GAS TURBINE COMPONENT ASSEMBLY FOR MITIGATING AIRFLOW SEPARATION AROUND ENGINE COMBUSTOR

摘要

According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprises: a first component (600) having a first surface and a second surface (620) 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 (704) path such that airflow (590) in the first airflow path separates from the second surface of the first component; and a first fairing (700) 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.