GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND LOBED COOLING HOLE

摘要

A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole is formed in the gas path wall and extends from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface. A longitudinal ridge extends along the cooling hole between the transition and the outlet. The longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes.