Gas turbine engine nozzle liner with thermally compliant attachment brackets
US7770399B2 · kind B2 · utility
4Cited by
4References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2006 |
| Grant date | Aug 10, 2010 |
| Priority date | — |
| Expiry date | Jun 10, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/1207
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced feet with an intermediate notch spaced away from the liner. In this manner, a temperature gradient along the liner can be easily compensated at the connection of the bracket to the liner by adjustment within the notch. In other features, the bracket is riveted to the liner, providing further resistance to thermal expansion due to temperature gradiations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.