Patent ID: 8631656
Filing Date: 2014-01-21
Classification: F23R

Abstract:
1. A gas turbine engine combustor comprising: annular outer and inner liners and a domed end radially extending therebetween, the outer and inner liners spaced radially inwardly of an outer combustor casing, an annulus of burners supported by the domed end, the annulus including one or more circular rows of the burners, the annulus of the burners comprising an equal number of equiangular spaced apart first and second arcuate segments of the burners, fuel lines in fuel supply communication with and extending to the burners, means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation by flowing fuel to and combusting the fuel in all of the burners and restricting fuel flow to one or more restricted burners of the burners in each of the first arcuate segments of the burners, and the means including flow restrictors having fixed flow area metering orifices with unobstructed fixed flow areas metering orifices in the fuel lines to the one or more of the burners in each of the first arcuate segments of the burners.