Remote temperature measurement system for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11859501-B2
Application number	US-202217946360-A
Country	US
Kind code	B2
Filing date	Sep 16, 2022
Priority date	Nov 11, 2019
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

A remote temperature measurement system for a gas turbine engine includes an optical emitter/receiver in communication with the control system and a probe system embedded within a component of the gas turbine engine, the probe system within a line-of-sight of the optical emitter/receiver, the control system operable to determine a local temperature of the component in response to optical communication with the probe system.

First claim

What is claimed is:

1. A remote temperature measurement system comprising:
a control system;
an optical emitter/receiver in communication with the control system; and
a probe system comprising a resonant probe embedded within a component of a gas turbine engine, an optical port on a surface of the component and in optical communication with the optical emitter/receiver, and a waveguide optically connecting the resonant probe to the optical port, whereby an optic signal emitted by the optical emitter/receiver passes through the optical port and the waveguide to the resonant probe, and a reflected optical signal travels from the resonant probe through the waveguide and the optical port back to the optical emitter/receiver, and wherein the control system is configured to determine a local temperature of the component from the reflected optical signal.

2. The system as recited in claim 1 , wherein the component is a rotor blade.

3. The system as recited in claim 1 , wherein the optical port is within a line-of-sight of the optical emitter/receiver.

4. The system as recited in claim 1 , wherein the resonant probe comprises thermographic phosphor film in which temperature of the thermographic phosphor film affects luminescence of the thermographic phosphor film.

5. The system as recited in claim 1 , wherein the resonant probe operates as an antenna for light.

6. The system as recited in claim 1 , wherein the resonant probe comprises a material designed for resonance in a desired spectral region.

7. The system as recited in claim 1 , wherein the resonant probe comprises dielectric materials designed for resonance in a desired spectral region.

8. The system as recited in claim 1 , wherein the component is additively manufactured.

9. The system as recited in claim 1 , wherein the resonant probe comprises a nano/micro-structured resonator.

10. The system as recited in claim 1 , wherein the resonant probe comprises dielectric materials designed for resonance in a spectral region of interest.

11. The system of claim 1 , wherein the resonant probe comprises a substrate having thermal properties matching material of the component, and at least one optical resonator on the substrate.

12. A method for remote temperature measurement of a component within a gas turbine engine, comprising:
operating the gas turbine engine having a probe system comprising a resonant probe embedded within a component of the gas turbine engine, an optical port on a surface of the component, and a waveguide optically connecting the resonant probe to the optical port;
optically communicating from outside of the component through the optical port and the waveguide to the resonant probe, the resonant probe generating a reflected optical signal that is conveyed back through the waveguide and the optical port; and
determining a local temperature of the component from the reflected optical signal.

13. The method as recited in claim 12 , wherein communication with the probe system comprises optical communication from a fixed location relative to the component.

14. The method as recited in claim 12 , wherein optical communication with the probe system comprises identifying a luminescence of a thermographic phosphor film of the resonant probe from the reflected optical signal.

15. The method as recited in claim 12 , wherein the reflected optical signal comprises at least one of luminescence data providing a detectable change in temporal response and reflection data providing a detectable change in spectral response.

16. The method as recited in claim 12 , wherein the component is an additively manufactured component, and wherein the probe system is embedded within the component during additive manufacturing.

17. The method as recited in claim 12 , further comprising conducting maintenance on the component based upon the reflected optical signal.

18. The method as recited in claim 12 , wherein the resonant probe comprises a nano/micro-structured resonator.

19. The method as recited in claim 12 , wherein the resonant probe comprises a substrate having thermal properties matching material of the component, and at least one optical resonator on the substrate.

Assignees

• Rtx Corp

Inventors

• Guler Urcan
• Sheedy Paul
• Sharon John A
• Schmidt Wayde R

Classifications

• F01D17/085 Primary

  to temperature · CPC title

• G01K11/20

  using thermoluminescent materials (G01K11/32 takes precedence) · CPC title

• G01K13/08 Primary

  in rotary movement · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F05D2270/303

  Temperature · CPC title