Thermal barrier coatings including CMAS-resistant thermal barrier coating layers
An article may include a superalloy substrate and a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer overlying the superalloy substrate. In some embodiments, the CMAS-resistant TBC layer includes between about 50 wt. % and about 90 wt. % of a TBC composition and between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition. In some examples, the TBC composition includes at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides. In some examples, the CMAS-resistant composition includes alumina, silica, and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu.
1. An article comprising:
a superalloy substrate; and
a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer overlying the superalloy substrate, wherein the CMAS-resistant TBC layer comprises:
between about 50 wt. % and about 90 wt. % of a TBC composition, wherein the TBC composition comprises at least one of hafnia or zirconia stabilized with the following rare earth oxides:
between about 20 mol. % and about 40 mol. % ytterbia,
between about 10 mol. % and about 20 mol. % samaria, and
between about 10 mol. % and about 20 mol. % of at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia, wherein the TBC composition comprises more ytterbia than samaria and more ytterbia than the at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia, and
between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition, wherein the CMAS-resistant composition comprises alumina, silica, and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu.
2. The article of claim 1 , wherein the CMAS-resistant TBC layer further comprises at least one of tantalum oxide, titanium oxide, hafnium silicate, an alkali oxide, or an alkali earth oxide.
3. The article claim 1 , wherein the CMAS-resistant TBC layer comprises a thickness of between about 0.5 mils and about 20 mils.
4. The article of claim 1 , wherein the TBC composition comprises a first TBC composition, further comprising
a layer comprising a second TBC composition overlying the superalloy substrate, wherein the CMAS-resistant TBC layer overlies the layer comprising the TBC composition.
5. The article of claim 4 , wherein the second TBC composition comprises hafnia stabilized with ytterbia, samaria, and at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia.
6. The article of claim 4 , further comprising a bond layer overlying the superalloy substrate, and wherein the layer comprising the first TBC composition overlies the bond layer.
7. The article of claim 4 , wherein the layer comprising the second TBC composition comprises a first layer, further comprising a second layer comprising a third TBC composition overlying the CMAS-resistant TBC layer, wherein the third TBC composition comprises at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides.
8. The article of claim 7 , wherein the first layer comprises a thickness of between about 0.5 mils and about 20 mils, wherein the CMAS-resistant TBC layer comprises a thickness of between about 0.5 mils and about 20 mils, and wherein the second layer comprises a thickness of between about 0.5 mils and about 20 mils.
9. A method comprising:
forming a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer over a superalloy substrate, wherein the CMAS-resistant TBC layer comprises:
between about 50 wt. % and about 90 wt. % of a TBC composition, wherein the TBC composition comprises at least one of hafnia or zirconia stabilized with the following rare earth oxides:
between about 20 mol. % and about 40 mol. % ytterbia,
between about 10 mol. % and about 20 mol. % samaria, and
between about 10 mol. % and about 20 mol. % of at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia, wherein the TBC composition comprises more ytterbia than samaria and more ytterbia than the at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia, and
between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition, wherein the CMAS-resistant composition comprises alumina, silica and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu.
10. The method of claim 9 , wherein forming the CMAS-resistant TBC layer over the superalloy substrate comprises depositing the CMAS-resistant TBC layer over the superalloy substrate using at least one of chemical vapor deposition, plasma spraying, physical vapor deposition, or a slurry process.
11. The method of claim 9 , wherein the thermal barrier coating (TBC) composition comprises a first TBC composition, further comprising:
forming a layer comprising a second TBC composition over a superalloy substrate, wherein the second TBC composition comprises at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides, and
wherein forming the calcia-magnesia-alumina-silicate (CMAS)-resistant TBC layer over the superalloy substrate comprises forming the CMAS-resistant TBC layer over the layer comprising the second TBC composition.
12. The method of claim 11 , further comprising:
forming a layer comprising a third TBC composition over the CMAS-resistant TBC layer, wherein the third TBC composition comprises at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides.