Combustion turbine component having rare earth NiCoCrAl coating and associated methods
View Patent ↗A combustion turbine component ( 10 ) includes a combustion turbine component substrate ( 16 ) and an alloy coating ( 14 ) on the combustion turbine component substrate. The alloy coating ( 14 ) includes a first amount, by weight percent, of nickel (Ni) and a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount. The alloy coating also includes chromium (Cr), aluminum (Al), and yttrium (Y). The alloy coating further includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). Moreover, the alloy coating includes at least one rare earth element, and an oxide of at least one of the yttrium the at least one rare earth element.
1. A combustion turbine component comprising:
a combustion turbine component substrate; and
an alloy coating on said combustion turbine component substrate comprising
a first amount, by weight percent, of nickel (Ni), a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount,
chromium (Cr), aluminum (Al), yttrium (Y), rhenium (Re),
at least one of titanium (Ti), tantalum (Ta), and tungsten (W),
at least one additional rare earth element, and
an oxide of at least one of the yttrium and the at least one additional rare earth element.
2. The combustion turbine component of claim 1 , wherein said alloy coating comprises, by percentage of weight, 20% to 30% of Co; 12% to 22% of Cr; and 8% to 15% of Al.
3. The combustion turbine component of claim 2 , wherein said alloy coating further comprises, by percentage of weight, 0.05% to 5% of Y; 0.4% to 4%, total, of Re and at least one of Ti, Ta, and W; and 0.1% to 5%, total, of at least one additional rare earth element; and a balance of Ni and O.
4. The combustion turbine component of claim 1 , wherein said alloy coating comprises, by percentage of weight, 23% to 27% of Co; 14% to 19% of Cr; and 9% to 12% of Al.
5. The combustion turbine component of claim 4 , wherein said alloy coating further comprises, by percentage of weight, 0.1% to 1% of Y; 0.5% to 3%, total, of Re and at least one of Ti, Ta, and W; 0.5% to 3%, total, of at least one additional rare earth element; and a balance of Ni and O.
6. The combustion turbine component of claim 1 , further comprising a thermal barrier coating on said alloy coating.
7. The combustion turbine component of claim 1 , wherein said at least one additional rare earth element comprises at least one of lanthanum (La), cerium (Ce), praseodymium (Pr), neodymium (Nd), promethium (Pm), samarium (Sm), europium (Eu), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm), ytterbium (Yb), lutetium (Lu).
8. A combustion turbine component comprising:
a metallic combustion turbine component substrate; and
an alloy coating on said metallic combustion turbine component substrate comprising, by weight percent,
20% to 30% of Co,
12% to 22% of Cr,
8% to 15% of Al,
0.05% to 5% of Y,
0.4% to 4%, total, of Re and at least one of Ti, Ta, and W,
0.1% to 5%, total, of at least one additional rare earth element, and
a balance of Ni and O.
9. The combustion turbine component of claim 8 , wherein said alloy coating comprises, by percentage of weight, 23% to 27% of Co; 14% to 19% of Cr; 9% to 12% of Al; 0.1% to 1% of Y; 0.5% to 3%, total, of Re and at least one of Ti, Ta, and W; 0.5% to 3%, total, of at least one additional rare earth element; and a balance of Ni and O.
10. The combustion turbine component of claim 8 , further comprising a thermal barrier coating on said alloy coating.
11. The combustion turbine component of claim 8 , wherein said at least one additional rare earth element comprises at least one of lanthanum (La), cerium (Ce), praseodymium (Pr), neodymium (Nd), promethium (Pm), samarium (Sm), europium (Eu), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm), ytterbium (Yb), lutetium (Lu).
12. A method of making a combustion turbine component comprising:
forming a combustion turbine component substrate;
applying an alloy coating on the combustion turbine component substrate, the alloy coating comprising
a first amount, by weight percent, of nickel (Ni), a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount,
chromium (Cr), aluminum (Al), yttrium (Y), rhenium (Re),
at least one of titanium (Ti), tantalum (Ta), and tungsten (W),
at least one additional rare earth element, and
an oxide of at least one of the yttrium the at least one additional rare earth element.
