density alloys which can work under high temperature and high load conditions.
State of the Art Nickel-base superalloys are widely used in the manufacture of components for gas turbines. In the particular field of gas turbines for aircraft, apart from the high requirements from the stress and temperature point of view, it is also important to develop low-density alloys. A precursor of low-density alloys is the InlOO
alloy (density 7.76 gr/cm3) developed at that beginning of the 60s by The International Nickel Company (INCO) and covered by patent US 3,061,426. This alloy is still used today to manufacture equiaxed turbine blades although it is admitted that it has low castability and low corrosion resistance.
In100 has been used as the basis for developing many alloys. Among others, In6212 (density 8.02 gr/cm3) covered by patent US 4,358,318 was also developed by INCO as a low-density material with better corrosion resistance and castability than those of In100 at the expense of a slight increase of density.
These two equiaxed materials, InlOO and In 6212, have been used as the basis for developing several single-crystal alloys. InlOO was used as a reference for developing the RR2000 alloy, covered by patent GB 2105369A in 1983 whereas In6212 was used as the basis for developing the CMSX-6 alloy, covered by patent US
4,721,540.
Both single-crystal alloys were developed according to a similar strategy. In both cases, the amount of grain boundary hardening elements such as carbon, boron and zirconium was eliminated to increase the melting point of the alloy. It was thus possible to carry out a solution heat treatment of the hardening gamma prime phase dissolving the microstructure obtained directly after the casting and achieving a fine and homogeneous distribution of precipitates in the subsequent heat treatments.
There is therefore a need to develop alternative alloys to those used currently.
Description of the Invention The present invention provides a low-density superalloy (7.867 g/cm3) useful for manufacturing components by means of directional solidification or single-crystal components with a relaxed grain structure specification.
A first aspect of the invention relates to a nickel-base superalloy comprising the following elements (percent by weight):
7-13% Chromium, 0-16% Cobalt, 2-5% Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten 0-2% Vanadium 0-5% Molybdenum 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02% Zirconium, Nickel and residual impurities In a particular embodiment the present invention relates to a nickel-base superalloy comprising: 0.07% carbon, 10% chromium, 15% cobalt, 3% molybdenum, 5.5% aluminium, 4% titanium, 1% vanadium, 1.4% hafnium, 0.015% boron and 0.01%
zirconium.
In a particular embodiment the present invention relates to a nickel-base superalloy comprising: 0.07% carbon, 10% chromium, 5% cobalt, 3% molybdenum, 2%
tantalum, 4.8% aluminium, 4.7% titanium, 1.4% hafnium, 0.015% boron and 0.01%
zirconium.
A second aspect of the present invention relates to the use of a nickel-base superalloy described above for obtaining a directionally solidified casting or a casting in single-crystal form.
A third aspect of the present invention relates to a process for obtaining a superalloy as described above, comprising the following steps:
a) Solution heat treatment at a temperature comprised between 1190-1250 C for 1 to 5 hours b) Intermediate heat treatment at a temperature comprised between 1000-1100 C
for 1 to 5 hours c) Precipitation heat treatment at a temperature comprised between 850-900 C
for 1 to 16 hours A fourth aspect of the present invention relates to a gas turbine comprising components manufactured with a superalloy as described above, or from alloys obtained by means of a process comprising the following steps:
a) Solution heat treatment at a temperature comprised between 1190- 1250 C
for 1 to 5 hours b) intermediate heat treatment at a temperature comprised between 1000-1100 C
for 1 to 5 hours c) precipitation heat treatment at a temperature comprised between 850-900 C
for 1 to 16 hours Brief Description of Drawings Figure 1: Low-cycle fatigue of composition E compared to commercial composition A.
Detailed Description of an Embodiment The present invention provides a low-density superalloy useful for manufacturing components by means of directional solidification or single-crystal components with a relaxed grain structure specification. The alloy of the present invention was developed taking two single-crystal alloys, RR2000 and CMSX-6, as a reference.
The following table shows examples of alloys according to this invention, alloys E to G, inclusive. Alloys A and B are commercial alloys for directional solidification whereas C and D are commercial alloys for manufacturing low-density single-crystal components. The latter alloys are only set forth as a comparison and are not included within the scope of this invention.
