COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE

摘要

A combustor (12) for a gas turbine engine includes a pilot fuel injector (38) and a plurality of circumferentially located main injectors (36) for injecting fuel and air into a combustion chamber defined by a liner wall (34) of a combustor basket. A combustion zone (16) is located in the combustion chamber where the fuel and air are ignited to produce hot combustion gases. A plurality of vortex generators (42) are located in circumferentially spaced relation on the liner wall and comprise structures extending radially inward into the combustion chamber to create vortices at predetermined circumferential locations downstream from where the fuel and air are ignited to effect a reduction in emissions of the combustion gases.