Aircraft engine propulsor blade pitch sensing.

摘要

Pitch of a blade (12) on an aircraft engine propulsor (14) is determined by employing a shaft (22) and a bevel gear (23) to alter relative circumferential distance between a first set of teeth (25) and a second set of teeth (26). Said teeth (25,26) creates fluctuations in a magnetic field generated by a magnetic poll piece (28a) wherein said fluctuations are converted to a signal (30) by a coil (28) located on a subsequent engine section (8). The time between pulses of the signal (30) is a function of said relative circumferential distance whereby the time between pulses is a function of the pitch of the blade (12).