Patent ID: 11773728

Abstract:
An airfoil, such as a vane or a blade for a gas turbine engine, may be provided. The airfoil may include a platform; a spar; a fillet; and a coversheet. The spar may include a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and a spar hole configured to direct the cooling fluid from the passageway to the outer surface of the spar. The fillet may be located at the intersection of the platform and the spar, and may couple the spar to the platform. The fillet and/or the coversheet may include a protrusion extending along the edge of the coversheet. The protrusion, along with the pedestal and the outer surface of the spar, may define a purge groove. The purge groove and a purge groove outlet may form a cooling path for cooling fluid to flow onto the platform.