Turbine or compressor stage for a turbojet
US8192149B2 · kind B2 · utility
4Cited by
6References
5Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 7, 2008 |
| Grant date | Jun 5, 2012 |
| Priority date | — |
| Expiry date | Oct 14, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T24/44744
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbojet turbine or compressor stage is disclosed. The stage includes at least one rotor disk mounted inside a sectorized ring supported by a casing and including a circumferential flange radially clamped on an annular rail of the casing by a substantially C-shaped cross-section annular locking device which is axially engaged on the casing rail and on the flange of the ring. A substantially cylindrical heat shielding foil is interposed between the ring and the device. The foil or the device includes at least one extra thickness which respectively bears on the device, or the foil, to radially immobilize this foil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.