A temperature measurement system includes at least one temperature measurement probe. The at least one temperature measurement probe includes at least one hollow filament configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one hollow filament. The at least one hollow filament has a first diameter and a first emissivity. The at least one temperature measurement probe also includes at least one thin filament extending within at least a portion of the at least one hollow filament. The at least one thin filament is configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one thin filament. The at least one thin filament has a second emissivity and a second diameter less than the first diameter.

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

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.

A measurement and reconstruction method for a turbine blade strain field of with integrates an imaging technology and an infrared photoelectric measurement technology. The imaging technology is mainly responsible for the measurement of the strain field on a target blade surface, so as to use a digital image processing technology to obtain blade strain field data. The infrared photoelectric measurement technology is mainly aimed at the strain at blade edges, which uses temperature difference between the blade edges and blade gaps to perform strain measurement. Measurement results of the two modes are finally converted into blade strain parameters, thereby reconstructing the target blade strain field based on host computer software.

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.

An inspection system includes one or more processors and an infrared (IR) camera operably coupled to the one or more processors. The one or more processors control a microwave transmitter to sequentially emit microwaves having different frequencies within a designated frequency range into an object during a first sweep. The IR camera generates thermal image data of the object after the object is heated by each of the different frequencies of microwaves. The one or more processors analyze the thermal image data and determine a selected frequency within the designated frequency range that provides greater heating of the object than one or more other frequencies in the designated frequency range. The one or more processors also analyze select thermal image data of the object, responsive to heating of the object by the selected frequency of microwaves, to detect an element in the object.

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 method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.

A method of detecting damage to a gas turbine engine, the method including observing a thermal response of the engine during a thermal transition occurring when the engine transitions between an elevated temperature and a lesser temperature; determining potential damage to the gas turbine engine based on the observed thermal response of the gas turbine engine; and generating an action in response to the determined potential damage to the gas turbine engine.

Systems and methods disclosed herein use a multi-color pyrometer configured to determine a first temperature in a high temperature range and a single-color pyrometer configured to determine second temperature in a low temperature range. The system uses information gained from determination of the first temperature in the high temperature range to facilitate later determining the second temperature in the low temperature range. The first temperature in the high temperature range and the second temperature in the low temperature range are used to monitor and control different engine operations that occur at different times.