A gas turbine engine component assembly, comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of 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; characterized in that the assembly further comprises: a lateral flow injection feature (500a-d) formed in the first component, the lateral flow injection feature fluidly connecting airflow exiting the first fairing to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway (506a-d) and into the cooling channel in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel; optionally wherein the passageway further comprises: a guide wall (508a-d) oriented at a selected angle (α1) configured to direct airflow in the lateral direction parallel to the second surface of the second component such that the cross flow is generated in the cooling channel, wherein: the lateral flow injection feature (500a-d) is fluidly connected to the airflow exiting the first fairing through an inlet (502a-d) oriented parallel with the airflow exiting the first fairing. a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of 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; characterized in that the assembly further comprises: a lateral flow injection feature (500a-d) formed in the first component, the lateral flow injection feature fluidly connecting airflow exiting the first fairing to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway (506a-d) and into the cooling channel in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel; optionally wherein the passageway further comprises: a guide wall (508a-d) oriented at a selected angle (α1) configured to direct airflow in the lateral direction parallel to the second surface of the second component such that the cross flow is generated in the cooling channel, wherein: the lateral flow injection feature (500a-d) is fluidly connected to the airflow exiting the first fairing through an inlet (502a-d) oriented parallel with the airflow exiting the first fairing.