Abstract: 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.

Abstract: 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.

Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.

Abstract: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.

Abstract: According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

Abstract: 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.

Abstract: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.

Abstract: According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates.

Abstract: 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.

Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.

Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates.

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.

Abstract: Apparatus for reducing the total pressure of a compressible fluid fuel. The apparatus includes at least two closely spaced apart constant enthalpy expansion sections, each section having at least one orifice, the orifices in adjacent sections being noncoaxial. The pressure reduction lowers flow velocity when mixed with the air to below the flame speed to promote ignition and stable combustion.

Abstract: There is provided a water-hydrocarbon mixture. In one example, the mixture includes low-molecular weight hydrocarbon and between about 5% and about 70% water. The mixture is in the gaseous state, and is at a pressure that is below the critical pressure of the mixture. The mixture temperature is above about 28° C. less than the boiling point temperature of water at the mixture pressure and is below about 450° C. The mixture provides a local environment of water molecules, tending to limit hydrocarbon polymerization and other undesirable side reactions and keeping the hydrocarbon from precipitating from the mixture, for a faster, more complete combustion cycle characterized by lower emissions of carbon monoxide, unburned hydrocarbons, and volatile organic and polyaromatic hydrocarbons. The hydrocarbon preferably includes hydrocarbon micro-droplets of a diameter of no more than about 1 &mgr;m.