Fan decoupler system for a gas turbine engine
US6240719A · kind A · utility
56Cited by
8References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 9, 1998 |
| Grant date | Jun 5, 2001 |
| Priority date | — |
| Expiry date | Dec 9, 2018 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2260/3011
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A support structure for a gas turbine engine includes a support arm (214, 216) extending between a low pressure shaft (202) and a rotor. The support arm includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap (A) between a portion of the low pressure shaft and the stub shaft permits movement of the low pressure shaft after fuse failure. A radial gap (B) between the stub shaft (270) and the low pressure shaft (202) allows radial deflection of the low pressure rotor system after fuse failure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.