Patent ID: 8683813

Claim:
A gas turbine engine component comprising: a wall having first and second wall surfaces and defining a cooling hole extending through the wall, the cooling hole including: 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, the diffusing section comprising: a first lobe diverging longitudinally in a first direction and laterally from the metering section, the first lobe comprising a curved outer portion; a second lobe adjacent the first lobe and diverging longitudinally in the first direction from the metering section; and a third lobe adjacent the second lobe and diverging longitudinally in the first direction and laterally from the metering section, the third lobe comprising a curved outer portion; and a transition region having an end adjacent the outlet and a portion that extends upstream of the outlet and between at least one of the first, second and third lobes and the outlet.