Alloy Co Cr Mo W Al Ta V Ti Re Hf C B Zr A 9,2 8,1 0,5 9,5 5,6 3,2 0,7 1,4 0,07 0,015 0,007 B 9,3 6 0,5 8,4 5,7 3,4 0,7 3 1,4 0,07 0,015 0,005 C 15 10 3 5,5 1 4 D 5 10 3 4,8 2 4,7 0,1 E 15 10 3 5,5 1 4 1,4 0,07 0,015 0,005 F 6 12 3 2 4,5 4,7 1,4 0,07 0,015 0,005 G 5 10 3 4,8 2 4,7 1,4 0,07 0,015 0,005 Carbon, boron and zirconium were added to the base composition of RR2000 and CMSX-6 but without reaching the high levels of these elements in the compositions In100 or of In6212. The C, B and Zr of the alloy of this invention were maintained at the same levels as other commercial allows that are usually used for manufacturing directionally solidified components such as alloy A and B of the previous table. The maximum carbon content was limited to 0.12%, the maximum boron content to 0.03%
and the maximum zirconium content to 0.02%, while these limits are 0.5%, 0.1%
and 0.25% respectively in In100. Hafnium was added to the composition to favor carbide formation in the grain boundary.
The introduction of these elements involved a reduction in the melting temperature of the alloy. Such that the maximum temperature at which the supersolution heat treatment can be carried out is limited, and therefore it is not possible to reach the high temperatures that are used in the supersolution treatments of single-crystal materials. The gamma prime dissolution that was achieved with the supersolution treatments was thus not as effective as that achieved with the high temperature treatments used in single-crystals. Nevertheless, there are commercial alloys which can be used to manufacture components by means of directional solidification with and without supersolution heat treatment. The absence of supersolution heat treatment gave rise to a drop in the alloy temperature capacity of about 30 C.
Even with this reduction, the benefit obtained with the low density of the alloy of this invention makes it a suitable option for manufacturing gas turbine blades or vanes.
The absence of supersolution heat treatment can also give rise to a loss of the resistance to low-cycle fatigue of the alloy with respect to the commercial RR2000 alloy from which it has been developed. However, as can be seen in Figure 1, composition E
of Table 1 has fatigue properties that are greater than those of commercial alloy A.
The introduction or grain boundary hardening elements allowed the use of this alloy for manufacturing directionally solidified components, which is not possible with most single-crystal alloys. The fact of using an alloy in directional solidification form instead of in single-crystal form gave rise to reduction in the creep rupture of the alloy.
Nevertheless, this decrease was considered very small and therefore the alloy of this invention is sufficiently attractive for a wide range of applications.
Finally, it must be mentioned that the main purpose of this alloy is to offer a low-density alternative to alloys that are currently used in gas turbines. The presence of elements such as C, B, Zr and Hf improved the tolerance of the alloy to the presence of grain boundaries at the expense of a small reduction in properties such as fatigue or creep rupture. But having been designed from low-density single-crystal alloys, even with this decrease of properties, the alloy of the present invention offers a clear improvement with respect to the alloys that are currently used for manufacturing directionally solidified materials. This benefit will be even greater in the design of advanced gas turbines in which the rotational speed is higher and therefore the 5 centrifugal forces are greater, and the use of a low-density material is a clear advantage.
Likewise, it must also be mentioned that the use of this material in gas turbines for aircraft involves a clear improvement with respect to current alloys because it can give rise to lighter components and therefore to a lower specific turbine consumption.
Field of the Invention The present invention relates to nickel-base superalloys used to manufacture gas turbine blades or vanes by means of directional solidification or in the form of single crystals. The present invention particularly relates to low-density alloys which can work under high temperature and high load conditions.
State of the Art Nickel-base superalloys are widely used in the manufacture of components for gas turbines. In the particular field of gas turbines for aircraft, apart from the high requirements from the stress and temperature point of view, it is also important to develop low-density alloys. A precursor of low-density alloys is the InlOO
alloy (density 7.76 gr/cm3) developed at that beginning of the 60s by The International Nickel Company (INCO) and covered by patent US 3,061,426. This alloy is still used today to manufacture equiaxed turbine blades although it is admitted that it has low castability and low corrosion resistance.
In100 has been used as the basis for developing many alloys. Among others, In6212 (density 8.02 gr/cm3) covered by patent US 4,358,318 was also developed by INCO as a low-density material with better corrosion resistance and castability than those of In100 at the expense of a slight increase of density.
These two equiaxed materials, InlOO and In 6212, have been used as the basis for developing several single-crystal alloys. InlOO was used as a reference for developing the RR2000 alloy, covered by patent GB 2105369A in 1983 whereas In6212 was used as the basis for developing the CMSX-6 alloy, covered by patent US
4,721,540.
