Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall

摘要

A turbine vane for a gas turbine engine having an internal cooling system in fluid communication with cooling channels positioned in the inner endwall is disclosed. The cooling system in the inner endwall may include cooling channels extending outwardly from the leading edge, trailing edge, pressure side and suction side toward the edges of the inner endwall. The cooling channels may be serpentine cooling channels and may be two or more serpentine cooling channels coupled together in series. The cooling channels may exhaust cooling fluids from the inner endwall through a plurality of orifices on an outer surface facing the opposing endwall and on the sides surfaces of the endwall. The pressure side and suction side midchord modulus serpentine flow circuits may receive cooling fluids from one pass of an internal midchord cooling channel and may exhaust those cooling fluids into another pass of the midchord cooling channel.