Distortion control for laser shock peened gas turbine engine compressor blade edges
US5531570A · kind A · utility
49Cited by
20References
24Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 6, 1995 |
| Grant date | Jul 2, 1996 |
| Priority date | — |
| Expiry date | Mar 6, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A method for counteracting distortion of the airfoil caused by laser shock peening a gas turbine engine compressor metallic airfoil along its leading and/or trailing edge to form laser shock peened surfaces extending radially along at least a portion of the edges with a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surfaces.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.