Patent ID: 10900361

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