Laser shock peened gas turbine engine fan blade edges
US5591009A · kind A · utility
58Cited by
17References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 17, 1995 |
| Grant date | Jan 7, 1997 |
| Priority date | — |
| Expiry date | Jan 17, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S148/903
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
Gas turbine engine fan blade with a metallic airfoil having a leading edge, a trailing edge, and a radially outer tip, and at least one laser shock peened surface located along the leading edge with a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.