Airfoil having serpentine core resupply flow control

An airfoil for a gas turbine engine, the airfoil comprising:

• an airfoil body having a leading edge and a trailing edge, the airfoil body defining an axial direction from the leading edge to the trailing edge, a radial direction from a root to a tip, and a circumferential direction from a pressure side to a suction side;
• a first serpentine cavity formed within the airfoil body and defining a first portion of a serpentine cooling flow path and enabling a cooling flow in a first direction within the airfoil body;
• a second serpentine cavity fluidly connected to the first serpentine cavity and defining a second portion of the serpentine cooling flow path and enabling a cooling flow in a second direction;
• a third serpentine cavity fluidly connected to the second serpentine cavity and defining a third portion of the serpentine cooling flow path and enabling a cooling flow in at least one of the first direction or a third direction, wherein a serpentine cooling air flows through the serpentine cooling flow path;
• a resupply cavity fluidly connected to the third serpentine cavity and arranged to supply a resupply air to the third serpentine cavity;
• a junction defined at the location where both the second serpentine cavity and the resupply cavity fluidly connect to the third serpentine cavity;
• and
• a flow control feature located at the junction and arranged to at least one of (i) turn the serpentine cooling air from the second direction to at least one of the first or third direction or (ii) prevent the resupply air from flowing into the second serpentine cavity,
• wherein the flow control feature defines a tapering flow control cavity that narrows in the circumferential direction to form one or more tapering portions to turn the serpentine cooling air and/or prevent the resupply air from flowing into the second serpentine cavity.