Patent ID: 7445432

Claim:
A cooling passageway for use in an airfoil portion of a turbine engine component having a pressure side wall and a suction side wall, said cooling passageway comprising: a serpentine flow passageway through which a cooling fluid flows, said passageway having an inlet through which cooling fluid is introduced into said passageway; said passageway having an inlet channel, an intermediate channel, and an outlet channel; said passageway having a first turn between said inlet channel and said intermediate channel; and a divider rib extending from a location in said inlet channel to a termination in said intermediate channel to divide a portion of inlet channel into a first inlet channel and a second inlet channel and a portion of said intermediate channel into a first intermediate channel and a second intermediate channel, said divider rib having an arcuately shaped portion located in said first turn to promote flow of said cooling fluid around said first turn, and said divider rib being solid from said location in said inlet channel to said termination in said intermediate channel including said arcuately shaped portion.