A gas turbine engine component assembly comprising: a first component having a first surface, a second surface opposite the first surface, a first cooling hole located in a first section of the first component extending from the second surface to first surface, and a second cooling hole located in a second section of the first component extending from the second surface to first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; wherein the first cooling hole is configured to direct at least one of the airflow and the particulate to impinge upon the second surface of the second component at first directional flow angle.