Methods and apparatus for improving engine operation
US6568909B2 · kind B2 · utility
8Cited by
5References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 26, 2001 |
| Grant date | May 27, 2003 |
| Priority date | — |
| Expiry date | Sep 26, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49336
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.