Abstract: Methods of making a component with an integral strain indicator and methods of monitoring such components are provided. A method for making a component includes forming the component, the component including an internal volume and an outer surface. The method further includes forming a plurality of fiducial markers on the component, wherein each of the plurality of fiducial markers is a depression defined in the component. The plurality of fiducial markers are positioned in an analysis region of the component.

Abstract: Systems for monitoring a component in a turbomachine can include a strain sensor comprising at least two reference points disposed on a surface of the component, and a data acquisition device connected to the turbomachine comprising a field of view, wherein the field of view is positioned to at least periodically capture the strain sensor on the component.

Abstract: Methods for manufacturing passive strain indicator on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points.

Abstract: This disclosure provides systems, components, and methods for visual creep inspection of rotating components, such as those in a gas turbine. A component is provided with an external surface and an axis of rotation. The external surface has a circumference and a plurality of three dimensional reference marks forming a reference pattern along the circumference. An optical data capture device generates a data signal based on the plurality of three dimensional reference marks. A data analysis system processes the data signal to calculate a deviation in spacing of the reference pattern along the circumference and determines a strain or creep measurement.

Abstract: A method of forming a passive strain indicator on a preexisting component includes directly depositing a plurality of fiducial markers on a portion of the outer surface of the preexisting component, the fiducial markers including a material that is compatible with the material of the outer surface. A method of evaluating a component includes initially scanning a plurality of fiducial markers on a portion of an outer surface of the component, subjecting the component to at least one duty cycle, subsequently scanning the plurality of fiducial markers after the at least one duty cycle, measuring a displacement of the plurality of fiducial markers by comparing the subsequent scan to the initial scan, and determining a remaining usable life of the component by looking up in a database a predetermined value of the remaining usable life of the component corresponding to the measured displacement of the plurality of fiducial markers.

Abstract: Methods of making a component with an integral strain indicator and methods of monitoring such components are provided. A method for making a component includes forming the component, the component including an internal volume and an outer surface. The method further includes forming a plurality of fiducial markers on the component, wherein each of the plurality of fiducial markers is a depression defined in the component. The plurality of fiducial markers are positioned in an analysis region of the component.

Abstract: A method of forming a passive strain indicator on a preexisting component includes directly depositing a plurality of fiducial markers on a portion of the outer surface of the preexisting component, the fiducial markers including a material that is compatible with the material of the outer surface. A method of evaluating a component includes initially scanning a plurality of fiducial markers on a portion of an outer surface of the component, subjecting the component to at least one duty cycle, subsequently scanning the plurality of fiducial markers after the at least one duty cycle, measuring a displacement of the plurality of fiducial markers by comparing the subsequent scan to the initial scan, and determining a remaining usable life of the component by looking up in a database a predetermined value of the remaining usable life of the component corresponding to the measured displacement of the plurality of fiducial markers.

Abstract: This disclosure provides systems, components, and methods for visual creep inspection of rotating components, such as those in a gas turbine. A component is provided with an external surface and an axis of rotation. The external surface has a circumference and a plurality of three dimensional reference marks forming a reference pattern along the circumference. An optical data capture device generates a data signal based on the plurality of three dimensional reference marks. A data analysis system processes the data signal to calculate a deviation in spacing of the reference pattern along the circumference and determines a strain or creep measurement.

Abstract: Systems for monitoring a component in a turbomachine can include a strain sensor comprising at least two reference points disposed on a surface of the component, and a data acquisition device connected to the turbomachine comprising a field of view, wherein the field of view is positioned to at least periodically capture the strain sensor on the component.

Abstract: Components can include a substrate and an array-based strain sensor disposed on the substrate, wherein the array-based strain sensor comprises a plurality of reference features distributed along both a first axis and a second axis to form at least a two-dimensional array.

Abstract: Methods for modifying components include disposing a ceramic material on an exterior surface of the component, wherein the component comprises a nickel-based or cobalt-based superalloy, and applying a local heat application to at least a portion of the ceramic material to bond it to the component, wherein the local heat application does not uniformly heat the entire component.

Abstract: Components can comprise a substrate, an embedded strain sensor comprising at least two reference points disposed on the substrate, and an outer coating disposed over at least a portion of the embedded strain sensor.

Abstract: Methods for modifying components include disposing a ceramic material on an exterior surface of the component, wherein the component comprises a nickel-based or cobalt-based superalloy, and applying a local laser application to at least a portion of the ceramic material to bond it to the component.

Abstract: Methods for manufacturing passive strain indicator on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points.

Abstract: Methods for manufacturing strain sensors on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a strain sensor comprising at least two reference points.

Abstract: Coating processes and coated components are disclosed. A coating process includes applying a suspension to an operationally-used surface, the suspension having one or more solvents, nano-materials, a plasticizer, a binder, and a dispersant suspending nano-materials within the suspension, applying heat to the suspension thereby removing liquids from the suspension, wherein solids are maintained on the surface after the applying of the heat, and sintering the solids on the surface to produce a coating. A coated component includes a substrate and a coating formed on the substrate by sintering of solids, the solids being positioned by application and heating of a suspension to an operationally-used surface, the suspension having one or more solvents, nano-materials, a plasticizer, a binder, and a dispersant suspending nano-materials within the suspension.

Abstract: Methods for manufacturing strain sensors on turbine components include providing a turbine component comprising an exterior surface, depositing a ceramic material onto a portion of the exterior surface, and ablating at least a portion of the ceramic material to form a strain sensor comprising at least two reference points.

Abstract: Methods for manufacturing strain sensors on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a strain sensor comprising at least two reference points.

Abstract: Methods for manufacturing strain sensors on turbine components include providing a turbine component comprising an exterior surface, depositing a ceramic material onto a portion of the exterior surface, and ablating at least a portion of the ceramic material to form a strain sensor comprising at least two reference points.