OXIDATION RESISTANT PROTECTIVE COATING SYSTEM FOR GAS TURBINE COMPONENTS, AND PROCESS FOR PREPARATION OF COATED COMPONENTS
Assignee
GARRETT CORPORATION, THE
Filed
Jun 29, 1983
Granted
May 10, 1988
Location
PHOENIX AZ US
Abstract
A coating for protecting the surfaces of gas turbine components such as single crystal turbine blades and vanes, wherein the coating has a composition (in weight percent) consisting essentially of chromium, 15-35; aluminum, 8-20; tantalum, 0-10; tantalum plus niobium, 0-10; silicon, 0.1-1.5; hafnium, 0.1-1.5; yttrium, 0-1; cobalt, 0-10; and nickel, balance totalling 100 percent. A preferred coating, which is particularly desirable for use with single-crystal turbine blades and vanes, has a composition consisting essentially of chromium, 17-23; aluminum, 10-13; tantalum plus niobium, 3-8; silicon, 0.1-1.5; hafnium, 0.1-1.5; yttrium, 0-0.8; cobalt, 0-trace; and nickel, balance totalling 100 percent. A process for preparing the coated component is also described.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Jan 16, 1985
Rescinded
Oct 3, 1986
Duration
1 year, 8 months
Inventor
- 1THOMAS E. STRANGMAN
Record Details
- Patent number
- US 4743514
- Application
- 06509284
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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