Both single-crystal alloys were developed according to a similar strategy. In both cases, the amount of grain boundary hardening elements such as carbon, boron and zirconium was eliminated to increase the melting point of the alloy. It was thus possible to carry out a solution heat treatment of the hardening gamma prime phase dissolving the microstructure obtained directly after the casting and achieving a fine and homogeneous distribution of precipitates in the subsequent heat treatments.
There is therefore a need to develop alternative alloys to those used currently.
Description of the Invention The present invention provides a low-density superalloy (7.867 g/cm3) useful for manufacturing components by means of directional solidification or single-crystal components with a relaxed grain structure specification.
A first aspect of the invention relates to a nickel-base superalloy comprising the following elements (percent by weight):
7-13% Chromium, 0-16% Cobalt, 2-5% Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten 0-2% Vanadium 0-5% Molybdenum 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02% Zirconium, Nickel and residual impurities In a particular embodiment the present invention relates to a nickel-base superalloy comprising: 0.07% carbon, 10% chromium, 15% cobalt, 3% molybdenum, 5.5% aluminium, 4% titanium, 1% vanadium, 1.4% hafnium, 0.015% boron and 0.01%
zirconium.
In a particular embodiment the present invention relates to a nickel-base superalloy comprising: 0.07% carbon, 10% chromium, 5% cobalt, 3% molybdenum, 2%
tantalum, 4.8% aluminium, 4.7% titanium, 1.4% hafnium, 0.015% boron and 0.01%
zirconium.
A second aspect of the present invention relates to the use of a nickel-base superalloy described above for obtaining a directionally solidified casting or a casting in single-crystal form.
A third aspect of the present invention relates to a process for obtaining a superalloy as described above, comprising the following steps:
a) Solution heat treatment at a temperature comprised between 1190-1250 C for 1 to 5 hours b) Intermediate heat treatment at a temperature comprised between 1000-1100 C
for 1 to 5 hours c) Precipitation heat treatment at a temperature comprised between 850-900 C
for 1 to 16 hours A fourth aspect of the present invention relates to a gas turbine comprising components manufactured with a superalloy as described above, or from alloys obtained by means of a process comprising the following steps:
a) Solution heat treatment at a temperature comprised between 1190- 1250 C
for 1 to 5 hours b) intermediate heat treatment at a temperature comprised between 1000-1100 C
for 1 to 5 hours c) precipitation heat treatment at a temperature comprised between 850-900 C
for 1 to 16 hours Brief Description of Drawings Figure 1: Low-cycle fatigue of composition E compared to commercial composition A.
Detailed Description of an Embodiment The present invention provides a low-density superalloy useful for manufacturing components by means of directional solidification or single-crystal components with a relaxed grain structure specification. The alloy of the present invention was developed taking two single-crystal alloys, RR2000 and CMSX-6, as a reference.
The following table shows examples of alloys according to this invention, alloys E to G, inclusive. Alloys A and B are commercial alloys for directional solidification whereas C and D are commercial alloys for manufacturing low-density single-crystal components. The latter alloys are only set forth as a comparison and are not included within the scope of this invention.
Alloy Co Cr Mo W Al Ta V Ti Re Hf C B Zr A 9,2 8,1 0,5 9,5 5,6 3,2 0,7 1,4 0,07 0,015 0,007 B 9,3 6 0,5 8,4 5,7 3,4 0,7 3 1,4 0,07 0,015 0,005 C 15 10 3 5,5 1 4 D 5 10 3 4,8 2 4,7 0,1 E 15 10 3 5,5 1 4 1,4 0,07 0,015 0,005 F 6 12 3 2 4,5 4,7 1,4 0,07 0,015 0,005 G 5 10 3 4,8 2 4,7 1,4 0,07 0,015 0,005 Carbon, boron and zirconium were added to the base composition of RR2000 and CMSX-6 but without reaching the high levels of these elements in the compositions In100 or of In6212. The C, B and Zr of the alloy of this invention were maintained at the same levels as other commercial allows that are usually used for manufacturing directionally solidified components such as alloy A and B of the previous table. The maximum carbon content was limited to 0.12%, the maximum boron content to 0.03%
and the maximum zirconium content to 0.02%, while these limits are 0.5%, 0.1%
and 0.25% respectively in In100. Hafnium was added to the composition to favor carbide formation in the grain boundary.
