A turbofan gas turbine engine fan blade and a turbofan gas turbine engine fan rotor arrangement

摘要

A fan blade ( 26 ) comprises a root portion ( 36 ) and an aerofoil portion ( 38 ). The aerofoil portion ( 38 ) has a leading edge ( 44 ), a trailing edge ( 46 ) and a tip ( 48 ) remote from the root portion ( 36 ). A concave pressure surface ( 50 ) extends from the leading edge ( 44 ) to the trailing edge ( 46 ) and a convex suction surface ( 52 ) extends from the leading edge ( 44 ) to the trailing edge ( 46 ). A portion ( 54 ) of the tip ( 48 ) of the aerofoil portion ( 38 ) between the leading edge ( 44 ) and the trailing edge ( 46 ) of the aerofoil portion ( 38 ) is thinner than the remainder ( 56, 58 ) of the tip ( 48 ). The portion ( 54 ) of the tip ( 48 ) of the aerofoil portion ( 38 ) is spaced from the leading edge ( 44 ) and is spaced from the trailing edge ( 46 ). The portion ( 54 ) of the tip ( 48 ) of the aerofoil portion ( 38 ) has a recess such that the portion ( 54 ) of the tip ( 48 ) of the aerofoil portion ( 38 ) is thinner than the remainder ( 56,58 ) of the tip ( 48 ). The recess is arranged on the concave pressure surface ( 50 ) of the aerofoil portion ( 38 ). This reduces vibrations of the fan blade ( 26 ).