COMBUSTOR HOLE ARRANGEMENT FOR GAS TURBINE ENGINE

摘要

A combustor liner (24) for a gas turbine is provided. The combustor liner comprises a wall (62, 64) and a plurality of airflow injection holes (42) in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes (42a) and at least one non-circular second airflow injection hole (42b).