Damping system for an expendable gas turbine engine
US6942451B1 · kind B1 · utility
19Cited by
36References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 3, 2003 |
| Grant date | Sep 13, 2005 |
| Priority date | — |
| Expiry date | Nov 5, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16C2360/23
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
A dampening system for a miniature high-speed turbojet engine provides single or multiple resilient mountings for forward and aft bearings which mount a rotor shaft. The self-induced first engine order of the rotating rotor shaft is transmitted through the forward and aft bearing and is then absorbed in the resilient mountings.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.