MORPHING STRUCTURES FOR ADJUSTABLE FAN INLET GUIDE VANES

A gas turbine engine (10) includes a fan section (12), a compressor section (14), and a turbine section (18). The fan section (12) has a plurality of vane assemblies (64) spaced circumferentially about an engine axis (A) and each including an airfoil (66) extending between a leading edge (66a) and a trailing edge (66b), a control rod (68) extending through the airfoil (66), and a mechanism driven by the control rod (68) to change the shape of the airfoil (66).