Relative position measurement

• US 10,436,056 B2
• Filed: 06/23/2015
• Issued: 10/08/2019
• Est. Priority Date: 06/23/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Prentice, Ian Francis
• Primary Examiner(s): Rivera, Carlos A
• Assistant Examiner(s): Corday, Cameron A
• Application Number:
  US14/747,114
• Publication Number:
  US 20160376912A1
• Time in Patent Office: 1,568 Days
• CPC Class Codes: F01D 17/02 Arrangement of sensing elements
• CPC Class Codes: F01D 17/12 arranged in stator parts
• CPC Class Codes: F04D 27/001 Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
• CPC Class Codes: F04D 29/323 adjustable
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2270/821 Displacement measuring means, e.g. inductive
• CPC Class Codes: G01B 7/30 for measuring angles or tapers; for testing the alignment of axes
• CPC Class Codes: G01D 5/20 by varying inductance, e.g. by a movable armature

Abstract

A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Claims

1. A feedback sensor system, the feedback sensor system comprising:

a shaft assembly rotatable about an axial direction;

a first ring coupled to or formed integrally with the shaft assembly, the first ring including a surface having one or more first ring features;

a second ring rotatable about the axial direction and enclosed within the shaft assembly, the second ring including a surface having one or more second ring features; and

a sensor spaced from the shaft assembly and the first ring and positioned on an opposite side of the shaft assembly than the second ring, the sensor directed at the surface of the first ring and the surface of the second ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features to determine a position of the first ring relative to the second ring;

wherein the surface of the first ring is a continuous surface along a circumferential direction, and wherein the surface of the second ring is also a continuous surface along the circumferential direction; and

wherein at least one of the surface of the first ring and the shaft assembly is positioned between the sensor and the surface of the second ring and substantially completely obstructs the surface of the second ring from a direct line of sight view of the sensor throughout the entire operation.

2. The feedback sensor system of claim 1, wherein the parameter is a magnetic flux.

3. The feedback sensor system of claim 1, wherein the one or more first ring features are a plurality of teeth spaced along the surface of the first ring, wherein the one or more second ring features are a plurality of teeth spaced along the surface of the second ring, and wherein the feedback sensor system is configured to determine an angular position of the first ring relative to the second ring.

4. The feedback sensor system of claim 1, wherein the one or more of first ring features are a plurality of teeth spaced along the surface of the first ring, wherein the one or more of second ring features are a plurality of helical ridges extending from the surface of the second ring, and wherein the feedback sensor system is configured to determine an axial position of the first ring relative to the second ring.

5. The feedback sensor system of claim 1, wherein the surface of the first ring further includes a marker having a geometry different than the plurality of first ring features for indicating a new revolution of the first ring.

6. The feedback sensor system of claim 5, wherein the marker and the one or more first ring features are evenly spaced along the surface of the first ring, and wherein the one or more second ring features are evenly spaced along the surface of the second ring.

7. The feedback sensor system of claim 1, wherein the feedback sensor system is configured for use with a gas turbine engine, wherein the first ring is configured to be mounted on a rotating shaft of the gas turbine engine, wherein the second ring is configured to be mounted on an actuation member of the gas turbine engine, the actuation member configured for changing a pitch of a fan blade of the gas turbine engine, and wherein the sensor is configured to be mounted on a stationary component of the gas turbine engine.

8. The feedback sensor system of claim 1, wherein the surface of the second ring has a different number of second ring features than the surface of the first ring has first ring features.

9. The feedback sensor system of claim 1, wherein the surface of the second ring has at least four less second ring features than the surface of the first ring has first ring features.

10. The feedback sensor system of claim 1, wherein the first ring is a continuous ring defining a thickness at each of the one or more first ring features that is greater than a thickness between each adjacent first ring features, and wherein the second ring is also a continuous ring defining a thickness through the one or more second ring features that is greater than a thickness between each adjacent second ring features.

11. The feedback sensor system of claim 1, wherein the sensor defines a sensing axis, and wherein the sensor is positioned such that the sensing axis extends through the surface of the first ring and the surface of the second ring.

12. The feedback sensor system of claim 1, wherein the surface of the first ring extends substantially parallel to the surface of the second ring such that the second ring is nested within the first ring.

13. The feedback sensor system of claim 1, wherein the first ring is positioned between the sensor and the shaft assembly.

14. The feedback sensor system of claim 1, wherein the shaft assembly is positioned between the sensor and the first ring.

15. A gas turbine engine defining an axial direction and a circumferential direction, the gas turbine engine comprising:

a turbine section mechanically coupled to a compressor section through a shaft;

a fan driven by the shaft, the fan including a plurality of fan blades;

an actuation member in mechanical communication with the plurality of fan blades for changing a pitch of the plurality of fan blades; and

a feedback sensor system including

a first ring coupled to or formed integrally with the shaft, the first ring including a surface having one or more first ring features;

a second ring rotatable with the actuation member of the gas turbine engine and enclosed within the shaft, the second ring including a surface having one or more second ring features; and

a sensor spaced from the shaft and the first ring and positioned on an opposite side of the shaft than the second ring, the sensor being directed at the surface of the first ring and the surface of the second ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features to determine a position of the first ring relative to the second ring;

wherein the surface of the first ring is a continuous surface along the circumferential direction, and wherein the surface of the second ring is also a continuous surface along the circumferential direction; and

wherein at least one of the surface of the first ring and the shaft assembly is positioned between the sensor and the surface of the second ring and substantially obstructs the surface of the second ring from a direct line of sight view of the sensor throughout the entire operation.

16. The gas turbine engine of claim 15, wherein the parameter is a magnetic flux.

17. The gas turbine engine of claim 15, wherein the one or more first ring features are a plurality of teeth spaced along the surface of the first ring, wherein the one or more second ring features are a plurality of teeth spaced along the surface of the second ring, and wherein the feedback sensor system is configured to sense an angular position of the first ring relative to the second ring.

18. The gas turbine engine of claim 15, wherein the one or more of first ring features are a plurality of teeth spaced along the surface of the first ring, wherein the one or more of second ring features are a plurality of helical ridges extending from the surface of the second ring, and wherein the feedback sensor system is configured to sense an axial position of the first ring relative to the second ring.