Patent ID: 9021816
Filing Date: 2015-05-05
Classification: B22C,F01D,F05D,Y02T

Abstract:
1. A turbine vane for a gas turbine engine comprising: inner and outer platforms joined by an airfoil extending in a radial direction, the airfoil including leading and trailing edges spaced apart from one another in a chord-wise direction and joined by spaced apart pressure and suction sides to provide an exterior airfoil surface, the airfoil including an airfoil cooling passage; and a platform core having a platform cooling passage arranged within at least one of the inner and outer platforms, the platform cooling passage including multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage in the radial direction and aligned with the airfoil cooling passage in the chord-wise direction, wherein the platform cooling passage includes a radially extending inlet, wherein the multiple cooling regions corresponds to first, second and third cooling regions arranged to provide a tortuous route for cooling air flowing through the platform cooling passage, the first cooling region adjoining the inlet, and wherein an elongated rib is arranged near the inlet and is circumscribed by and separates the first and second cooling regions.