LOW RADIUS RATIO FAN FOR A GAS TURBINE ENGINE

摘要

A fan blade (18) for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure (40) and suction sides (42), and further including at least one shoulder (62,64) protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss (66,74) defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.