High temperature aluminum alloys
View Patent ↗High temperature aluminum alloys that can be used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.) are described herein. These alloys comprise aluminum; scandium; at least one of nickel, iron, chromium, manganese and cobalt; and at least one of zirconium, gadolinium, hafnium, yttrium, niobium and vanadiuim. These alloys comprise an aluminum solid solution matrix and a mixture of various dispersoids. These alloys are substantially free of magnesium.
1. An aluminum alloy comprising:
about 0.5-2.6 weight percent scandium;
about 2-10 weight percent nickel, about 0.4-2 weight percent zirconium, about 4-8.8 weight percent gadolinium; and
the balance substantially aluminum,
the alloy characterized by at least some Ll 2 Al 3 Sc fine and coherent precipitate dispersoids that are an ordered face centered cubic structure with scandium atoms located at the corners and aluminum atoms located on the cube faces and that are fine and coherent with the aluminum matrix microstructure produced by a rapid solidification technique utilizing a cooling rate of at least about 10 3 ° C./second or higher and is compacted by vacuum hot pressing at about 343-399° C. to produce an alloy having a tensile strength of at least 118 ksi at 100° C.
2. The aluminum alloy of claim 1 , wherein the alloy comprises an aluminum solid solution matrix and a plurality of dispersoids, the dispersoids comprising at least one of:
Al 3 Ni, Al 3 Fe, Al 6 Fe, Al 7 Cr, Al 6 Mn, Al 9 CO 2 , and Al 3 X,
each Al 3 X dispersoid having an Ll 2 structure where X comprises scandium and at least one of: zirconium, gadolinium, hafnium, yttrium, niobium and vanadium.
3. The aluminum alloy of claim 1 , wherein the alloy is substantially free of magnesium.
4. The aluminum alloy of claim 1 , wherein the alloy is capable of being used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.).
5. The aluminum alloy of claim 1 , wherein the aluminum alloy is used in at least one of: an aircraft component, a rocket component, and an automobile component.
6. The aluminum alloy of claim 5 , wherein the rocket component comprises at least one of a structural jacket, a turbo pump housing, a turbine rotor, a turbine rotor housing, an impeller, a valve, a valve housing, an injector, a nozzle, a bracket, a duct, a plumbing component, and a structural rocket engine component.
7. The aluminum alloy of claim 5 , wherein the aircraft component comprises at least one of an air inlet housing, a stator assembly a gearbox, a bearing housing, a carbon seal housing, a dome, a cover, a vane, and a stator.
8. The aluminum alloy of claim 1 , wherein the alloy further comprises up to about 50 volume percent of a reinforcing second phase.
9. The aluminum alloy of claim 8 , wherein the reinforcing second phase comprises at least one of: an oxide, a carbide, a nitride, an oxynitride, an oxycarbonitride, a silicide, a boride, a ferrous alloy, boron, graphite, tungsten, titanium, SiC, Si 3 N 4 , Al 2 O 3 , B 4 C, Y 2 O 3 , MgAl 2 O 4 , TiC and TiB 2 .
10. The aluminum alloy of claim 1 , wherein the rapid solidification technique comprises at least one of: melt spinning, splat quenching, atomization, spray deposition, vacuum plasma spraying, cold spraying, laser melting, mechanical alloying, cryomilling, spin forming, and ball milling.
11. The aluminum alloy of claim 1 , wherein the rapid solidification technique comprises at least the following steps:
creating an ingot having a predetermined composition;
melting the ingot;
atomizing the melted ingot to form a powder;
degassing the powder;
compacting the powder to create a billet;
hot working the billet into a predetermined form.
12. The aluminum alloy of claim 11 , wherein the creating step occurs in an argon atmosphere at about 1149-1260° C. for about 15-60 minutes.
13. The aluminum alloy of claim 11 , wherein the melting step occurs in an argon atmosphere at about 1316-1427° C. for about 15-60 minutes.
14. The aluminum alloy of claim 13 , wherein the degassing step comprises hot vacuum degassing the powder at about 343-399° C. for about 1-5 hours.
