Claims
- 1. An air cooled gas turbine component which comprises:
- a. a superalloy substrate having internal cooling passages for the flow of cooling air,
- b. a thermal barrier coating on said substrate, comprising:
- at least 10 layers of ceramic, each layer being from about 10 angstroms to 10,000 angstroms in thickness, each layer being separated from adjacent layers by a stable interface with the total thickness of the coating being at least 1 mil (25 microns).
- 2. A component as in claim 1 wherein at least 50% of the layers are based on a material selected from the group consisting of alumina, ceria, and zirconia.
- 3. A component as in claim 1 wherein at least 20% of the layers have a microstructure which is partially amorphous.
- 4. A component as in claim 1 wherein the substrate is one which contains sufficient aluminum so that it forms an alumina layer upon exposure to oxygen at elevated temperatures.
- 5. A component as in claim 1 having at least 10 boundaries separating thin ceramic layers.
CROSS REFERENCE TO RELATED APPLICATIONS
This is a Continuation Application of prior application Ser. No. 08/321,052 filed on Oct. 5, 1994, now abandoned.
US Referenced Citations (6)
Continuations (1)
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Number |
Date |
Country |
Parent |
321052 |
Oct 1994 |
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