TURBINE AIRFOIL WITH BIASED TRAILING EDGE COOLING ARRANGEMENT

摘要

An airfoil (10) for a turbine engine includes an array of features (22) positioned in an interior portion (11) of the airfoil (10). Each feature (22) extends from a pressure (14) side to a suction side (16). The array includes multiple radial rows (A-N) of features (22) with the features (22) in each row (A-N) being interspaced radially to define coolant passages (24) therebetween. The radial rows (A-N) are spaced along a forward-to-aft direction toward an airfoil trailing edge (20). The coolant passages (24) of the array are fluidically interconnected to lead a pressurized coolant toward the trailing edge (20) via a serial impingement on to the rows of features (22). The coolant passages (24) are geometrically configured to bias a coolant flow therethrough toward a first side (14) in relation to a second side (16) of the outer wall (12) to effect a greater cooling of the first side (14) than the second side (16).