System and method for propeller feedback ring position detection

Patent metadata

Field	Value
Publication number	US-10864979-B2
Application number	US-201816020930-A
Country	US
Kind code	B2
Filing date	Jun 27, 2018
Priority date	Jun 27, 2018
Publication date	Dec 15, 2020
Grant date	Dec 15, 2020

Abstract

A system and method for determining a position of a feedback ring of a propeller of an aircraft engine are provided. The feedback ring is coupled to the propeller to rotate with the propeller and to be displaced along a longitudinal axis with adjustment of a blade angle. An engagement member is configured to engage the feedback ring and to be displaced along a longitudinal direction substantially parallel to the longitudinal axis with displacement of the feedback ring. A sensor comprises a first member coupled to the engine and a second member coupled to the engagement member. The second member is moveable relative to the first member along the longitudinal direction as the engagement member is displaced. The sensor generates a signal indicative of a longitudinal position of the second member relative to the first member. A controller determines an axial position of the feedback ring from the sensor signal.

First claim

What is claimed is:

1. A feedback ring position detection system for a propeller of an aircraft engine, the propeller rotatable about a longitudinal axis and having an adjustable blade angle, the system comprising:
a feedback ring coupled to the propeller to rotate with the propeller and to be displaced along the longitudinal axis with adjustment of the blade angle;
an engagement member configured to moveably engage the feedback ring and to be displaced along a longitudinal direction substantially parallel to the longitudinal axis with displacement of the feedback ring;
a sensor comprising a first member coupled to the aircraft engine and a second member coupled to the engagement member, the first member stationary and the second member moveable relative to the first member along the longitudinal direction as the engagement member is displaced, the sensor configured to generate a sensor signal indicative of a longitudinal position of the second member relative to the first member; and
a controller configured to receive the sensor signal and to determine an axial position of the feedback ring along the longitudinal axis based on the longitudinal position of the second member relative to the first member.

2. The system of claim 1 , wherein the feedback ring has a channel formed around a circumference thereof.

3. The system of claim 2 , wherein the engagement member is configured to be retained in the channel.

4. The system of claim 3 , wherein the channel is u-shaped and the engagement member is a block.

5. The system of claim 1 , wherein the sensor is a linear variable differential transformer, the first member comprising a plurality of solenoidal coils and the second member comprising a ferromagnetic core.

6. The system of claim 1 , wherein the first member is secured to a gear box of the aircraft engine.

7. The system of claim 1 , wherein the sensor is configured to generate the sensor signal indicative of a longitudinal displacement of the second member relative to a reference position of the first member.

8. An aircraft engine comprising:
a propeller rotatable about a longitudinal axis and having blades with an adjustable blade angle;
a feedback ring coupled to the propeller to rotate with the propeller and to be displaced along the longitudinal axis with adjustment of the blade angle;
an engagement member configured to moveably engage the feedback ring and to be displaced along a longitudinal direction substantially parallel to the longitudinal axis with displacement of the feedback ring;
a sensor comprising a first member coupled to the aircraft engine and a second member coupled to the engagement member, the first member stationary and the second member moveable relative to the first member along the longitudinal direction as the engagement member is displaced, the sensor configured to generate a sensor signal indicative of a longitudinal position of the second member relative to the first member; and
a controller configured to receive the sensor signal and to determine an axial position of the feedback ring along the longitudinal axis based on the longitudinal position of the second member relative to the first member.

9. The engine of claim 8 , wherein the feedback ring has a channel formed around a circumference thereof.

10. The engine of claim 9 , wherein the engagement member is configured to be retained in the channel.

11. The engine of claim 10 , wherein the channel is u-shaped and the engagement member is a block.

12. The engine of claim 8 , wherein the sensor is a linear variable differential transformer, the first member comprising a plurality of solenoidal coils and the second member comprising a ferromagnetic core.

13. The engine of claim 8 , wherein the first member is secured to a gear box of the aircraft engine.

14. The engine of claim 9 , wherein the sensor is configured to generate the sensor signal indicative of a longitudinal displacement of the second member relative to a reference position of the first member.

15. A method for determining an axial position of a feedback ring of a propeller of an aircraft engine, the propeller rotatable about a longitudinal axis and having an adjustable blade angle and the feedback ring rotatable with the propeller, the method comprising:
displacing a moveable sensor member relative to a stationary sensor member, the stationary sensor member coupled to the aircraft engine and the moveable sensor member displaceable relative to the stationary sensor member along a longitudinal direction substantially parallel to the longitudinal axis as the feedback ring is displaced along the longitudinal axis;
receiving a sensor signal indicative of a longitudinal position of the moveable sensor member relative to the stationary sensor member; and
determining the axial position of the feedback ring along the longitudinal axis based on the longitudinal position of the moveable sensor member relative to the stationary sensor member as obtained from the sensor signal.

16. The method of claim 15 , wherein the sensor signal is indicative of a longitudinal displacement of the moveable sensor member relative to a reference position of the stationary sensor member.

17. The method of claim 16 , wherein the axial position of the feedback ring is determined based on the longitudinal displacement of the moveable sensor member relative to the reference position of the stationary sensor member.

18. The method of claim 15 , wherein the moveable sensor member comprises a ferromagnetic core of a linear variable differential transformer, and the stationary sensor member comprises a plurality of solenoidal coils of the linear variable differential transformer.

Assignees

• Pratt & Whitney Canada

Inventors

• Marone Joseph Ernesto
• Farrell Ian

Classifications

• B64C11/301 Primary

  characterised by blade position indicating means · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• F01D7/00

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

• F05D2260/76

  the adjusting mechanism using auxiliary power sources · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title