GAS TURBINE ENGINE COMBUSTOR CIRCUMFERENTIAL ACOUSTIC REDUCTION USING FLAME TEMPERATURE NONUNIFORMITIES

摘要

A gas turbine engine combustor includes an annulus with one or more circularrows of burners and a means forproviding a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation.The number of the flame temperature nonunif ormities being equal to acircumferential acoustic mode to be attenuated in thecom-bustor (i.e three, five, or seven). Fuel lines and/or water lines insupply communication with the burners and metering orifices in aportion of the fuel lines and/or the water lines may be used to produce theflame temperature nonunif ormities. The annulus of theburners may have an equal number of equiangular spaced apart first and secondarcuate segments of the burners and a means foroperating the burners in the first segments and operating the burners in thesecond segments at different first and second flametemperatures respectively.