Proximity vane angle measurement

Patent metadata

Field	Value
Publication number	US-11021991-B2
Application number	US-201916428051-A
Country	US
Kind code	B2
Filing date	May 31, 2019
Priority date	May 31, 2019
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A measurement system for determining an angular position of a component of a gas turbine engine includes one or more proximity sensors positioned at a fixed structure of the gas turbine engine and one or more sensor targets positioned at a rotatable component of the gas turbine engine. Each sensor target of the one or more sensor targets includes a target surface having a variable distance between the target surface and the proximity sensor with rotation of the rotatable component about a component axis of rotation. A measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the rotatable component relative to the component axis of rotation.

First claim

What is claimed is:

1. A measurement system for determining an angular position of a component of a gas turbine engine, comprising:
one or more proximity sensors disposed at a fixed structure of the gas turbine engine; and
one or more sensor targets disposed at a rotatable component of the gas turbine engine, each sensor target of the one or more sensor targets including a target surface having a variable distance between the target surface and the proximity sensor with rotation of the rotatable component about a component axis of rotation;
wherein a measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the rotatable component relative to the component axis of rotation;
wherein the target surface is a curvilinear surface having one of a continuously variable or continuously increasing radial distance from the component axis of rotation.

2. The measurement system of claim 1 , wherein the radius is centered on the component axis of rotation.

3. The measurement system of claim 1 , wherein the one or more proximity sensors is at least two proximity sensors.

4. The measurement system of claim 3 , wherein the two or more proximity sensors are offset in a direction along the component axis of rotation.

5. The measurement system of claim 3 , wherein the two or more proximity sensors are offset circumferentially about the component axis of rotation.

6. The measurement system of claim 1 , wherein the target surface is formed integral to the rotatable component.

7. A variable pitch stator vane system of a gas turbine engine, comprising:
a plurality of stator vanes, each stator vane rotatable about a stator vane axis;
a synchronization ring operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes; and
a rotational position measurement system disposed at a stator vane of the plurality of stator vanes including:
one or more proximity sensors disposed at a fixed structure of the gas turbine engine; and
one or more sensor targets disposed at the stator vane, each sensor target of the one or more sensor targets including a target surface having a variable distance between the target surface and the proximity sensor with rotation of the stator vane about the stator vane axis;

wherein a measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the stator vane relative to the stator vane axis;
wherein the target surface is a curvilinear surface having one of a continuously variable or continuously increasing radial distance from the stator vane axis.

8. The variable pitch stator vane system of claim 7 , wherein the radius is centered on the stator vane axis.

9. The variable pitch stator vane system of claim 7 , wherein the one or more proximity sensors is at least two proximity sensors.

10. The variable pitch stator vane system of claim 9 , wherein the at least two proximity sensors are offset in a direction along the stator vane axis.

11. The variable pitch stator vane system of claim 9 , wherein the at least two proximity sensors are offset circumferentially about the stator vane axis.

12. The variable pitch stator vane system of claim 7 , wherein each stator vane is operably connected to the synchronization ring via a vane arm configured for rotation with the stator vane about the stator vane axis.

13. The variable pitch stator vane system of claim 12 , wherein the target surface is formed integral to the vane arm.

14. A gas turbine engine, comprising:
a turbine section;
a combustor section configured to drive rotation of the turbine; and
a compressor section, including:
a variable pitch stator vane system, including:
a plurality of stator vanes, each stator vane rotatable about a stator vane axis;
a synchronization ring operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes; and
a rotational position measurement system disposed at a stator vane of the plurality of stator vanes including:
one or more proximity sensors disposed at a fixed structure of the gas turbine engine; and
one or more sensor targets disposed at the stator vane, each sensor target of the one or more sensor targets including a target surface having a variable distance between the target surface and the proximity sensor with rotation of the stator vane about the stator vane axis;
wherein a measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the stator vane relative to the stator vane axis;
wherein the target surface is a curvilinear surface having one of a continuously variable or continuously increasing radial distance from the stator vane axis.

15. The gas turbine engine of claim 14 , wherein the radius is centered on the stator vane axis.

16. The gas turbine engine of claim 14 , wherein each stator vane is operably connected to the synchronization ring via a vane arm configured for rotation with the stator vane about the stator vane axis.

17. The gas turbine engine of claim 16 , wherein the target surface is formed integral to the vane arm.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Boudreau Daniel J
• Warren Eli Cole
• Hackett Bryan J

Classifications

• G01D5/241

  by relative movement of capacitor electrodes · CPC title

• G01D2205/776

  Cam-shaped profiles · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• F01D17/02

  Arrangement of sensing elements · CPC title

• F05D2260/74

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