Multi-lobed cooling hole and method of manufacture

摘要

A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.

主权项

1. 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.