Patent ID: 8763402

Claim:
A gas turbine engine component comprising: a wall having first and second opposing surfaces and defining a cooling hole, the cooling hole extending through the wall from an inlet located at the first wall surface to an outlet located at the second wall surface and having: a metering section; and a diffusing section extending from the metering section to the outlet, the diffusing section comprising: a first lobe diverging longitudinally and laterally from the metering section and having a trailing edge; a second lobe diverging longitudinally and laterally from the metering section and having a trailing edge; and a transition region having a portion that extends between the first and second lobes, the transition region comprising a downstream end adjacent the outlet, wherein the downstream end is at least axially coextensive with the trailing edges of the first and second lobes such that a substantially straight line is formed from the trailing edges of the first to second lobes.