13. The method of claim 12 , wherein the alloy coating comprises, by percentage of weight, 20% to 30% of Co; 12% to 22% of Cr; and 8% to 15% of Al.
14. The method of claim 13 , wherein the alloy coating further comprises, by percentage of weight, 0.05% to 5% of Y; 0.4% to 4%, total, of Re and at least one additional of Ti, Ta, and W; 0.1% to 5%, total, of at least one additional rare earth element; and a balance of Ni and O.
15. The method of claim 12 , wherein the alloy coating comprises, by percentage of weight, 23% to 27% of Co; 14% to 19% of Cr; and 9% to 12% of Al.
16. The method of claim 15 , wherein the alloy coating further comprises, by percentage of weight, 0.1% to 1% of Y; 0.5% to 3%, total, of Re and at least one of Ti, Ta, and W; 0.5% to 3%, total, of at least one additional rare earth element; and a balance of Ni and O.
17. The method of claim 12 , wherein applying the alloy coating on the combustion turbine component substrate comprises:
atomizing a metallic liquid in an atmosphere to form a metallic powder;
milling the metallic powder to form a nanosized metallic powder; and
thermal spraying the nanosized metallic powder onto the combustion turbine component substrate.
18. The method of claim 17 , wherein the atmosphere comprises an oxidizing atmosphere.
19. The method of claim 17 , further comprising forming a thermal barrier coating on the combustion turbine component substrate after thermal spraying.
20. The method of claim 12 , wherein applying the alloy coating on the combustion turbine component substrate comprises:
atomizing a metallic liquid to form a metallic powder;
performing a series of heat treating steps on the metallic powder comprising
a first heat treating step performed in an oxidizing atmosphere,
a second heat treating step performed in an inert atmosphere, and
a third heat treating step performed in a reducing atmosphere to form a metallic power having an increased proportion of rare-earth oxides compared to non rare-earth oxides; and
thermal spraying the metallic powder having an increased proportion of rare-earth oxides compared to non rare-earth oxides onto the combustion turbine component substrate.
21. The method of claim 20 , wherein the first heat treating step is performed for a first period of time; and wherein the second heat treating step is performed for a second period of time; and wherein the second period of time is greater than the first period of time.
22. The method of claim 20 , further comprising forming a thermal barrier coating after the thermal spraying.
23. A method of making a combustion turbine component comprising:
forming a combustion turbine component substrate;
applying an alloy coating on the combustion turbine component substrate by at least
atomizing a metallic liquid to form a metallic powder;
performing a series of heat treating steps on the metallic powder comprising
a first heat treating step performed in an oxidizing atmosphere,
a second heat treating step performed in an inert atmosphere, and
a third heat treating step performed in a reducing atmosphere to form a metallic power having an increased proportion of rare-earth oxides compared to non rare-earth oxides; and
thermal spraying the metallic powder having an increased proportion of rare-earth oxides compared to non rare-earth oxides onto the combustion turbine component substrate,
the alloy coating comprising
a first amount, by weight percent, of nickel (Ni), a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount,
chromium (Cr), aluminum (Al), yttrium (Y),
at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re),
at least one additional rare earth element, and
an oxide of at least one of the yttrium the at least one additional rare earth element.
24. The method of claim 23 , wherein the first heat treating step is performed for a first period of time; and wherein the second heat treating step is performed for a second period of time; and wherein the second period of time is greater than the first period of time.
25. The method of claim 24 , further comprising forming a thermal barrier coating after the thermal spraying.
26. The method of claim 23 , further comprising milling the metallic powder to form a nanosized metallic powder after atomizing the metallic liquid; wherein the series of heat treating steps are performed on the nanosized metallic powder; and wherein the nanosized metallic powder is thermal sprayed.
27. The method of claim 23 , wherein the metallic powder is atomized in an oxidizing atmosphere.