Rotor blade for a compressor or a gas turbine
US7399163B2 · kind B2 · utility
4Cited by
3References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 18, 2005 |
| Grant date | Jul 15, 2008 |
| Priority date | — |
| Expiry date | Jan 12, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.