Turbomachine blade that is cast with a local fattening of the section of the airfoil
US8128375B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 12, 2008 |
| Grant date | Mar 6, 2012 |
| Priority date | — |
| Expiry date | Aug 19, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/607
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.