Methods and apparatus for reducing vibrations induced to compressor airfoils
US6905309B2 · kind B2 · utility
13Cited by
19References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 28, 2003 |
| Grant date | Jun 14, 2005 |
| Priority date | — |
| Expiry date | Oct 2, 2023 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49318
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.