Near-wall serpentine cooled turbine airfoil

摘要

A serpentine coolant flow path is formed by inner walls in a cavity between pressure and suction side walls of a turbine airfoil, the cavity partitioned by one or more transverse partitions into a plurality of continuous serpentine cooling flow streams each having a respective coolant inlet.

主权项

1. A turbine airfoil comprising:
a pressure side wall and a suction side wall connected to each other along leading and trailing edges; a cavity disposed between the pressure and suction side walls; a continuous serpentine cooling flow path formed by first and second inner walls in the cavity; wherein:
the continuous serpentine cooling flow path routes a coolant flow in the following sequence as seen in a transverse section of the airfoil:
a) a cooling inlet channel that extends span-wise along at least a portion of the pressure side wall;b) a forward pressure side near-wall channel along a forward portion of the pressure side wall;c) a leading edge near-wall channel;d) a forward suction side near-wall channel along a forward portion of the suction side wall; ande) a loop channel routed between the first and second inner walls;the cooling inlet channel, as seen in the transverse section, is adjacent to the pressure side wall at position between 30% and 70% of a chord length from the leading edge of the airfoil;the first inner wall comprises a first end joined to an inner surface of the pressure side wall at a position between 50% and 75% of a chord length from the leading edge;the cavity is partitioned by one or more transverse partitions into a plurality of continuous serpentine cooling flow streams each having a respective coolant inlet; andthe first inner wall extends span-wise along at least a portion of the airfoil.