Gas turbine engine turbine vane baffle and serpentine cooling passage

A method of cooling an airfoil for a gas turbine engine, the method comprising:

• providing an airfoil that includes:
• pressure and suction side walls joined to one another at leading and trailing edges, the pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface;
• a baffle arranged in the airfoil cavity, the baffle includes a supply hole;
• ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle, the ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls, the serpentine cooling passage has first and second passes joined by a bend, the ribs form an inlet pass upstream from and parallel to the first and second passes, the inlet pass and first and second passes form an S-shape, the ribs form a film cooling cavity between the first and second passes, and the supply hole fluidly connects the baffle to the film cooling cavity;
• and
• film cooling holes extend through the at least one of the pressure and suction side walls, the film cooling holes in fluid communication with the film cooling cavity;
• and
• supplying a first cooling fluid to the inlet pass, the first cooling fluid flows along the inlet pass in a first radial direction;
• turning the first cooling fluid and flowing the first cooling fluid along the first pass in a second radial direction opposite the first radial direction;
• turning the first cooling fluid at the bend and flowing the first cooling fluid along the second pass in the first direction;
• and
• supplying a second cooling fluid through the baffle and through the supply hole, flowing the second cooling fluid through the film cooling cavity and out the film cooling holes.