Multi-lobed cooling hole

A gas turbine engine component subjected to a flow of high temperature gas, the component comprising:

• a wall having first and second wall surfaces;
• and
• a cooling hole extending through the wall and comprising:
• an inlet located at the first wall surface;
• an outlet located at the second wall surface;
• a metering section extending downstream from the inlet;
• and
• a diffusing section extending from the metering section to the outlet and comprising:
• a first lobe diverging longitudinally and laterally from the metering section and having a first downstream end adjacent the outlet and spaced from the inlet by a first distance;
• a second lobe diverging longitudinally from the metering section and having a second downstream end adjacent the outlet and spaced from the inlet by a second distance different from the first distance;
• a first transition region positioned between the first and second lobes, the first transition region comprising a third downstream end adjacent the outlet;
• and
• a second transition region positioned between the first transition region and the second lobe, the second transition region comprising a fourth downstream end adjacent the outlet, wherein the metering section comprises a longitudinal axis, and wherein the third downstream end is generally perpendicular to the longitudinal axis of the metering section, and wherein the fourth downstream end is angled with respect to the longitudinal axis of the metering section.