15. The aluminum alloy of claim 11 , wherein the hot working step occurs at about 343-399° C. for about 5-30 minutes.
16. An aluminum alloy comprising:
about 0.6-2.9 weight percent scandium;
about 1.5-25 weight percent nickel;
at least one of:
about 0.4-20 weight percent gadolinium,
about 0.4-2.9 weight percent zirconium,
about 0.4-30 weight percent hafnium,
about 0.3-10 weight percent niobium,
about 0.2-10 weight percent vanadium, and
about 0.4-30 weight percent yttrium; and
the balance substantially aluminum, the alloy characterized by at least some fine and coherent Ll 2 Al 3 Sc precipitate dispersoids, that are an ordered face centered cubic structure with scandium atoms located at the corners and aluminum atoms located on the cube faces and that are fine and coherent with the aluminum matrix microstructure produced by a rapid solidification technique utilizing a cooling rate of at least about 10 3 ° C./second or higher and is compacted by vacuum hot pressing at about 343-399° C. to produce an alloy having a tensile strength of at least 118 ksi at 100° C.
17. The aluminum alloy of claim 16 , wherein the alloy comprises an aluminum solid solution matrix and a dispersion of Al 3 Ni and Al 3 X, the Al 3 X having an Ll 2 structure where X comprises scandium and at least one of gadolinium, zirconium, hafnium, niobium, vanadium and yttrium.
18. The aluminum alloy of claim 16 , wherein the alloy is substantially free of magnesium.
19. The aluminum alloy of claim 16 , wherein the alloy is capable of being used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.).
20. The aluminum alloy of claim 16 , wherein the aluminum alloy is used in at least one of: an aircraft component, a rocket component, and an automobile component.
21. The aluminum alloy of claim 20 , wherein the rocket component comprises at least one of a structural jacket, a turbo pump housing, a turbine rotor, a turbine rotor housing, an impeller, a valve, a valve housing, an injector, a nozzle, a bracket, a duct, a plumbing component, and a structural rocket component.
22. The aluminum alloy of claim 20 , wherein the aircraft component comprises at least one of an air inlet housing, a stator assembly, a gearbox, a bearing housing, a carbon seal housing, a dome, a cover, a vane, and a stator.
23. The aluminum alloy of claim 16 , comprising:
about 1-2.9 weight percent scandium;
about 6-10 weight percent nickel;
at least one of:
about 2-10 weight percent gadolinium,
about 0.5-2.9 weight percent zirconium,
about 6-12 weight percent hafnium,
about 1-6 weight percent niobium,
about 1-5 weight percent vanadium, and
about 1-8 weight percent yttrium; and
the balance substantially aluminum.
24. The aluminum alloy of claim 23 , comprising:
about 2.16 weight percent scandium;
about 8.4 weight percent nickel;
at least one of:
about 4.1-8.8 weight percent gadolinium,
about 1.5-2.5 weight percent zirconium,
about 8.0-11.5 weight percent hafnium,
about 2.5-5.0 weight percent niobium,
about 2.0-3.2 weight percent vanadium, and
about 2.5-6.5 weight percent yttrium; and
the balance substantially aluminum.
25. An aluminum alloy comprising at least one of the following compositions, in weight percent:
about Al-(6-10)Ni-(1-2.9)Sc-(6-10)Gd-(0.5-2.9)Zr;
about Al-(6-10)Ni-(1-2.9)Sc-(6-10)Gd-(1-4)Y;
about Al-(6-10)Ni-(1-2.9)Sc-(2-6)Gd-(4-8)Y;
about Al-(6-10)Ni-1-2.9)Sc-(6-12)Hf-(0.5-2.9)Zr;
about Al-(6-10)Ni-(1-2.9)Sc-(6-12)Hf-(3-7)Gd;
about Al-(6-10)Ni-(1-2.9)Sc-(6-12)Hf-(2-6)Y;
about Al-(6-10)Ni-(1-2.9)Sc-(4-9)Y-(0.5-2.9)Zr;
about Al-(6-10)Ni-(1-2.9)Sc-(1-6)Nb-(0.5-2.9)Zr;
about Al-(6-10)Ni-(1-2.9)Sc-(6-12)Hf-(1-6)Nb;
about Al-(6-10)Ni-(1-2.9)Sc-(6-12)Hf-(1-5)V;
about Al-(6-10)Ni-(1-2.9)Sc-(1-6)Nb-(1-5)V;
about Al-(6-10)Ni-(1-2.9)Sc-(0.5-2.9)Zr-(1-5)V;
about Al-8.4Ni-2.15Sc-8.8Gd-1.5Zr;
about Al-8.4Ni-2.15Sc-8.5Gd-2.5Y;
about Al-8.4Ni-2.15Sc-4.1Gd-5.4Y;
about Al-8.4Ni-2.15Sc-11.5Hf-1.5Zr;
about Al-8.4Ni-2.15Sc-9.8Hf-1.5Zr;
about Al-8.4Ni-2.15Sc-9.0Hf-4.5Gd;
about Al-8.4Ni-2.15Sc-8.5Hf-3.0Y;
about Al-8.4Ni-2.15Sc-6.5Y-1.5Zr;
about Al-8.4Ni-2.15Sc-9.5Hf-2.5Nb;
about Al-8.4Ni-2.15Sc-8.0Hf-2.0V;
about Al-8.4Ni-2.15Sc-2.5Nb-3.2V; and
about Al-8.4Ni-2.15Sc-2.5Zr-3.2V, the alloy characterized by at least some fine and coherent Ll 2 Al 3 Sc precipitate dispersoids, that are an ordered face centered cubic structure with scandium atoms located at the corners and aluminum atoms located on the cube faces and that are fine and coherent with the aluminum matrix microstructure and is compacted by vacuum hot pressing at about 343-399° C. to produce an alloy having a tensile strength of at least 118 ksi at 100° C.
