A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid subsystem operable to supply a fluid into the cooling passage. The thermal inspection system also includes a thermal camera subsystem operable to monitor a fluid temperature difference of the fluid exiting the cooling passage relative to the input temperature of the fluid supplied to the cooling passage.

A measurement system for measuring at least one thermal magnitude at a point of a propulsion assembly of an aircraft. The measurement system is connected to a structure integral with the propulsion assembly and comprises at least one thermal sensor as well as at least one barrier transparent to infrared radiation in at least one zone of the barrier. The barrier at least partially delimits a cavity in which the thermal sensor is positioned. Also an aircraft propulsion system with at least one such measurement system.

A device for measuring temperature of a turbine wheel in a turbocharger includes: a guide that passes infrared ray generated from the turbine wheel and includes a coolant path; a protection unit that protects an optical head which senses the infrared ray; and a signal processing unit that measures a temperature of the turbine wheel by processing a signal corresponding to the sensed infrared ray.

An infrared imaging device includes a case, a plurality of electronic components, and a heat transfer structure. The plurality of electronic components is configured to collect data and have a predetermined temperature parameter. The plurality of electronic components is disposed within the case. The heat transfer structure is disposed within the case. The heat transfer structure is configured to conduct heat away from the plurality of electronic components. The heat transfer structure is further configured to regulate a temperature of the electronic components below the predetermined temperature parameter.

A device for measuring surface-temperature of a turbine blade, the device including a probe having a front-end mirror for receiving infrared radiation of a surface on the blade, a collimation lens for refracted the infrared radiation, a PD detector to receive the infrared radiation, and a focal-length servo; and a radial-scanning servo connected to the probe. The front-end mirror, the collimation lens, and PD detector are disposed along the optical axis of the collimation lens. The focal-length servo is adapted to move the collimation lens along the optical axis of the collimation lens. The radial-scanning servo is adapted to move the probe along the optical axis of the collimation lens. The device of the invention is capable of accurately targeting a particular point on the blade having an irregular shape for temperature measurement to accurately detect the temperature distribution on the surface of the blade.

The temperature sensor includes a light pipe and a cap configured to be positioned within a flow path of a fluid. The cap includes a material configured to emit radiation based on a temperature of the material. A light source is configured to emit light through the light pipe toward the cap, and a detector is configured to receive the radiation emitted by the material of the cap and to generate a first signal based on the received radiation emitted by the material. The detector is configured to generate a second signal indicative of a light-induced delta temperature caused by the light emitted toward the inner surface of the cap. The system also includes a controller configured to determine a condition of the temperature sensor based on the first signal and the second signal.

An infrared imaging device includes a plurality of electronic components, a phase change material, and a heat transfer structure. The plurality of electronic components is configured to collect data and have a predetermined temperature parameter. The plurality of electronic components is disposed within the phase change material. The phase change material has a first material phase and a second material phase. The phase change material has a first material phase and a second material phase. The phase change material is configured to absorb heat through changing from the first material phase to the second material phase. The heat transfer structure is disposed within the phase change material. The heat transfer structure is configured to conduct heat within the phase change material. The phase change material and the heat transfer structure are further configured to regulate a temperature of the electronic components below the predetermined temperature parameter.

A system and method for prognostic health monitoring of thermal barrier coatings is provided. The system may comprise monitoring a thermal barrier coated gas turbine engine component, and measuring the infrared radiation emitting from the component. The measured thermal radiation data may be analyzed and compared to known material thermal radiation data in order to determine the health of the thermal barrier coating. The compiled comparison results may be compared against a historical statistical study to then determine the overall health of the thermal barrier coating. The system may comprise generating a health monitoring alert in response to the health of the thermal barrier coating indicating an imminent failure.

An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft aft of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.

A fuel nozzle for a gas turbine engine includes a feed arm including a fuel passage for issuing a spray of fuel. A nozzle assembly is fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage. A fiber optic cable is configured to collect burner radiation for a pyrometer input and has a first end centered within an optical connector of the nozzle assembly and a second end exposed from the spray outlet. The fiber optic cable fitted within the feed arm and nozzle assembly has a permanent bend radius preformed in the fiber optic cable. The bend radius can be equal to or greater than the minimum bend radii for the fiber optic cable to serve as a wave guide in wavelengths for monitoring combustion.