Method and apparatus for reducing turbine blade tip temperatures
US6422821B1 · kind B1 · utility
33Cited by
3References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 9, 2001 |
| Grant date | Jul 23, 2002 |
| Priority date | — |
| Expiry date | Jan 9, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.