Flexible seal for gas turbine engine system
US9228533B2 · kind B2 · utility
2Cited by
17References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2007 |
| Grant date | Jan 5, 2016 |
| Priority date | — |
| Expiry date | Nov 4, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49297
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.