Patent ID: 8689568

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 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 trailing edge; a second lobe diverging longitudinally and laterally from the metering section and having a trailing edge; an upstream end located at the outlet; a downstream end generally opposite the upstream end and located at the outlet, wherein the downstream end extends in a straight and lateral direction from an end of the first lobe to an end of the second lobe, and wherein the downstream end is at least axially coextensive with the trailing edges of the first and second lobes; a first sidewall having a first edge extending along the outlet between the upstream end and the downstream end trailing edge, the first edge diverging laterally from the upstream end and converging laterally before reaching the downstream end; and a second sidewall having a second edge extending along the outlet between the upstream end and the downstream end generally opposite the first sidewall, the second edge diverging laterally from the upstream end and converging laterally before reaching the downstream end.