Rotor blade for a gas turbine engine
US4120607A · kind A · utility
9Cited by
5References
7Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Mar 16, 1977 |
| Grant date | Oct 17, 1978 |
| Priority date | — |
| Expiry date | Mar 16, 1997 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2260/3011
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine engine comprises an aerofoil, an inner platform and a root portion. In order to restrain the movement of the blade should it become detached from its rotor, the platform has an indentation in that edge adjacent the convex flank. If the blade detaches, this indentation engages with the leading edge of the next adjacent blade in the row, tending to restrict motion of the detached blade to the radial plane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.