Fan Blades for Gas Turbine Engines with Reduced Stress Concentration at Leading Edge

A gas turbine engine comprising:

• a fan blade assembly including a rotor disk having an outer periphery, the outer periphery of the rotor disk including a plurality of single tooth attachment slots;
• a plurality of fan blades, each fan blade including an airfoil connected to a single tooth attachment at a transition section, each single tooth attachment slot of the rotor disk accommodating one of the single tooth attachments of one of the fan blades;
• for each fan blade, the airfoil, transition section and dovetail including leading and trailing edges;
• for each fan blade, the transition section defining a first chord at a junction of said transition section and its airfoil, for each fan blade, the transition section defining a second chord at a junction of said transition section and its single tooth attachment, for each fan blade, the leading and trailing edges of the single tooth attachment define a length;
• wherein for each fan blade, the second chord is at least as long as the length of its single tooth attachment and, for each fan blade, the first chord is longer than the second chord.