Abstract: Non-destructive inspection systems (10) and methods for inspecting structural flaws that may be in a structure (15) based on guided wave thermography. The method may include sweeping a frequency-phase space to maximize ultrasonic energy distribution across the structure while minimizing input energy, e.g., via a plurality of actuators. The system may include transducer elements (12, 14, 16, 17) configured to predominantly generate shear horizontal-type guided waves in the structure to maximize thermal response from any flaws.

Abstract: Non-destructive inspection systems (10) and methods for inspecting structural flaws that may be in a structure (15) based on guided wave thermography. The method may include sweeping a frequency-phase space to maximize ultrasonic energy distribution across the structure while minimizing input energy, e.g., via a plurality of actuators. The system may include transducer elements (12, 14, 16, 17) configured to predominantly generate shear horizontal-type guided waves in the structure to maximize thermal response from any flaws.

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: A thermal imaging system that detects the growth of cracks in a structural element, where the system has particular application for detecting the growth of cracks and similar defects in a turbine blade. The thermal imaging system includes at least one infrared (IR) fiber optic cable where a sensing end of the fiber optic cable is positioned in close proximity to a location where a crack in the structural element may occur. Infrared emissions generated as a result of crack growth are collected by the IR fiber cable and transmitted by the cable to an infrared monitoring device. The amount of heat that is detected provides an indication of whether the crack is growing, and if so, at what rate.

Abstract: A system and a method for image acquisition suitable for use in a turbine engine are disclosed. Light received from a field of view in an object plane is projected onto an image plane through an optical modulation device and is transferred through an image conduit to a sensor array. The sensor array generates a set of sampled image signals in a sensing basis based on light received from the image conduit. Finally, the sampled image signals are transformed from the sensing basis to a representation basis and a set of estimated image signals are generated therefrom. The estimated image signals are used for reconstructing an image and/or a motion-video of a region of interest within a turbine engine.

Abstract: Apparatus and method for determining a two-dimensional temperature distribution in a cross-sectional path of a hot-temperature flow in a turbine engine (10). A grid (22, 24, 38) is located in a path of a hot-temperature flow in the turbine engine. A thermal imager (34) has a field of view configured to sense infrared emissions from the grid. A processor (50) is configured to generate data indicative of a two-dimensional temperature distribution in a cross-sectional path of the flow based on the sensed infrared emissions.

Abstract: Methods and systems (10) based on guided wave thermography for non-destructively inspecting structural flaws that may be present in a structure (15). For example, such systems and methods may provide the ability to selectively deliver sonic or ultrasonic energy to provide focusing and/or beam steering throughout the structure from a fixed transducer location (12, 14, 16). Moreover, such systems and methods may provide the ability to selectively apply sonic or ultrasonic energy having excitation characteristics (FIGS. 11 and 12) which may be uniquely tailored to enhance the thermal response (FIGS. 5 and 7) of a particular flaw geometry and/or flaw location.

Abstract: Computerized methodology for organizing and/or retrieving pixel data for rendering digital images In one embodiment, the method may include transforming (12) an image depicting an object from an image-searchable domain to a pixel-searchable domain by way of spatial and temporal registration assigned to pixels forming the image The method may further include storing (14) pixel data including the spatial and temporal registration in an electronic storage Pixel data may be retrieved (16) from the electronic storage based on the assigned spatial and temporal registration An image may be reconstituted (18) with the retrieved pixel data This methodology may be used in a broad array of technical fields, such as for inspections of components of a turbine engine, medical imaging applications, ecological and biodiversity applications, etc.

Abstract: In an optical probe (10) having an inner tube (30) arranged to house one or more optical elements (32), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections (32, 34) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections (32, 34) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.

Abstract: A thermal imaging system that detects the growth of cracks in a structural element, where the system has particular application for detecting the growth of cracks and similar defects in a turbine blade. The thermal imaging system includes at least one infrared (IR) fiber optic cable where a sensing end of the fiber optic cable is positioned in close proximity to a location where a crack in the structural element may occur. Infrared emissions generated as a result of crack growth are collected by the IR fiber cable and transmitted by the cable to an infrared monitoring device. The amount of heat that is detected provides an indication of whether the crack is growing, and if so, at what rate.

