Gas turbine engine e.g. turbofan aircraft engine, fan blade, has vane presenting front aerodynamic deflection at distal end, from leading edge to trailing edge, and comprising lower and upper surfaces situated opposite to each other

摘要

The blade has a vane (36) that extends outwards from a slanted base (38) to define an inner radial limit for an air stream passage. The vane has a concave shaped lower surface (42) and a convex shaped upper surface situated opposite to each other in the direction of the periphery. The surfaces radially extend in height from an inner base side end to a distal end (46) situated radially at outside, in the immediate neighborhood of a fan casing (16). The vane presents a front aerodynamic deflection at the end (46), from a leading edge (48) to a trailing edge (50). An independent claim is also included for a set of fan blades.