Methods and apparatus to reduce turbine engine nozzle basesheet stresses
US7302793B2 · kind B2 · utility
1Cited by
16References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 29, 2003 |
| Grant date | Dec 4, 2007 |
| Priority date | — |
| Expiry date | Mar 14, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a downstream side, forming at least one relief cut in the basesheet that extends at least partially across the basesheet from at least one of the circumferentially-spaced sides, and coupling the basesheet to the backbone assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.