Blade anchored securely in radial translation, propeller, turbine engine and aircraft
US9840921B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 14, 2015 |
| Grant date | Dec 12, 2017 |
| Priority date | — |
| Expiry date | Feb 18, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49337
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade includes an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (23). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion (21) to pass through. The base of the aerodynamic portion (21) has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion (21) in the blade shank (20).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.