A gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, a cooling hole extending from the second surface to the first surface through the first component, and a receiving aperture extending from the second surface to the first surface through the first component; 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; and a passageway portion including a first end, a second end opposite the first end, and an outer surface extending from the second end to the first end, the passageway portion extending from the second surface of the second component through the cooling channel and through the receiving aperture of the first component, wherein the outer surface of the passageway portion and the receiving aperture of the first component define a gap therebetween, the gap fluidly connecting airflow in an airflow path proximate the second surface of the first component to the cooling channel, wherein the gap is configured to direct the airflow along the outer surface of the passageway portion and the outer surface of the passageway portion is shaped to redirect the airflow in a lateral direction parallel to the second surface of the second component such that a lateral airflow is generated in the cooling channel, characterized in that the gas turbine engine component assembly further comprises an intermittent circumferential ring located in the cooling channel and partially circumferentially surrounding the outer surface of the passageway portion, wherein the intermittent circumferential ring is configured to direct the lateral airflow in a selected lateral direction. a first component having a first surface, a second surface opposite the first surface, a cooling hole extending from the second surface to the first surface through the first component, and a receiving aperture extending from the second surface to the first surface through the first component; 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; and a passageway portion including a first end, a second end opposite the first end, and an outer surface extending from the second end to the first end, the passageway portion extending from the second surface of the second component through the cooling channel and through the receiving aperture of the first component, wherein the outer surface of the passageway portion and the receiving aperture of the first component define a gap therebetween, the gap fluidly connecting airflow in an airflow path proximate the second surface of the first component to the cooling channel, wherein the gap is configured to direct the airflow along the outer surface of the passageway portion and the outer surface of the passageway portion is shaped to redirect the airflow in a lateral direction parallel to the second surface of the second component such that a lateral airflow is generated in the cooling channel, characterized in that the gas turbine engine component assembly further comprises an intermittent circumferential ring located in the cooling channel and partially circumferentially surrounding the outer surface of the passageway portion, wherein the intermittent circumferential ring is configured to direct the lateral airflow in a selected lateral direction.