Aircraft turbine engine having means for detecting the axial displacement of a fan

An aircraft turbomachine comprising:

• a fan which is able to rotate about a longitudinal axis and which comprises a rotor disc and a plurality of blades with variable angular setting mounted at the periphery of the disc,
• a system for determining an angular setting position of at least one blade comprising:
• several setting reference members which are secured to the rotor disc,
• a position reference element secured to said at least one blade and which is able to change angular position with respect to the setting reference members in the event of modification of the angular setting of said at least one blade,
• at least one sensor which is positioned fixedly with respect to the fan and which is able to determine a relative angular position between the position reference element and the setting reference members by detecting the passage of the position reference element and of the setting reference members during the rotation of the fan,
• wherein the turbomachine is configured to detect an axial displacement of the fan by detecting an axial displacement of the setting reference members based on said at least one sensor.