Patent ID: 8128375

Claim:
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, the airfoil having a theoretical profile; an endpiece of the airfoil, having an airfoil end face on a 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 P 1 situated on the suction face of the airfoil and on the end face of the endpiece upstream of the suction face neck with reference to the direction of flow of the fluid and a point P 3 situated on the pressure face of the airfoil and on the end face of the endpiece upstream of the pressure face neck, wherein a line of points situated furthest upstream relative to a direction of flow of fluid in the connection zone P 2 is situated in line with the leading edge on the skeleton, and wherein a surface of the connection zone has a profile C 1 between the line of the points P 2 and the point P 1 which is similar to the suction face surface of the theoretical profile of the airfoil, and a surface of the connection zone has a profile C 3 between the line of the points P 2 and the point P 3 which is similar to the pressure face surface of the theoretical profile of the airfoil.