Combustion liner for a gas turbine engine including heat transfer columns to increase cooling of a hula seal at the transition duct region
US8245514B2 · kind B2 · utility
3Cited by
23References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 10, 2008 |
| Grant date | Aug 21, 2012 |
| Priority date | — |
| Expiry date | Feb 14, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00012
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move relative to the transition duct. The combustion liner is formed with heat transfer columns adjacent the downstream end, and radially inwardly of the hula seal.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.