Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating assembly and a sensor. The rotating assembly is configured to rotate about an axis. The rotating assembly includes an engine shaft and a phonic wheel threaded onto the engine shaft. The phonic wheel includes a lubricant scoop. The sensor is configured to measure fluctuations in a magnetic field induced by the phonic wheel during rotation of the rotating assembly about the axis.

An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating assembly configured to rotate about an axis. The rotating assembly includes an engine component and a phonic wheel. The engine component includes a first material and a plurality of apertures arranged circumferentially about the axis. The phonic wheel includes a second material and a plurality of teeth arranged circumferentially about the axis. Each of the teeth projects axially into a respective one of the apertures. One of the first material and the second material is or otherwise includes non-ferromagnetic material. Another one of the first material and the second material is or otherwise includes ferromagnetic material.

A system for preventing asynchronous rotation in aircraft components includes an optical emitting source, an optical receiver, and a retroreflector configured to be disposed on a rotating component connected to an engine of an aircraft. The system emits radiant flux from the optical emitting source towards the retroreflector when the retroreflector is on the rotating component and the engine positions the rotating component into a field of view of the optical emitting source; receives incident radiant flux from the retroreflector by the optical receiver when the retroreflector is within the field of view of the optical emitting source; records a time of receiving the incident radiant flux; determines a rotational speed of the rotating component based on the recorded time; determines whether the rotational speed is within a predetermined range; and selectively changes a state of the engine when the rotational speed is outside of the predetermined range.