Remote temperature measurement system for gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsUrcan Guler, Paul Sheedy, John A. Sharon, Wayde R. Schmidt
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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.
Claims12
A remote temperature measurement system comprising:
- a control system;
- an optical emitter/receiver in communication with the control system;
- and
- a probe system embedded within a component of a gas turbine engine, the probe system comprising a resonant probe embedded within the component and in communication with an optical port of the component via a waveguide, the optical port being 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 of the optical emitter/receiver with the probe system, wherein the resonant probe comprises thermographic phosphor film in which changes in temperature affects the luminescence of the thermographic phosphor film, and wherein the resonant probe comprises a nano/micro structured resonator.
A probe system embedded within a component of a gas turbine engine, comprising:
- a resonant probe embedded within the component;
- an optical port in a surface of the component;
- and
- a waveguide in communication with the resonant probe and the optical port, wherein the resonant probe further comprises a thermographic phosphor film in which changes in temperature affects the luminescence of the thermographic phosphor films and optical properties thereof, and wherein the resonant probe comprises a nano/micro-structured resonator.
A method for remote temperature measurement of a component within a gas turbine engine, comprising:
- embedding a probe system within an additively manufactured component of the gas turbine engine;
- optically communicating with the probe system from external of the component, through an optic port in the component and a waveguide leading from the optic port within the component to the probe system;
- and
- determining a local temperature of the component in response to optical communication with the probe system, wherein the probe system comprises a thermographic phosphor film, and wherein the step of optical communication with the probe system comprises determining a luminescence of the thermographic phosphor film in the probe system, and wherein the probe system comprises a resonant probe comprising a nano/micro structured resonator.
Dependencies are inferred from the claim text.