Gas turbine engine rotor tie shaft arrangement
US8794923B2 · kind B2 · utility
7Cited by
5References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 29, 2010 |
| Grant date | Aug 5, 2014 |
| Priority date | — |
| Expiry date | Jul 12, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Independent axial preloading of compressor and turbine disks in a gas turbine engine rotor is achieved by a dual tie shaft arrangement wherein a forward tie shaft engages forward and aft portions of a compressor hub within which the compressor disks are disposed to axially and compressively preload the compressor disks between the forward and aft portions of the compressor hub. An independent tie shaft engages an aft portion of a turbine hub within which turbine disks are disposed and an aft portion of the compressor hub to axially and compressively preload the turbine disks between the turbine and compressor hubs.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.