FAN BLADE FOR A GAS TURBINE ENGINE

A fan blade (100) includes an aerofoil portion (110) including a leading edge (120) extending from a root (140) to a tip (150) and defining a blade span (145) therebetween. A leading edge thickness (TLE) is defined as a thickness of a cross-section at a given radius at a location along a camber line (C) that is 9% of the total length of the camber line (C) from the leading edge (120). For cross-sections through the aerofoil portion (110) at radii between 50% and 70% of the blade span (145) from a root radius, the leading edge thickness (TLE) includes a first maximum value (T1max). For cross-sections through the aerofoil portion (110) at radii greater than 70% of the blade span (145) from the root radius, the leading edge thickness (TLE) includes a second maximum value (T2max) that is between 105% and 125% of the first maximum value (T1max).