Gas turbine engine airfoils having multimodal thickness distributions

Abstract

Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions are provided. In one embodiment, the GTE airfoil includes an airfoil tip, an airfoil root opposite the airfoil tip in a spanwise direction, and first and second airfoil halves extending between the airfoil tip and the airfoil root. The first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in a thickness direction substantially perpendicular to the spanwise direction. The first multimodal thickness distribution may be defined by multiple locally-thickened airfoil regions, which are interspersed with multiple locally-thinned airfoil regions. The second airfoil half may or may not have a multimodal thickness distribution. By imparting at least one airfoil half with such a multimodal thickness distribution, targeted mechanical properties of the GTE airfoil may be enhanced with relatively little impact on aerodynamic performance.