Abstract: A method for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The method includes providing an internally-cooled stationary vane (12). The method may further include locating at least one monitoring port (14) in the stationary vane and operatively connecting a monitoring instrument (16) to the monitoring port to provide a field of view of a region of interest.

Abstract: Apparatus and method for temperature mapping a rotating component (12) in a high temperature combustion environment. The apparatus includes a thermal imager (14) having a field of view to sense infrared (IR) emissions. Emissivity of a surface of the component is subject to variation in the combustion environment. A radiance emitter (18) defines a spot within the field of view of the thermal imager. The spot indicates a respective emissivity value. A processor (30) is connected to the thermal imager to generate a radiance map of the component based on the IR emissions from the component. The processor includes a thermal calibration module configured to calibrate the radiance map based on the emissivity value of the spot within the field of view of the thermal imager to generate a calibrated thermal map of the component that displays absolute temperature over the surface of the component.

Abstract: The monitoring system for a gas turbine engine including a viewing tube assembly having an inner end and an outer end. The inner end is located adjacent to a hot gas flow path within the gas turbine engine and the outer end is located adjacent to an outer casing of the gas turbine engine. An aperture wall is located at the inner end of the viewing tube assembly and an optical element is located within the viewing tube assembly adjacent to the inner end and is spaced from the aperture wall to define a cooling and purge chamber therebetween. An aperture is defined in the aperture wall for passage of light from the hot gas flow path to the optical element. Swirl passages are defined in the viewing tube assembly between the aperture wall and the optical element for passage of cooling air from a location outside the viewing tube assembly into the chamber, wherein swirl passages effect a swirling movement of air in a circumferential direction within the chamber.

Abstract: Methods for maximum scene surface temperature estimation for blades with reflective surface properties in advanced stationary gas turbines are disclosed. The approach utilizes high speed infrared imagery provided by an online monitor system using a focal plan array (FPA) for near-infrared monitoring during engine runtime up to base load. The one waveband method for temperature estimation is assumed as starting point. A lower surface emissivity and higher surface reflectance of thermal barrier coating (TBC) in near-infrared can cause systematic estimation errors. Methods using the one wave band method, with the purpose to reduce estimation errors for maximum temperatures are also disclosed. Theoretical results, data from numerical simulations, and real data from engine test are provided. A system for performing temperature estimation methods is also disclosed.

Abstract: Apparatus and method for temperature mapping a rotating component (12) in a high temperature combustion environment. The apparatus includes a thermal imager (14) having a field of view to sense infrared (IR) emissions. Emissivity of a surface of the component is subject to variation in the combustion environment. A radiance emitter (18) defines a spot within the field of view of the thermal imager. The spot indicates a respective emissivity value. A processor (30) is connected to the thermal imager to generate a radiance map of the component based on the IR emissions from the component. The processor includes a thermal calibration module configured to calibrate the radiance map based on the emissivity value of the spot within the field of view of the thermal imager to generate a calibrated thermal map of the component that displays absolute temperature over the surface of the component.

Abstract: Aspects of the invention are directed to a visual-based system and method for non-destructively evaluating an uncoated turbine engine component. Aspects of the invention are well suited for high speed, high temperature components. Radiant energy emitted from an uncoated turbine engine component can be captured remotely and converted into a useful form, such as a high resolution image of the component. A plurality of images of the component can be captured over time and evaluated to identify failure modes. The system can also measure and map the temperature and/or radiance of the component. The system can facilitate the non-destructive evaluation of uncoated turbine components during engine operation without disassembly of the engine, thereby providing significant time and cost savings. Further, the system presents data to a user with sufficient context that allows an engine operator can evaluate the information with an increased degree of confidence and certainty.

Abstract: An imaging system (110) for imaging a scene with a detector array (104) having an array of imaging elements is provided. The imaging system (110) includes an image estimation module (202) for generating a plurality estimates of uncorrupted images based upon a plurality of noisy images generated by the detector array (104). The imaging system (110) further includes a parameter determination module (204) for determining one or more nonuniformity correction parameters based upon the estimates of uncorrupted images.

Abstract: An inspection system formed at least from a viewing tube for inspecting aspects of a turbine engine during operation of the turbine engine. An outer housing of the viewing tube may be positioned within a turbine engine using at least one bearing configured to fit into an indentation of a support housing to form a ball and socket joint enabling the viewing tube to move during operation as a result of vibrations and other movements. The viewing tube may also include one or more lenses positioned within the viewing tube for viewing the turbine components. The lenses may be kept free of contamination by maintaining a higher pressure in the viewing tube than a pressure outside of the viewing tube and enabling gases to pass through an aperture in a cap at a viewing end of the viewing tube.