A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.