System and method for electronic propeller blade angle position feedback

Patent metadata

Field	Value
Publication number	US-9821901-B2
Application number	US-201414546252-A
Country	US
Kind code	B2
Filing date	Nov 18, 2014
Priority date	Nov 21, 2013
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A system and method for blade angle position feedback. The system comprises an annular member operatively connected to rotate with a propeller, a sensor fixedly mounted adjacent the annular member and configured for detecting a passage of each singularity as the annular member is rotated and axially displaced and for generating a sensor signal accordingly, the annular member and sensor configured for relative axial displacement between a first relative axial position and a second relative axial position respectively corresponding to the first and the second mode of operation, and a detection unit connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive singularities, and computing from the time interval blade angle position.

First claim

The invention claimed is:

1. A blade angle position feedback system for an aircraft propeller, the propeller rotatable about an axis and comprising a plurality of blades each rotatable through a plurality of blade angles, the propeller having at least a first mode of operation where the plurality of blades are operated at a positive blade angle and a second mode of operation where the plurality of blades are operated at a negative blade angle, the system comprising:
an annular member operatively connected to rotate with the propeller, the annular member comprising at least two circumferentially-spaced first singularities extending substantially parallel to the axis and at least one second singularity extending non-parallel to the first singularities;
at least one sensor fixedly mounted adjacent the annular member, the at least one sensor configured for successively detecting a passage of each one of the at least two first singularities and the at least one second singularity as the annular member is rotated and axially displaced and for generating a sensor signal accordingly, the annular member and at least one sensor configured for relative axial displacement between a first relative axial position and a second relative axial position, the first position corresponding to the first mode of operation and the second position corresponding to the second mode of operation; and
a detection unit connected to the at least one sensor for receiving the sensor signal therefrom, determining, by a processor, on the basis of the sensor signal a time interval elapsed between the passage of successive ones of the at least two first singularities and the at least one second singularity, and computing, by the processor, from the time interval a blade angle position for the plurality of blades.

2. The system of claim 1 , wherein the annular member is mounted for axial displacement relative to a fixedly-mounted at least one sensor.

3. The system of claim 1 , wherein each of the at least one second singularity is positioned between two consecutive ones of the at least two first singularities.

4. The system of claim 3 , wherein the detection unit is for computing a first time interval Tm between the passage of a first one of the at least two first singularities and the passage of a first one of the at least one second singularity, computing a second time interval Ts between the passage of the first one of the at least one second singularity and the passage of a second one of the at least two first singularities, the first one of the at least one second singularity positioned between the first one and the second one of the at least two first singularities, and computing the blade angle position as: Blade angle position =(Ts−Tm)/(Ts+Tm).

5. The system of claim 4 , wherein the annular member is rotatable about the axis and axially displaceable therealong for exposing different portions of the at least one second singularity to the at least one sensor, the annular member, when in the first position, exposing a forward portion of the at least one second singularity to the at least one sensor, when in the second position, exposing a rearward portion of the at least one second singularity to the at least one sensor, and, when transitioning between the first and the second position exposing successive portions of the at least one second singularity provided between the forward and the rearward portion.

6. The system of claim 5 , wherein, as the annular member is rotated and axially displaced between the first and the second position, a time at which the at least one sensor detects a given one of the portions of the at least one second singularity is different from a time at which the at least one sensor detects a subsequent one of the portions of the at least one second singularity, such that the first and the second time intervals computed by the detection unit further to detection of a first passage of the at least two first singularities and the at least one second singularity differ from the first and the second time intervals computed by the detection unit further to detection of a subsequent passage of the at least two first singularities and the at least one second singularity.

7. The system of claim 4 , further comprising a memory having stored therein data indicative of a number of the at least two first singularities and the at least one second singularity provided on the annular member, wherein the detection unit is configured to retrieve the data from the memory, to compute a sum of the first time interval and the second time interval and to determine a rotation speed of the propeller on the basis of the number of singularities and of the sum.

8. The system of claim 1 , wherein the at least one sensor is configured to detect a missing one of the singularities removed from the annular member and to accordingly generate the sensor signal indicative of detection of the missing singularity, the detection unit configured to synchronize the propeller of a first engine with the propeller of at least one second engine on the basis of the sensor signal.

9. The system of claim 1 , wherein the singularities are on an internal face of the annular member and the at least one sensor is mounted adjacent the internal face.

10. The system of claim 1 , wherein the singularities are on an outer face of the annular member and the at least one sensor is mounted adjacent the outer face.

11. The system of claim 1 , wherein the at least two first singularities and the at least one second singularity are selected from a group consisting of a projecting tooth extending away from the annular member and a slot formed in the annular member.

12. The system of claim 1 , wherein the at least one sensor comprises a first sensor diametrically opposite to a second sensor.

13. An aircraft propeller system comprising:
a propeller having a plurality of blades each rotatable from a positive blade angle to a negative blade angle;
an annular member comprising circumferentially-spaced first singularities each extending generally parallel and at least a second singularity extending non-parallel to the first singularities;
a sensor adjacent the annular member and configured for detecting said singularities passing the sensor, the annular member and sensor slidingly mounted with respect to one another between first and second relative axial positions, one of the annular member and sensor mounted for rotation with the propeller and the other fixedly mounted to the engine; and
a detection unit connected to the sensor and configured for computing, by a processor, a blade angle position based elapsed time between detected singularities.

14. The system of claim 13 , wherein said movement of the annular member is exposing different portions of the singularities to the sensor, the first and second singularities arranged to have different relative spacings therebetween at the sensor location depending on axial position of the annular member.

15. The system of claim 13 , wherein the singularities are selected from a group consisting of a projecting tooth and a slot formed in the annular member.

16. A method for blade angle position feedback for an aircraft propeller, the propeller rotatable about an axis and comprising a plurality of blades each rotatable through a plurality of blade angles, the propeller having at least a first mode of operation where the plurality of blades are operated at a positive blade angle and a second mode of operation where the plurality of blades are operated at a negative blade angle, the method comprising:
receiving a sensor signal from at least one s

Assignees

• Pratt & Whitney Canada

Inventors

• Duke Brant
• Jarvo James Robert
• Mark Michael
• Guerra Mario

Classifications

• G01P3/488

  delivered by variable reluctance detectors · CPC title

• G01D5/145

  influenced by the relative movement between the Hall device and magnetic fields (see G01R33/06) · CPC title

• F01D7/00

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C11/06

  for variable-pitch blades · CPC title