Aircraft engine propulsor blade pitch sensing
AssigneeUnited Technologies Corporation
InventorsAnthony N. Martin, Robert G. Bartle
Life of this patent
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Abstract
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).
Claims4
A mechanism for determining pitch angle of a blade located on an aircraft engine propulsor, said mechanism comprising:
- means for generating a magnetic field;
- first and second magnetic field fluctuation inducers located on said propulsor and revolving about the axis of rotation of said propulsor for causing fluctuations in said magnetic field;
- a magnetic field-to-signal converter located on an engine section adjacent to said propulsor responsive to said fluctuations in said magnetic field for providing a signal indicative of said fluctuations and;
- a mechanical linkage responsive to changes in the pitch angle of said blade for changing the relative circumferential distance between said first and second magnetic field fluctuation inducers, wherein said relative circumferential distance is a monotonic function of the pitch angle of the blade, whereby said fluctuations vary as a monotonic function of the pitch angle of said blade.
Dependencies are inferred from the claim text.