Patent ID: 9464528
Filing Date: 2016-10-11
CPC Classification: F01D,F05D

Claim Text:
1. A turbine blade for a gas turbine engine, the turbine blade having a tip end and a root end, the turbine blade comprising: a base including a blade root, a platform, a cooling air inlet, and a base air passageway within the base, the base air passageway being configured to receive cooling air from the cooling air inlet and route the cooling air through the base air passageway; and an airfoil section adjoined to the base, the airfoil section including the plurality of directional film holes including a first portion of film holes and a second portion of film holes, each film hole of the first portion of film holes having the film hole inlet located closer to the platform than the film hole outlet, respectively, and being configured to discharge the cooling air toward the tip end at a first target angle relative to the platform, the second portion of film holes being located closer to the platform than the first portion of film holes, each film hole of the second portion of film holes having the film hole outlet located closer to the platform than the film hole inlet, respectively, and being configured to discharge the cooling air toward the platform at a second target angle relative to the platform, wherein