Method of making a protective coating forming a thermal barrier with a bonding underlayer on a superalloy substrate, and a part obtained thereby
View Patent ↗A protective coating forming a thermal barrier is made on a superalloy metal substrate by forming a bonding underlayer on the substrate, the bonding underlayer being constituted by an intermetallic compound comprising at least aluminum and a metal from the platinum group, and by forming a ceramic outer layer which is anchored on a film of alumina present on the surface of the bonding underlayer. The bonding underlayer preferably has a thickness of less than 50 μm and is made by using physical vapor deposition, e.g. by cathode sputtering, to deposit a plurality of individual layers alternately of aluminum and of a metal from the platinum group, and by causing the metals in the resulting layers to react together exothermally.
1. A gas turbine part comprising a superalloy metal substrate, a bonding underlayer formed on the substrate and made of an intermetallic compound comprising aluminum and a metal from the platinum group, an adhesive film of alumina formed on a surface of the bonding underlayer, and an outer coating of ceramic anchored on the alumina film, wherein the bonding underlayer has a thickness of less than 50 μm, the bonding underlayer is substantially free from elements diffused from the substrate, and the bonding underlayer presents phases of different compositions.
2. A gas turbine part according to claim 1 , wherein the bonding underlayer has thickness lying in the range 3 μm to 30 μm.
3. A gas turbine part according to claim 1 , wherein the bonding underlayer further comprises at least one reactive element selected from the group constituted by yttrium, zirconium, hafnium, and the lanthanides.
4. A gas turbine part according to claim 1 , wherein the bonding underlayer further comprises at least one additional metal other than the platinum and the aluminum.
5. A gas turbine part according to claim 1 , wherein the bonding underlayer presents a structure that is substantially homogenous.
6. A gas turbine part according to claim 1 , where the bonding underlayer presents a structure that is laminated.
7. A gas turbine part comprising a superalloy metal substrate, a bonding underlayer formed on the substrate and made of an intermetallic compound comprising aluminum and a metal from the platinum group, an adhesive film of alumina formed on a surface of the bonding underlayer, and an outer coating of ceramic anchored on the alumina film,
wherein the bonding underlayer has a thickness of less than 50 μm,
wherein the bonding underlayer is substantially free from elements diffused from the substrate, and
wherein the bonding underlayer is of a composition that varies in a controlled manner within its thickness.
8. A gas turbine part according to claim 7 , wherein the bonding underlayer has a thickness lying in the range 3 μm to 30 μm.
9. A gas turbine part according to claim 7 , wherein the bonding underlayer further comprises at least one reactive element selected from the group constituted by yttrium, zirconium, hafnium, and the lanthanides.
10. A gas turbine part according to claim 7 , wherein the bonding underlayer further comprises at least one additional metal other than the platinum and the aluminum.
11. A gas turbine part according to claim 7 , wherein the bonding underlayer presents a structure that is substantially homogenous.
12. A gas turbine part according to claim 7 , where the bonding underlayer presents a structure that is laminated.
13. A gas turbine part comprising a superalloy metal substrate, a bonding underlayer formed on the substrate and made of an intermetallic compound comprising aluminum and a metal from the platinum group, an adhesive film of alumina formed on a surface of the bonding underlayer, and an outer coating of ceramic anchored on the alumina film,
wherein the bonding underlayer has a thickness of less than 50 μm,
wherein the bonding underlayer is substantially free from elements diffused from the substrate, and
wherein the bonding underlayer presents a plurality of distinct superposed stages or phases.
14. A gas turbine part according to claim 13 , wherein the bonding underlayer has a thickness lying in the range 3 μm to 30 μm.
15. A gas turbine part according to claim 13 , wherein the bonding underlayer further comprises at least one reactive element selected from the group constituted by yttrium, zirconium, hafnium, and the lanthanides.
16. A gas turbine part according to claim 13 , wherein the bonding underlayer further comprises at least one additional metal other than the platinum and the aluminum.
17. A gas turbine part according to claim 13 , wherein the bonding underlayer presents a structure that is substantially homogenous.
18. A gas turbine part according to claim 13 , where the bonding underlayer presents a structure that is laminated.
19. A gas turbine part according to claim 13 , wherein the bonding underlayer is of a composition that varies in controlled manner within its thickness.
20. A gas turbine part according to claim 13 , wherein the bonding underlayer presents phases of different compositions.