26. An aluminum alloy comprising the following composition, in weight percent, about Al-8.4Ni-2.15Sc-8.8Gd-2.5Zr, the alloy characterized by at least some Ll 2 Al 3 Sc fine and coherent precipitate dispersoids, that are an ordered face centered cubic structure with scandium atoms located at the corners and aluminum atoms located on the cube faces and that are fine and coherent with the aluminum matrix microstructure and is compacted by vacuum hot pressing at about 343-399° C. to produce an alloy having a tensile strength of at least 118 ksi at 100° C.
27. The aluminum alloy of claim 26 , wherein the alloy comprises an aluminum solid solution matrix, a plurality of Al 3 (Sc,Gd,Zr) dispersoids having an Ll 2 structure, and a plurality of Al 3 Ni dispersoids.
28. The aluminum alloy of claim 26 , wherein the alloy is substantially free of magnesium.
29. The aluminum alloy of claim 26 , wherein the alloy is capable of being used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.).
30. The aluminum alloy of claim 26 , wherein the alloy further comprises up to about 50 volume percent of a reinforcing second phase.
31. The aluminum alloy of claim 30 , wherein the reinforcing second phase comprises at least one of: an oxide, a carbide, a nitride, an oxynitride, an oxycarbonitride, a silicide, a boride, a ferrous alloy, boron, graphite, tungsten, titanium, SiC, Si 3 N 4 , Al 2 O 3 , B 4 C, Y 2 O 3 , MgAl 2 O 4 , TiC and TiB 2 .
32. The aluminum alloy of claim 26 , wherein the alloy is produced by
a rapid solidification technique utilizing a cooling rate of at least about 10 3 ° C./second or higher.
33. The aluminum alloy of claim 32 , wherein the rapid solidification technique comprises at least the following steps:
creating an ingot having a predetermined composition;
melting the ingot;
atomizing the melted ingot to form a powder;
degassing the powder;
compacting the powder to create a billet; and
hot working the billet into a predetermined form.
34. The aluminum alloy of claim 33 , wherein the creating step occurs in an argon atmosphere at about 1149-1260° C. for about 15-60 minutes.
35. The aluminum alloy of claim 33 , wherein the melting step occurs in an argon atmosphere at about 1316-1427° C. for about 15-60 minutes.
36. The aluminum alloy of claim 33 , wherein the degassing step comprises hot vacuum degassing the powder at about 343-399° C. for about 4-15 hours.
37. The aluminum alloy of claim 33 , wherein the hot working step occurs at about 343-399° C. for about 5-30 minutes.
38. The aluminum alloy of claim 26 , wherein the aluminum alloy is used in at least one of: an aircraft component, a rocket component, and an automobile component.
39. The aluminum alloy of claim 38 , wherein the rocket component comprises at least one of a structural jacket, a turbo pump housing, a turbine rotor, a turbine rotor housing, an impeller, a valve, a valve housing, an injector, a nozzle, a bracket, a duct, a plumbing component, and a structural rocket engine component.
40. The aluminum alloy of claim 38 , wherein the aircraft component comprises at least one of an air inlet housing, a stator assembly, a gearbox, a bearing housing, a carbon seal housing, a dome, a cover, a vane, and a stator.