Turbomachine blade that is cast with a local fattening of the section of the airfoil

A monocrystalline turbine blade for a turbomachine turbine rotor, said blade being cast and directionally solidified, comprising

• an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element,
• an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis and
• a connection zone between the airfoil and said airfoil end face, said connection zone forming a fattening of the airfoil,
• wherein said connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil and on the end face of the heel upstream of the suction face neck with reference to the direction of flow of the fluid and a point P3 situated on the pressure face of the airfoil and on the end face of the heel upstream of the pressure face neck.