A method of imaging a turbine engine component with a first surface and a second surface that is spaced from the first surface. The turbine engine component includes a plurality of holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes determining at least one fluid frequency, determining at least one sampling frequency, and pulsing fluid through at least a portion of the interior of turbine engine component while imaging the turbine engine component.

A temperature measuring system is disclosed herein. The temperature measuring system includes an optical assembly and a spectral data receiver. The temperature measuring system views passing gas and measures the radiant response of a selected gas. The measurement includes radiant intensities with respect to wavelengths in the infrared region.

A four-shaft panoramic scanning temperature measuring device with a circulating water-cooling device is provided, which not only improves the working reliability of the probe, but also increases the overall flexibility and scanning measurement efficiency. The circulating water-cooling device is self-cooled. Compared with the conventional single-circulation water-cooling way, the design of five cooling cavities can achieve higher circulating water-cooling efficiency. The four-shaft structure includes a shaft structure for translation, a shaft structure for rotation, a shaft structure for swinging, and a shaft structure with coaxial sight pipe and light pipe. The design of the four-shaft structure is able to panoramically scan the high-temperature components inside the turbine. The temperature measuring device integrates functions of cooling, swinging, translating and rotating together, which solves problems of large size and complex control of the conventional temperature measuring device.

A system and method for determining the condition of a thermal barrier coating on a base metal component, comprising the use of an induction coil to input into the metallic base layer through the coating layer, a temporally varying heat waveform, and measuring the temperature of the coating surface layer resulting from the input of the heat waveform using a temperature sensor disposed close to the surface of the coating layer. A controller correlates a signal from the temporally varying output of the temperature sensor with a signal corresponding to the temporally varying heat waveform, to determine the phase angle between the signals. The controller uses a mathematical relationship between the phase angle and the frequency of the heat waveform to determine the thermal properties of the non-metallic coating. Both the thermal diffusivity and the barrier coating thickness can be accurately obtained by this method and apparatus.

An optical probe with high stability for measurement of radiation information of a turbine disk of an aeroengine includes a one-piece outer casing, a pressing ring, a sapphire window piece, an inner spacer, an outer spacer, a lens, first fixing nuts, second fixing nuts, fixing ropes and fixing screws. The one-piece outer casing is made from GH3044 solid solution strengthened nickel-based antioxidant alloy. An interior of the probe is divided into eight parts, which are as follows from a proximal hot end to a right end of the probe in sequence: a pressing ring chamber, a cold air vent, a sapphire window piece chamber, an outer spacer fixing chamber, a lens chamber, a beam chamber, a beam focusing chamber, and an optical fiber chamber.

A four-shaft panoramic scanning temperature measuring device with a circulating water-cooling device is provided, which not only improves the working reliability of the probe, but also increases the overall flexibility and scanning measurement efficiency. The circulating water-cooling device is self-cooled. Compared with the conventional single-circulation water-cooling way, the design of five cooling cavities can achieve higher circulating water-cooling efficiency. The four-shaft structure includes a shaft structure for translation, a shaft structure for rotation, a shaft structure for swinging, and a shaft structure with coaxial sight pipe and light pipe. The design of the four-shaft structure is able to panoramically scan the high-temperature components inside the turbine. The temperature measuring device integrates functions of cooling, swinging, translating and rotating together, which solves problems of large size and complex control of the conventional temperature measuring device.

An 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.

An infrared temperature-measurement probe, including: a probe housing; a reflector; and a reflector adjusting mechanism. The probe housing includes an inner wall, an outer wall, a cooling channel sandwiched between the inner wall and the outer wall, a chamber surrounded by the inner wall, and a light transmission hole communicating with the chamber. The reflector includes a mirror and a mirror frame. The reflector adjusting mechanism includes a motion controller, a drive coupling, and three control rods. The reflector and the three control rods are disposed in the chamber of the probe housing. The motion controller is disposed outside the chamber of the probe housing. The drive coupling is disposed between the motion controller and the three control rods, and the motion controller is adapted to move each of the three control rods via the drive coupling. The mirror is imbedded in and is supported by the mirror frame.

A device for measuring surface temperature of a turbine blade based on a rotatable prism includes a probe, a prism rotating apparatus and an optical focusing apparatus. The prism rotating apparatus and the optical focusing apparatus are located inside the probe. The probe includes a probe outer casing, a probe inner casing, a water-cooled casing pipe, a sapphire window piece, a quartz prism, a light pipe, a collimating lens, a focusing lens and an infrared array detector. The prism rotating apparatus includes a rotary motor, a worm, a gear and a prism rotary table, the rotary motor rotates to drive the prism rotary table to rotate. The optical focusing apparatus includes a telescopic motor, a coupler, a lead screw and a drive rod, the telescopic motor rotates to drive the lead screw, so as to further drive the drive rod to move along the slot.