US Patent 12123317 Aeronautical propulsion system

A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the root including a first platform which has a radially outer surface; a shroud including a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.