Patent ID: 9057276
Filing Date: 2015-06-16
Classification: F01D

Abstract:
1. A gas turbine engine blade, comprising: an airfoil comprising a pressure side exterior surface, a pressure side interior surface, a suction side exterior surface, a suction side interior surface, and a first rib spanning between the pressure side interior surface and the suction side interior surface, wherein the first rib defines part of a serpentine cooling channel, wherein the airfoil is twisted from a base end of the airfoil to a tip end of the airfoil, wherein the first rib is twisted from a base end of the first rib to a tip end of the first rib, wherein the first rib comprises a narrowing taper along its entire length between the pressure side interior surface and the suction side interior surface, wherein the taper is effective to increase an angle of intersection between a first rib surface and at least one of the pressure side and suction side interior surfaces in a corner of the serpentine cooling channel defined by the first rib when compared to an untapered rib, and wherein the taper is symmetric about a first longitudinal axis of the first rib, and wherein the pressure side surfaces, the suction side surfaces, and the first rib are cast as a monolith; and a second rib spanning between the pressure side exterior surface and the suction side exterior surface that is twisted from a base end of the second rib to a tip end of the second rib, wherein the second rib comprises a narrowing taper along its entire length between the pressure side interior surface and the suction side interior surface, and the first rib and the second rib taper in an opposite direction than the other.