Gas turbine vane segment having a bifurcated cavity

摘要

A turbine nozzle segment (10) includes a single hollow airfoil (28) extending radially between radially outer and inner band segments (24 and 26). The airfoil has an airfoil wall with pressure and suction sides (22 and 23) extending axially between leading and trailing edges (LE and TE) of the airfoil. The airfoil wall surrounds a bifurcated cavity (37) and a bifurcating rib (39) extends through the bifurcated cavity (37) and between the pressure and suction sides (22 and 23) of the airfoil wall dividing the bifurcated cavity (37) into forward and aft cavities (41 and 43). A stiffening rib (60) extends radially outwardly from and along a radially outer surface (62) of the outer band segment (24) and axially and circumferentially from a pressure side forward corner (64) of the outer band segment (24) to the bifurcating rib (39). The outer and inner band segments (24 and 26), the bifurcating rib (39), and the stiffening rib (60) are integral and made from a unitary one-piece casting.