Adjusting pitch for airfoils of an aircraft propulsion system

Abstract

A method is provided for operating an aircraft propulsion system. During this method, rotation of a propulsor rotor of the propulsion system is driven about a rotational axis. The propulsor rotor includes a plurality of rotor blades. A first blade pitch schedule is applied to the propulsor rotor while the propulsor rotor is rotating about the rotational axis such that: (a) a pitch of each of the rotor blades has a maximum blade pitch value when located at a first circumferential position about the rotational axis; (b) the pitch of each of the rotor blades has a minimum blade pitch value when located at a second circumferential position about the rotational axis; and (c) a reference line extending between the first circumferential position and the second circumferential position is angularly offset from a pitch axis of the aircraft by a first offset angle between zero degrees and forty-five degrees.

Dependencies are inferred from the claim text.