THERMAL BARRIER COATING SYSTEM FOR SUPERALLOY COMPONENTS
Assignee
GARRETT CORPORATION, THE
Filed
Apr 25, 1984
Granted
May 7, 1996
Location
PHOENIX AZ US
Abstract
An improvement in a thermal barrier coating for superalloy turbine engine components subjected to high operating temperatures, such as turbine airfoils, e.g., vanes and blades, is disclosed which eliminates the expensive MCrAlY oxidation resistant bond coating underlayer for a columnar grained ceramic thermal barrier coating. In accordance with my present invention, a relatively low cost thermal barrier coating system for superalloy turbine components is provided which utilizes a diffusion aluminide coating layer as the oxidation resistant bonding surface for the columnar grained ceramic insulating coating.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Sep 14, 1984
Rescinded
Feb 22, 1994
Duration
9 years, 5 months
Inventor
- 1THOMAS E. STRANGMAN
Record Details
- Patent number
- US 5514482
- Application
- 06603811
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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