Rare-earth doped thermal barrier coating bond coat for thermally grown oxide luminescence sensing
A thermal barrier coated component, such as a turbine blade formed from a superalloy substrate, includes a thermal barrier coating applied onto the substrate. A metallic bond coat layer is on the substrate and includes rare-earth luminescent dopants. A ceramic top coat layer is on the bond coat layer. A temperature sensing thermally grown oxide (TGO) layer is formed at the interface of the bond coat layer and ceramic top coat layer. The temperature sensing TGO layer includes grown rare-earth luminescent ions migrated from the metallic bond coat layer in an amount sufficient to enable luminescence sensing of the TGO layer for real-time phosphor thermometry temperature measurements at the TGO layer.
1. A thermal barrier coated component, comprising:
a substrate;
a thermal barrier coating applied onto the substrate, said thermal barrier coating comprising,
a metallic bond coat layer on the substrate, said metallic bond coat layer including about 96 to 98 percent of NiCoCrAlY and about 2.0 to about 4.0 percent of rare-earth luminescent dopants selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium;
a ceramic top coat layer on the bond coat layer; and
a heat aged, high temperature sensing thermally grown oxide (TGO) layer formed at the interface of the bond coat layer and ceramic top coat layer, said high temperature sensing TGO layer includes grown rare-earth luminescent ions selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium and migrated during heat aging from the metallic bond coat layer in an amount sufficient to enable high temperature luminescence sensing of the TGO layer for real-time phosphor thermometry high temperature measurements up to about 1,100° C. at the TGO layer, wherein said TGO layer comprises about 1.7 to 2.0 weight percent of nickel, about 0.67 to 0.82 weight percent of chromium, about 52.7 to 64.4 weight percent of aluminum, about 35.0 to about 42.7 weight percent of oxygen, and no more than about 0.1 weight percent of the rare-earth dopants selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium.
2. The thermal barrier coated component of claim 1 , wherein said ceramic top coat layer comprises a ytrria-stabilized zirconia (YSZ) barrier top coat layer on the bond coat layer.
3. The thermal barrier coated component of claim 1 , wherein said substrate comprises a turbine component or an engine exhaust component.
4. The thermal barrier coated component of claim 1 , wherein said bond coat layer is about 50 to 200 micrometers and said ceramic top coat layer is about 50 to 300 micrometers.
5. A thermal barrier coated component, comprising:
a superalloy substrate;
a thermal barrier coating applied onto the superalloy substrate, said thermal barrier coating comprising,
a metallic bond coat layer on the superalloy substrate, said metallic bond coat layer including about 96 to 98 percent of NiCoCrAlY and about 2.0 to about 4.0 percent of rare-earth luminescent dopants selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium;
a ytrria-stabilized zirconia (YSZ) barrier top coat layer on the bond coat layer; and
a heat aged, high temperature sensing thermally grown oxide (TGO) layer formed at the interface of the bond coat layer and YSZ barrier top coat layer, said high temperature sensing TGO layer includes grown rare-earth luminescent ions selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium, and migrated during heat aging from the metallic bond coat layer in an amount sufficient to enable high temperature luminescence sensing of the TGO layer for real-time phosphor thermometry high temperature measurements up to about 1,100° C. at the TGO layer, wherein said TGO layer comprises about 1.7 to 2.0 weight percent of nickel, about 0.67 to 0.82 weight percent of chromium, about 52.7 to 64.4 weight percent of aluminum, about 35.0 to about 42.7 weight percent of oxygen, and no more than about 0.1 weight percent of the rare-earth dopants selected from the group consisting of samarium, erbium, europium, dysprosium, praseodymium, and terbium.
6. The thermal barrier coated component of claim 5 , wherein said superalloy substrate comprises a turbine component or an engine exhaust component.
7. The thermal barrier coated component of claim 5 , wherein said bond coat layer is about 50 to 200 micrometers and said ceramic top coat layer is about 50 to 300 micrometers.