PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

A feedback device (400; 600; 650) for use in a gas turbine engine (110), and methods and systems (200) for controlling a pitch for an aircraft-bladed rotor (130), are provided. The feedback device (400; 600; 650) is composed of a circular disk (410) and a plurality of position markers (402). The circular disk (410) is coupled to rotate with a rotor (130) of the gas turbine engine (110), to move along a longitudinal axis (A) of the rotor (130), and has first and second opposing faces (416, 418) defining a root surface (412) that extends between and circumscribes the first and second faces. (416, 418) The plurality of position markers (402) extend radially from the root surface (412) and are circumferentially spaced around the circular disk (410). The position markers (402) have a top surface (404) elevated with respect to the root surface (412) and opposing first and second side surfaces (406, 408). The side surfaces of the position markers (402) have a curved concave profile extending toward the root surface (412).