Turbine vane cooling arrangement

A method for cooling a vane doublet, comprising:

• generating a film cooling layer across a pressure side filet of each airfoil in the vane doublet by passing air through a plurality of film cooling holes that extend through an exterior surface of said airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein said first subset of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.