Turbine blade platform undercut
US8550783B2 · kind B2 · utility
3Cited by
16References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 1, 2011 |
| Grant date | Oct 8, 2013 |
| Priority date | — |
| Expiry date | Apr 4, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/114
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.