Abstract: Computerized methodology for organizing and/or retrieving pixel data for rendering digital images In one embodiment, the method may include transforming (12) an image depicting an object from an image-searchable domain to a pixel-searchable domain by way of spatial and temporal registration assigned to pixels forming the image The method may further include storing (14) pixel data including the spatial and temporal registration in an electronic storage Pixel data may be retrieved (16) from the electronic storage based on the assigned spatial and temporal registration An image may be reconstituted (18) with the retrieved pixel data This methodology may be used in a broad array of technical fields, such as for inspections of components of a turbine engine, medical imaging applications, ecological and biodiversity applications, etc.

Abstract: Apparatus and method for determining a two-dimensional temperature distribution in a cross-sectional path of a hot-temperature flow in a turbine engine (10). A grid (22, 24, 38) is located in a path of a hot-temperature flow in the turbine engine. A thermal imager (34) has a field of view configured to sense infrared emissions from the grid. A processor (50) is configured to generate data indicative of a two-dimensional temperature distribution in a cross-sectional path of the flow based on the sensed infrared emissions.

Abstract: A system (8) for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The system includes an internally cooled stationary vane (12) located in a path of a working gas of the turbine. A monitoring port (14) is located in the stationary vane. A monitoring instrument (16) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.

Abstract: A method for non-destructive evaluation of an article of manufacture (30) by coating the article with a temperature-sensitive coating (34), stimulating the article with energy (18) to induce temperature changes in the article responsive to features of the article, then evaluating (24) a resulting topography of energy-induced changes (50, 52, 53) in the coating (34). The energy imparted to the article may be, for example, electromagnetic, magnetic, or sonic energy that produces localized changes in temperature in the article (30) in response to features (32) of the article such as flaws or other discontinuities. The coating (34) may be a suspension of liquid crystals in a liquid, and the energy may be an application of sonic energy. The coating may be a material that hardens (42, 54) or softens (44, 56) upon a slight increase in temperature. Layers (34, 35) of different energy-sensitive coatings (38, 40) may be applied to indicate different aspects of features of the article.

Abstract: In an optical probe (10) having an inner tube (30) arranged to house one or more optical elements (32), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections (32, 34) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections (32, 34) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.

Abstract: A system and a method for image acquisition suitable for use in a turbine engine are disclosed. Light received from a field of view in an object plane is projected onto an image plane through an optical modulation device and is transferred through an image conduit to a sensor array. The sensor array generates a set of sampled image signals in a sensing basis based on light received from the image conduit. Finally, the sampled image signals are transformed from the sensing basis to a representation basis and a set of estimated image signals are generated therefrom. The estimated image signals are used for reconstructing an image and/or a motion-video of a region of interest within a turbine engine.

Abstract: A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil.

Abstract: Methods and systems (10) based on guided wave thermography for non-destructively inspecting structural flaws that may be present in a structure (15). For example, such systems and methods may provide the ability to selectively deliver sonic or ultrasonic energy to provide focusing and/or beam steering throughout the structure from a fixed transducer location (12, 14, 16). Moreover, such systems and methods may provide the ability to selectively apply sonic or ultrasonic energy having excitation characteristics (FIGS. 11 and 12) which may be uniquely tailored to enhance the thermal response (FIGS. 5 and 7) of a particular flaw geometry and/or flaw location.

Abstract: A diagnostic system and method for monitoring operating conditions of turbine machine components (18, 19, 22, 23) that comprise one or more non-contact sensors (24, 31) that detect an operating condition of a turbine component (18, 19, 22, 23) over a defined region of the component. In addition, point sensors (50) are provided that detect and monitor the same operating condition within the defined region. Data generated from the point sensor (50) is used to calibrate the non-contact sensor (24, 31) and the data generated by the non-contact sensor (24, 31).

Abstract: An imaging system for on-line imaging of a component in a gas turbine engine. The imaging system includes a flexible imaging bundle formed by a plurality of optical elements. An imaging end of the optical elements images a component in a hot gas path of the engine during operation of the engine and a viewing end provides an image of the component at a location displaced from the hot gas path. The optical elements are surrounded by a flexible metal sheath that is permeable to air to provide cooling air the optical elements from an air source surrounding the flexible imaging bundle.