COMBUSTOR LINER EFFUSION COOLING HOLES

摘要

A gas turbine engine component may be manufactured by an additive manufacturing process. The component may be a combustor liner. The combustor liner may include nonlinear cooling holes. The cooling holes may have an increased length compared to conventional linear cooling holes. The longer cooling holes may increase the amount of heat transfer from the combustor liner to the cooling air flowing through the cooling holes.

主权项

1. A gas turbine engine component comprising:
an outer surface of a first wall; an inner surface of the first wall; and a first cooling hole extending from the outer surface of the first wall to the inner surface of the first wall, wherein the first cooling hole is nonlinear.