Methods and apparatus for supplying cooling fluid to turbine nozzles

摘要

A turbine nozzle assembly for a gas turbine engine (10) comprises a turbine nozzle (50) including an outer band (54), an inner band (56), and a plurality of airfoil vanes (52) coupled together by the outer and inner bands, each airfoil vane is hollow and defines a cavity (90) therein; and a manifold ring (51) extending circumferentially around the turbine nozzle for channeling cooling fluid radially inwardly into each airfoil vane cavity. The manifold ring comprises a radially outer wall (138) and a radially inner wall (134) coupled together by a pair of sidewalls (136), wherein at least a portion (152) of the radially inner wall extends arcuately between the pair of sidewalls.