System for directing airflow into a combustor

A system, comprising;

• a turbine engine, comprising:
• a compressor and a turbine having an axis of rotation;
• and
• a combustor coupled to the compressor and the turbine, wherein the combustor comprises:
• a combustion liner disposed about a combustion region;
• a sleeve disposed about the combustion liner, wherein the combustion liner and the sleeve define an airflow passage circumferentially about the liner;
• and
• a plurality of axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor, wherein the plurality of axial injectors is configured to increases an effective area for airflow injection further away from the axis of rotation.