Patent ID: 7946825

Claim:
A turbofan gas turbine engine fan blade comprising: a root portion and an aerofoil portion, the aerofoil portion has a leading edge, a trailing edge and a tip remote from the root portion, a concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge, a portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion has a recess arranged on the concave pressure surface of the aerofoil portion such that the portion of the tip of the aerofoil portion is thinner than a remainder of the tip, the portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge, and the turbofan gas turbine engine fan blade being located in a fan section of a turbofan gas turbine engine, wherein a thickness of the portion of the tip of the aerofoil portion reduces to a minimum thickness in the range of 60% to 70% of the thickness of the remainder of the tip.