A gas turbine engine component assembly, comprising: a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component, wherein the first end of the threaded stud is located proximate to the second surface of the first component; a second component having a first surface, a second surface opposite the first surface of the second component, a cooling hole extending from the second surface of the second component to the first surface of the second component through the second component, and a receiving aperture extending from the second surface to the first surface through the second component, wherein the first surface of the second component and the second surface of the first component define a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the first component, a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow from the injection aperture in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel, wherein the faired body is located proximate the first end of the threaded stud; and an injection aperture (730a-c) fluidly connecting airflow in an airflow path proximate the second surface of the second component to the cooling channel and configured to convey the airflow into the cooling channel towards the faired body; wherein the threaded stud extends from the second surface of the first component through the cooling channel and through the receiving aperture of the second component; characterised in that the gas turbine engine component assembly further comprises: a plurality of channel walls encircling the threaded stud, each of the plurality of channel walls extending out from the second surface of the first component into the cooling channel, wherein the faired body is integrally formed with each of the plurality of channel walls, the plurality of channel walls being shaped such that airflow is channeled away from the threaded stud through channels radially interposed between the channel walls, and wherein each of the channel walls includes a flat top so as to act as push pins. a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component, wherein the first end of the threaded stud is located proximate to the second surface of the first component; a second component having a first surface, a second surface opposite the first surface of the second component, a cooling hole extending from the second surface of the second component to the first surface of the second component through the second component, and a receiving aperture extending from the second surface to the first surface through the second component, wherein the first surface of the second component and the second surface of the first component define a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the first component, a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow from the injection aperture in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel, wherein the faired body is located proximate the first end of the threaded stud; and an injection aperture (730a-c) fluidly connecting airflow in an airflow path proximate the second surface of the second component to the cooling channel and configured to convey the airflow into the cooling channel towards the faired body; wherein the threaded stud extends from the second surface of the first component through the cooling channel and through the receiving aperture of the second component; characterised in that the gas turbine engine component assembly further comprises: a plurality of channel walls encircling the threaded stud, each of the plurality of channel walls extending out from the second surface of the first component into the cooling channel, wherein the faired body is integrally formed with each of the plurality of channel walls, the plurality of channel walls being shaped such that airflow is channeled away from the threaded stud through channels radially interposed between the channel walls, and wherein each of the channel walls includes a flat top so as to act as push pins.