Gas turbine engine rotor blades
US6517319B2 · kind B2 · utility
9Cited by
4References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 18, 2001 |
| Grant date | Feb 11, 2003 |
| Priority date | — |
| Expiry date | Sep 18, 2021 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC21D7/06
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A component for a gas turbine engine having at least one surface, that has been treated by ultrasonic hammer peening so as to provide a region of deep compressive residual stress in the treated region.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.