Dual-fed airfoil tip

A gas turbine engine comprising:

• an airfoil having:
• a leading edge extending in a radial direction;
• a tip extending in an axial direction form the leading edge;
• a first rib extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity within the airfoil;
• a second rib, the second rib and the first rib defining a serpentine cavity therein;
• a third rib extending axially within the tip, a flag tip cavity defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity;
• a bypass aperture formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity, wherein the bypass aperture is located adjacent the first rib;
• and
• a divider portion located proximate to the bypass aperture within the serpentine cavity and configured to aid in directing (i) a first portion of air from the serpentine cavity into the flag tip cavity and (ii) a second portion of air within the serpentine cavity,
• wherein the first rib includes a direction portion proximate to the bypass aperture that is canted toward the leading edge and away from the bypass aperture and divider portion.