Laser shock peening integrally bladed rotor blade edges
US6541733B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 29, 2001 |
| Grant date | Apr 1, 2003 |
| Priority date | — |
| Expiry date | Feb 20, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A method for laser shock peening rotor blade leading and trailing edges of gas turbine engine integrally bladed rotors and disks that are not blocked by other rows of blades. The method includes continuously firing a stationary laser beam, which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges of the blade, with the laser beam aimed at an oblique angle with respect to a surface of the edge such that laser pulses form overlapping elliptical shaped laser spots. In the exemplary embodiment of the invention, the elliptical shaped laser spots have an overlap of about 50% and are on the order of 11.7 mm by 4 mm in diameter. Another method is for laser shock peening rotor blade leading and trailing edges of gas turbine engine integrally bladed rotors and disks that are blocked by other rows of blades. The method includes continuously firing the stationary laser beam, which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges of the blade, with the laser beam compoundly angled such that it is aimed at a first oblique angle with respect to a surface of the edge and at a second…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.