Patent ID: 8613197
Filing Date: 2013-12-24
Classification: F02C,F05D,F23N,F23R

Abstract:
1. A combustor cap and fuel nozzle assembly for a turbine engine, comprising: a combustor cap; and a plurality of fuel nozzles mounted on the combustor cap, wherein a plurality of fuel nozzles includes a first fuel circuit that delivers fuel from only a central portion of a downstream end of the fuel nozzle and a second fuel circuit that delivers fuel from only an outer annular portion of the downstream end of the fuel nozzle, and wherein a flow of fuel through the first and second fuel circuits is independently controllable, wherein a first one of the multiple fuel nozzles with the first and second fuel circuits is located at a center of the combustor cap, wherein a first subset of the remaining fuel nozzles includes the first and second fuel circuits, the first subset being arranged symmetrically around the central fuel nozzle, and wherein a second subset of the remaining fuel nozzles have only a single fuel circuit, the second subset also being arranged symmetrically around the central fuel nozzle.