Patent ID: 6969233

Claim:
A turbine nozzle segment comprising: a single hollow airfoil extending radially between radially outer and inner band segments, the airfoil located between circumferentially spaced apart pressure and suction side edges of the radially outer and inner band segments, the airfoil having an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil, the airfoil wall surrounding a bifurcated cavity, and a bifurcating rib extending through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities and, a stiffening rib axially and circumferentially aligned with the bifurcating rib, extending radially outwardly from and along a radially outer surface of the outer band segment, and extending axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib.