Gas turbine engine rotor construction
US8840373B2 · kind B2 · utility
0Cited by
6References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 3, 2011 |
| Grant date | Sep 23, 2014 |
| Priority date | — |
| Expiry date | Mar 1, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine rotor is provided with a longitudinal stack of blade supporting disks each including a medial web and a radially outer rim. The disks are spaced from one another by axial gaps. The disks include recesses in the forward and aft major surfaces thereof proximal to the juncture of the webs and rims thereof. Annular spacers received with the recesses in the disks span the axial gaps and provide a load path for the axial compressive preloading of the disks and the transmission of torque along the disk stack.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.