Patent ID: 9243500
Filing Date: 2016-01-26
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A turbine blade for a gas turbine engine comprising: an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction, the trailing edge arranged on an aft side of the turbine blade; a root supporting a platform from which the airfoil extends, and a cooling passage extending within the root in the radial direction to the airfoil; and a lower wing arranged beneath the platform on the aft side and extending in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction, and an impingement hole extending from the U-channel to the cooling passage, wherein the impingement hole is oriented generally in a radial direction, wherein the impingement hole is configured to direct fluid onto an underside of the platform.