Patent attributes
An airfoil for a gas turbine engine, the airfoil including a cooling air passage to provide internal cooling for the airfoil. A supply passage is formed in the root of the airfoil to deliver cooling air to the airfoil. A series of near-wall cooling passages extend along the wall of the airfoil in a radial direction and provide near-wall cooling for the airfoil. Within the airfoil wall is a plurality of collector cavities separated by a rib. A first near-wall cooling passage carries cooling air from the supply passage, around the airfoil from pressure side to suction side, and then discharges the cooling air into a collector cavity. Adjacent near-wall cooling passages carry cooling air from the supply passage to the collector cavity in an opposite direction from the first near-wall cooling passage, from the suction side to the pressure side of the airfoil. Film cooling holes extend from the collector cavity to the external surface of the airfoil. A shower head cooling arrangement is supplies by the forward cavity while a trailing edge cooling holes are supplied by cooing air from an aft collector cavity. A tip region cooling channel connects the pressure side channel with the suction side channel, and provides near-wall cooling for the tip region.
