Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US8631656B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2008 |
| Grant date | Jan 21, 2014 |
| Priority date | — |
| Expiry date | Dec 4, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00014
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.