Turbine engine shaft torque sensing

Patent metadata

Field	Value
Publication number	US-10450863-B2
Application number	US-201615171359-A
Country	US
Kind code	B2
Filing date	Jun 2, 2016
Priority date	Jun 2, 2016
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may be positioned on the gas turbine engine shaft and electrically connected with the first sensor module. The second coupler may be positioned on the gas turbine engine shaft and electrically connected with the second sensor module. The static antenna may include a first band and a second band. The first signal band may be in operable communication with the first sensor module and positioned radially outward from the first coupler. The second signal band may be in operable communication with the second sensor module and positioned radially outward from the second coupler.

First claim

What is claimed is:

1. A system for measuring torque for a gas turbine engine shaft, the gas turbine engine shaft defining a central axis in an axial direction, the system comprising:
a first sensor module including a strain sensor positioned on the gas turbine engine shaft;
a second sensor module including a strain sensor positioned on the gas turbine engine shaft separate from the first sensor module;
a first coupler positioned on the gas turbine engine shaft and electrically connected with the first sensor module;
a second coupler positioned on the gas turbine engine shaft and electrically connected with the second sensor module;
a static antenna for redundant signal transmission, the static antenna including
a first signal band in operable communication with the first sensor module and positioned radially outward from the first coupler, and
a second signal band in operable communication with the second sensor module and positioned radially outward from the second coupler;

a controller operably connected to the static antenna for receiving a signal therefrom;
a first remote memory storage unit in operable communication between the static antenna and the controller; and
a first wiring path between the static antenna and the controller, wherein the first remote memory storage unit is disposed along the first wiring path.

2. The system of claim 1 , further comprising:
an electromagnetic shield disposed between the first coupler and the second coupler in the axial direction for hampering signal communication between the first coupler and the second coupler.

3. The system of claim 1 , wherein the strain sensor of the first sensor module is high-frequency surface acoustic wave (SAW) sensor configured to operate at a first frequency, and wherein the strain sensor of the second sensor module is a low-frequency SAW sensor configured to operate at a second frequency, the second frequency being lower than the first frequency.

4. The system of claim 1 , wherein the first sensor module includes a primary high-frequency surface acoustic wave (SAW) sensor and a secondary low-frequency SAW sensor, and wherein the second sensor module includes a primary high-frequency SAW sensor and a secondary low-frequency SAW sensor.

5. The system of claim 1 , wherein the strain sensor of the first sensor module includes a first strain resonator, a second strain resonator, and a temperature resonator, and wherein the strain sensor of the second sensor module includes a strain resonator and a temperature resonator.

6. The system of claim 1 , wherein the first sensor module includes a protective housing enclosing the strain sensor of the first sensor module, and wherein the second sensor module includes a protective housing enclosing the strain sensor of the second sensor module.

7. The system of claim 1 , further comprising:
a second remote memory storage unit in operable communication between the static antenna and the controller; and
a second wiring path between the static antenna and the controller, the second wiring path being electromagnetically isolated from the first wiring path.

8. The system of claim 7 , wherein the second remote memory storage unit is disposed along the second wiring path, and wherein the first remote memory storage unit and the second remote memory storage unit store calibration information for the first sensor module and the second sensor module.

9. A gas turbine engine defining a central axis in an axial direction, the gas turbine engine comprising:
an engine shaft extending along the central axis;
a turbine attached to the engine shaft for providing rotation thereto;
a first sensor module including a strain sensor positioned on the engine shaft;
a second sensor module including a strain sensor positioned on the engine shaft separate from the first sensor module;
a first coupler positioned on the engine shaft and electrically connected with the first sensor module;
a second coupler positioned on the engine shaft and electrically connected with the second sensor module; and
a static antenna for redundant signal transmission, the static antenna including
a first signal band in operable communication with the first sensor module and positioned radially outward from the first coupler, and
a second signal band in operable communication with the second sensor module and positioned radially outward from the second coupler;

a controller operably connected to the static antenna for receiving a signal therefrom;
a first remote memory storage unit in operable communication between the static antenna and the controller; and
a first wiring path between the static antenna and the controller, wherein the first remote memory storage unit is disposed along the first wiring path.

10. The gas turbine engine of claim 9 , further comprising:
a static frame member enclosing at least a portion of the engine shaft;
an output drive assembly disposed radially inward from the static frame member, wherein the static antenna is housed within the output drive assembly; and
a blind mate connector, including a selectively-coupled first mated segment and second mated segment, the first mated segment being attached to the output drive assembly and the second mated segment being attached to the static frame member.

11. The gas turbine engine of claim 9 , further comprising;
an electromagnetic shield disposed between the first coupler and the second coupler in the axial direction.

12. The gas turbine engine of claim 9 , wherein the first sensor module is a high-frequency surface acoustic wave (SAW) sensor configured to operate at a first frequency, and wherein the second sensor module is a low-frequency SAW sensor configured to operate at a second frequency, the second frequency being lower than the first frequency.

13. The gas turbine engine of claim 9 , wherein the first sensor module includes a primary high-frequency surface acoustic wave (SAW) sensor and a secondary low-frequency SAW sensor, and wherein the second sensor module includes a primary high-frequency SAW sensor and a secondary low-frequency SAW sensor.

14. The gas turbine engine of claim 9 , wherein the strain sensor of the first sensor module includes a first strain resonator, a second strain resonator, and a temperature resonator, and wherein the strain sensor of the second sensor module includes a strain resonator and a temperature resonator.

15. The gas turbine engine of claim 9 , wherein the engine shaft includes a power take-off shaft, a low pressure turbine shaft, a high pressure turbine shaft, a fan shaft, or an engine coupling shaft.

16. The gas turbine engine of claim 9 , wherein the first sensor module includes a protective housing enclosing the strain sensor of the first sensor module, and wherein the second sensor module includes a protective housing enclosing the strain sensor of the second sensor module.

17. The gas turbine engine of claim 9 , further comprising:
a second remote memory storage unit in operable communication between the static antenna and the controller; and
a second wiring path between the static antenna and the controller, the second wiring path being electromagnetically isolated from the first wiring path.

18. The gas turbine engine of claim 17 , wherein the second remote memory storage unit is disposed along the second wiring path, and wherein the first remote memory storage unit and the second remote memory storage unit store calibration information for the first sensor module and the second sensor module.

Assignees

• Gen Electric

Inventors

• Jacobs Douglas Scott
• Knobloch Aaron Jay
• Goeller Robert Edward
• Muhammad Mudassar Ali
• Iannotti Joseph Alfred

Classifications

• F05D2220/32

  in gas turbines · CPC title

• G01L3/108

  involving resistance strain gauges · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/60

  Shafts · CPC title