Can combustor for a gas turbine engine
US6772583B2 · kind B2 · utility
91Cited by
24References
18Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 11, 2002 |
| Grant date | Aug 10, 2004 |
| Priority date | — |
| Expiry date | Oct 2, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23C2201/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine (10) includes a plurality of can combustors (19). Each can combustor includes a first stage of burners (46) located at a first radius about the combustor centerline (42) and a second stage of burners (50) located at a second radius greater than the first radius. The second stage of burners may be clocked to an angular position that is not midway between respective neighboring burners of the first stage. Combustion instabilities may be controlled by exploiting variations in combustion parameters created by differential fueling of the two stages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.