The introduction of these elements involved a reduction in the melting temperature of the alloy. Such that the maximum temperature at which the supersolution heat treatment can be carried out is limited, and therefore it is not possible to reach the high temperatures that are used in the supersolution treatments of single-crystal materials. The gamma prime dissolution that was achieved with the supersolution treatments was thus not as effective as that achieved with the high temperature treatments used in single-crystals. Nevertheless, there are commercial alloys which can be used to manufacture components by means of directional solidification with and without supersolution heat treatment. The absence of supersolution heat treatment gave rise to a drop in the alloy temperature capacity of about 30 C.
Even with this reduction, the benefit obtained with the low density of the alloy of this invention makes it a suitable option for manufacturing gas turbine blades or vanes.
The absence of supersolution heat treatment can also give rise to a loss of the resistance to low-cycle fatigue of the alloy with respect to the commercial RR2000 alloy from which it has been developed. However, as can be seen in Figure 1, composition E
of Table 1 has fatigue properties that are greater than those of commercial alloy A.
The introduction or grain boundary hardening elements allowed the use of this alloy for manufacturing directionally solidified components, which is not possible with most single-crystal alloys. The fact of using an alloy in directional solidification form instead of in single-crystal form gave rise to reduction in the creep rupture of the alloy.
Nevertheless, this decrease was considered very small and therefore the alloy of this invention is sufficiently attractive for a wide range of applications.
Finally, it must be mentioned that the main purpose of this alloy is to offer a low-density alternative to alloys that are currently used in gas turbines. The presence of elements such as C, B, Zr and Hf improved the tolerance of the alloy to the presence of grain boundaries at the expense of a small reduction in properties such as fatigue or creep rupture. But having been designed from low-density single-crystal alloys, even with this decrease of properties, the alloy of the present invention offers a clear improvement with respect to the alloys that are currently used for manufacturing directionally solidified materials. This benefit will be even greater in the design of advanced gas turbines in which the rotational speed is higher and therefore the 5 centrifugal forces are greater, and the use of a low-density material is a clear advantage.
Likewise, it must also be mentioned that the use of this material in gas turbines for aircraft involves a clear improvement with respect to current alloys because it can give rise to lighter components and therefore to a lower specific turbine consumption.
Claims (6)
1.- A nickel-base superalloy comprising the following elements (percent by weight) 7-13% Chromium, 0-16% Cobalt,
2-5% Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten 0-2% Vanadium 0-5% Molybdenum 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02% Zirconium, Nickel and residual impurities.
2.- A superalloy according to claim 1, comprising: 0.07% carbon, 10%
chromium, 15% cobalt, 3% molybdenum, 5.5% aluminium, 4% titanium, 1% vanadium, 1.4% hafnium, 0.015% boron and 0.01% zirconium.
2.- A superalloy according to claim 1, comprising: 0.07% carbon, 10%
chromium, 15% cobalt, 3% molybdenum, 5.5% aluminium, 4% titanium, 1% vanadium, 1.4% hafnium, 0.015% boron and 0.01% zirconium.
3.- A superalloy according to any of the previous claims, comprising: 0.07%
carbon, 10% chromium, 5% cobalt, 3% molybdenum, 2% tantalum, 4.8% aluminium,
carbon, 10% chromium, 5% cobalt, 3% molybdenum, 2% tantalum, 4.8% aluminium,
4.7% titanium, 1.4% hafnium, 0.015% boron and 0.01% zirconium.
4.- The use of a nickel-base superalloy according to any of the previous claims for obtaining a directionally solidified casting or a casting in single-crystal form.
4.- The use of a nickel-base superalloy according to any of the previous claims for obtaining a directionally solidified casting or a casting in single-crystal form.
