Patent ID: 9422816
Filing Date: 2016-08-23
CPC Classification: F01D,F05D,Y10T

Claim Text:
1. An apparatus for a gas turbine engine, the apparatus comprising: an airfoil defining a trailing edge, opposite first and second faces, and a mean camber line; a metering opening for metering a cooling fluid; a cutback slot configured to deliver the cooling fluid from the metering opening, the cutback slot defined along the first face of the airfoil adjacent to the trailing edge and offset from the mean camber line of the airfoil; and a cooling hole having an outlet that is located at the trailing edge and substantially aligned with the mean camber line of the airfoil, wherein the cooling hole delivers a portion of the cooling fluid from the metering opening, wherein the cutback slot defines an upstream boundary at the first face of the airfoil, and wherein the cooling hole defines an inlet located at or downstream from the upstream boundary of the cutback slot.