Gas turbine engine component with compound cooling holes and met

Details Gas turbine engine component with compound cooling holes and met Gas turbine engine component with compound cooling holes and met

1993-03-17

1997-11-04

Carone, Michael J.

Electric heating

Metal heating

By arc

21912172, B23K 2600

Patent

active

056836007

ABSTRACT:
A gas turbine engine component includes a wall portion with at least one compound cooling hole formed therein between an external surface of the component and an interior plenum. The at least one compound cooling hole includes a non-circular diffuser opening formed by a laser beam with a non-circular cross-sectional area, and a channel with a substantially circular cross-section connecting the diffuser opening and the interior plenum. The channel is also formed by the non-circular laser beam in the same laser drilling operation as the diffuser opening. The cooling hole further includes a transition point at which the compound hole begins to convert from a substantially non-circular cross-section to a substantially circular cross-section. The location of the transition point is controlled by positioning a focal point of the non-circular laser beam to undershoot the external surface of the component by a predetermined distance.

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