Patent ID: 9416666
Filing Date: 2016-08-16
CPC Classification: F01D,F05D

Claim Text:
1. A turbine blade cooling system, comprising: a first turbine blade; the first turbine blade comprising an airfoil, a first turbine blade platform, and a blade cooling cavity extending into the airfoil and the first turbine blade platform; wherein the blade cooling cavity is in communication with a pressure side passage positioned in the first turbine blade platform and extending to a pressure side edge of the first turbine blade platform, wherein the pressure side passage has a first axial length extending from a forward end to an aft end of the pressure side passage each positioned along the pressure side edge of the first turbine blade platform, wherein the airfoil has a second axial length extending from a forward end to an aft end of the airfoil, and wherein the aft end of the pressure side passage is positioned axially upstream with respect to the aft end of the airfoil; and a second turbine blade; the second turbine blade comprising a second turbine blade platform and a platform cooling cavity; wherein the platform cooling cavity is in communication with a suction side passage positioned in the second turbine blade platform and extending to a suction side edge of the second turbine blade platform; and wherein the pressure side passage of the first turbine blade platform is in communication with the suction side passage of the second turbine blade platform.