To provide an improved flow directing device for a gas turbine engine.

The flow directing device for the gas turbine engine has an airfoil (103) having a leading edge, trailing edge, suction side and pressure side, a wall (105) contacting to the airfoil (103), and a fillet part (F) provided between the airfoil (103) and the wall (105). The fillet part (F) has an enlarged section (E) at the leading edge, along the suction and pressure sides, and toward the trailing edge. The device could be a part of a vane segment (101). In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil (103) by directing the relatively low temperature gas from the proximal end of the airfoil (103) toward the relatively high temperature gas at the intermediate section of the airfoil (103).