Multi-peripheral serpentine microcircuits for high aspect ratio blades

摘要

A cooling arrangement for a pressure side of an airfoil portion (102) of a turbine engine component (100) is provided. The cooling arrangement comprises a pair of cooling circuits (104, 106; 204, 206) embedded within a wall forming the pressure side. The pair of cooling circuits includes a first serpentine cooling circuit (104; 204) and a second circuit (106; 206) offset from the first serpentine cooling circuit (104; 204).