5.- A process for obtaining a superalloy described in any of claims 1-3 comprising the following steps:
a) solution heat treatment at a temperature comprised between 1190- 1250 °C for 1 to 5 hours b) intermediate heat treatment at a temperature comprised between 1000-1100 °C
for 1 to 5 hours c) precipitation heat treatment at a temperature comprised between 850-900 °C
for 1 to 16 hours
a) solution heat treatment at a temperature comprised between 1190- 1250 °C for 1 to 5 hours b) intermediate heat treatment at a temperature comprised between 1000-1100 °C
for 1 to 5 hours c) precipitation heat treatment at a temperature comprised between 850-900 °C
for 1 to 16 hours
6.- A gas turbine comprising components manufactured with a superalloy according to any of claims 1-3.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200603079A ES2269013B2 (en) | 2006-12-01 | 2006-12-01 | MONOCRISTALIN AND SOLIDIFIED SUPERALLOYS DIRECTLY LOW DENSITY. |
| ES200603079 | 2006-12-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2612815A1 true CA2612815A1 (en) | 2008-06-01 |
Family
ID=38293769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002612815A Abandoned CA2612815A1 (en) | 2006-12-01 | 2007-11-28 | Low-density directionally solidified single-crystal superalloys |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20080240972A1 (en) |
| EP (1) | EP1927669B1 (en) |
| AU (1) | AU2007237291A1 (en) |
| CA (1) | CA2612815A1 (en) |
| ES (2) | ES2269013B2 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8216509B2 (en) | 2009-02-05 | 2012-07-10 | Honeywell International Inc. | Nickel-base superalloys |
| JP6213185B2 (en) * | 2013-11-25 | 2017-10-18 | 株式会社Ihi | Nickel base alloy |
| JP6460336B2 (en) * | 2015-07-09 | 2019-01-30 | 三菱日立パワーシステムズ株式会社 | Ni-based high-strength heat-resistant alloy member, method for producing the same, and gas turbine blade |
| GB2554898B (en) | 2016-10-12 | 2018-10-03 | Univ Oxford Innovation Ltd | A Nickel-based alloy |
| CN109022923B (en) * | 2018-07-27 | 2020-10-27 | 江阴鑫宝利金属制品有限公司 | Alloy component of low-cobalt high-temperature alloy supercharging turbine and preparation method thereof |
| DE102021203258A1 (en) * | 2021-03-31 | 2022-10-06 | Siemens Energy Global GmbH & Co. KG | Alloy, powder, process and component |
| FR3125067B1 (en) * | 2021-07-07 | 2024-01-19 | Safran | NICKEL-BASED SUPERALLOY, MONOCRYSTAL BLADE AND TURBOMACHINE |
| GB2625101A (en) * | 2022-12-06 | 2024-06-12 | Siemens Energy Global Gmbh & Co Kg | Nickel based superalloy, raw material, component and method |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE599751A (en) | 1960-02-01 | |||
| US4358318A (en) | 1980-05-13 | 1982-11-09 | The International Nickel Company, Inc. | Nickel-based alloy |
| GB2105369B (en) * | 1981-09-11 | 1985-06-26 | Rolls Royce | An alloy suitable for making single-crystal castings |
| US4721540A (en) * | 1984-12-04 | 1988-01-26 | Cannon Muskegon Corporation | Low density single crystal super alloy |
| US4895201A (en) * | 1987-07-07 | 1990-01-23 | United Technologies Corporation | Oxidation resistant superalloys containing low sulfur levels |
| US5130088A (en) * | 1987-10-02 | 1992-07-14 | General Electric Company | Fatigue crack resistant nickel base superalloys |
| US5037495A (en) * | 1987-10-02 | 1991-08-06 | General Electric Company | Method of forming IN-100 type fatigue crack resistant nickel base superalloys and product formed |
| CH675256A5 (en) * | 1988-03-02 | 1990-09-14 | Asea Brown Boveri | |
| US5124123A (en) * | 1988-09-26 | 1992-06-23 | General Electric Company | Fatigue crack resistant astroloy type nickel base superalloys and product formed |
| US5129969A (en) * | 1988-09-28 | 1992-07-14 | General Electric Company | Method of forming in100 fatigue crack resistant nickel base superalloys and product formed |
| US4957567A (en) * | 1988-12-13 | 1990-09-18 | General Electric Company | Fatigue crack growth resistant nickel-base article and alloy and method for making |
-
2006
- 2006-12-01 ES ES200603079A patent/ES2269013B2/en not_active Expired - Fee Related
-
2007
- 2007-11-28 ES ES07380330.6T patent/ES2524249T3/en active Active
- 2007-11-28 EP EP07380330.6A patent/EP1927669B1/en not_active Revoked
- 2007-11-28 CA CA002612815A patent/CA2612815A1/en not_active Abandoned
- 2007-11-30 US US11/948,431 patent/US20080240972A1/en not_active Abandoned
- 2007-11-30 AU AU2007237291A patent/AU2007237291A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| EP1927669A1 (en) | 2008-06-04 |
| AU2007237291A1 (en) | 2008-06-19 |
| ES2269013A1 (en) | 2007-03-16 |
| US20080240972A1 (en) | 2008-10-02 |
| EP1927669B1 (en) | 2014-08-20 |
| ES2269013B2 (en) | 2007-11-01 |
| ES2524249T3 (en) | 2014-12-04 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |
Effective date: 20130802 |