Patent ID: 6408610
Filing Date: 2002-06-25
Classification: B23P,C23C,F01D,Y10T

Abstract:
A method of adjusting airflow through a plurality of cooling holes extending through a gas turbine engine component from an interior surface of the component to an exterior surface of the component, the method comprising the steps of:depositing a thermal barrier coating on at least one of the exterior surface and the interior surface of the component by a physical vapor deposition process without masking said plurality of cooling holes thereby permitting a portion of the thermal barrier coating to partially obstruct airflow through said plurality of cooling holes and reducing airflow through said plurality of cooling holes; developing a predetermined pressure drop across said plurality of cooling holes after depositing the thermal barrier coating on the component; calculating airflow through said plurality of cooling holes resulting from the predetermined pressure drop across said plurality of cooling holes; comparing the calculated airflow through said plurality of cooling holes to a preselected range of desired cooling hole airflows; and repeating the steps of depositing the thermal barrier coating, developing the predetermined pressure drop, calculating airflow and comparing the calculated airflow to the preselected range until the calculated airflow is within the preselected range of desired cooling hole airflows.