Gas turbine compressor last stage rotor blades with axial retention
US8727733B2 · kind B2 · utility
5Cited by
1References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 26, 2011 |
| Grant date | May 20, 2014 |
| Priority date | — |
| Expiry date | Aug 3, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/36
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.