Elliptical-rectangular film cooling hole

A component of a gas turbine engine, the component comprising:

• a wall having a first surface and a second surface opposite the first surface and bounding a primary flow of the gas turbine engine;
• and
• a cooling passage extending through the wall from an inlet at the first surface to an outlet at the second surface, the inlet in fluid communication with a cooling fluid source and the outlet offset from the inlet along a primary flow direction of the primary flow, the cooling passage comprising:
• a metering section extending from the inlet towards the outlet along a centerline extending through a geometric center of the metering section;
• and
• a diffuser section extending from the metering section to the outlet, wherein the diffuser section comprises:
• a fore wall;
• and
• a back wall opposite and downstream from the fore wall relative to the primary flow direction;
• wherein the fore wall and the back wall diverge laterally towards the outlet;
• wherein the fore wall is parallel to the centerline and the back wall diverges from the centerline towards the outlet;
• and
• wherein the fore wall and the back wall define a plurality of cross-sections normal to the centerline, each cross-section including a semi-elliptical portion formed by the fore wall and a semi-rectangular portion formed by the back wall, a semi-minor axis of the semi-elliptical portion bisecting the fore wall.