FILM COOLING OF JET ENGINE COMPONENTS

摘要

Patent 13DV-10548 A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second surface exposable to a hotter, lower static pressure gas flow flowing across the second surface. The component further includes a film coolant passageway having an inlet on the first surface and an outlet on the second surface. The second surface has an open groove extending from the outlet along the gas flow for improved film cooling of the second surface.