Abstract: A system and method for thermal inspection of a component having at least one cooling hole is disclosed, that uses an evaporative membrane for direct evaporative cooling of an exhausted working fluid. A working fluid is supplied to at least one internal passage of a component that is configured to exhaust the working fluid from the internal passage sequentially through the cooling holes and the wetted evaporative membrane disposed in direct air-tight contact with the component. An imager captures a time series of images corresponding to a transient evaporative response of the exhausted working fluid to determine a plurality of temperature values for the exhausted working fluid after passage through the evaporative membrane. A processor circuit is configured to evaluate the transient evaporative response of the exhausted working fluid.

Abstract: A corrosion monitoring system includes at least one corrosion sensor. The corrosion sensor includes a metallic plug having at least one opening, at least one ceramic sheath in the opening of the metallic plug, and a plurality of probes. Each probe has a central portion with a predetermined cross sectional area extending from the metallic plug. The ceramic sheath electrically isolates each first end and each second end of the probes from the metallic plug and the other first ends and second ends. The probes are sized to provide a distribution of predetermined cross sectional areas of the central portions. The corrosion monitoring system also includes a resistance meter measuring an ohmic resistance for at least one of the probes and a computer determining a corrosion rate by correlating a rate of change of the ohmic resistance to the corrosion rate of the probe.

Abstract: A gas turbine process includes supplying a fuel to a gas turbine, combusting the fuel in the gas turbine with a hot gas path temperature reaching at least 1100° C. during operation of the gas turbine, and supplying an inhibition composition including at least one yttrium-containing inorganic compound to interact with the vanadium and inhibit vanadium hot corrosion in the gas turbine caused by vanadium as a fuel impurity in the fuel. A process includes supplying an inhibition composition including at least one yttrium-containing inorganic compound to a hot gas path or a combustor of a gas turbine. A fuel composition includes a fuel including at least one fuel impurity including vanadium and an inhibition composition including at least one yttrium-containing compound. An atomic ratio of yttrium to vanadium in the fuel composition is in a range of 1 to 1.5.

Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

Abstract: A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change.

Abstract: Laser cladding systems include a metal-filled wire comprising a metal shell surrounding a metal-filled core, wherein the metal-filled core comprises at least one of a powder metal or a fine wire metal, and, a laser that produces a laser beam directed onto at least a portion of a tip of the metal-filled wire to melt the metal shell and metal-filled core to produce a molten pool for depositing on a substrate.

Abstract: A thermally-controlled component and thermal control process are disclosed. The thermally-controlled component includes thermally-responsive features. The thermally-responsive features are configured to modify a flow path to control temperature variation of the thermally-controlled component. The thermally-responsive features deploy from or retract toward a surface of the thermally-controlled component in response to a predetermined temperature change. The thermal control process includes modifying the flow path in the thermally-controlled component to control temperature variation of the thermally-controlled component and/or cooling a region of the thermally-controlled component through the thermally-responsive features deploying from or retracting toward a surface of the thermally-controlled component.

Abstract: Coating methods and a coated substrate are provided. The coating method includes providing a component having an aperture formed in a surface thereof, arranging and disposing a hollow member on a portion of the surface to define a hollow space above the aperture corresponding to a shape of the aperture at the surface, applying at least one coating over the surface of the component and the hollow member to form an applied coating having an applied coating thickness, and removing at least a portion of the hollow member to expose the hollow space through the applied coating. The coated substrate includes a component having an aperture formed in a surface thereof, a hollow member arranged and disposed on the surface to define a hollow space above the aperture, and an applied coating over the surface of the component, the hollow space being exposed through the applied coating.

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: A corrosion sensor for an internal structure of a machine is provided. The corrosion sensor may include a test cap having at least one of a material and a geometry configured to fail faster than a material of the internal structure due to a corrosive influence. A mount secures the test cap in position in an opening in a portion of the machine that defines an operational environment. A chamber is adjacent the test cap and in at least one of the test cap and the mount. A failure in the test cap creates an environmental change in the chamber that indicates exceeding a corrosion threshold and can be sensed by, for example, a temperature or pressure change.

Abstract: A system for locating at least one surface feature, such as a cooling aperture, on a turbine component is provided. The system includes at least one feature marker configured for placement adjacent to the at least one surface feature. The system also includes at least one sensor configured for non-visual detection of the at least one feature marker. The system also includes a control device coupled to the at least one sensor for receiving signals from the at least one sensor, wherein the signals represent data indicative of one of a presence of the at least one feature marker and an absence of the at least one feature marker.

Abstract: A corrosion sensor for an internal structure of a machine is provided. The corrosion sensor may include a test cap having at least one of a material and a geometry configured to fail faster than a material of the internal structure due to a corrosive influence. A mount secures the test cap in position in an opening in a portion of the machine that defines an operational environment. A chamber is adjacent the test cap and in at least one of the test cap and the mount. A failure in the test cap creates an environmental change in the chamber that indicates exceeding a corrosion threshold and can be sensed by, for example, a temperature or pressure change.

Abstract: A method of forming a plurality of turbulators on a turbomachine surface includes depositing a portion of material on the turbomachine surface forming a first portion of the plurality of turbulators, adding additional material to the first portion, and establishing a desired dimension of the plurality of turbulators.

Abstract: A method for machining a shaft includes the step of machining a compound radius into the shaft at a junction between a radial surface of the shaft and an axial facing flange portion of the shaft. The compound radius has a curved surface with at least two different radii. The curved surface extends circumferentially around the shaft.

Abstract: A method for manufacturing a corrosion sensor includes spraying a non-conductive material on a substrate and spraying a conductive material at discrete locations on the substrate or on the non-conductive material. The method further includes spraying the non-conductive material around the discrete locations of the conductive material.

Abstract: A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material.

Abstract: A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material.

Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

Abstract: A components comprising a plurality of tab members formed thereon are provided. The plurality of tab members include at least one dissimilar metallic layer applied to the component. The plurality of tab members are configured to extend away from or retract toward a surface of the component in response to a temperature change.

Abstract: A refurbishing method, refurbishing apparatus and refurbished article are provided. The refurbishing method includes accessing a plurality of rotatable components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, providing a predetermined volume of a buffered electrolytic solution in an electro-polishing tank, coupling the plurality of rotatable components to a power supply, immersing an immersion portion of at least one of the plurality of rotatable components in the buffered electrolytic solution, passing an electrical energy through the immersion portion of at least one of the plurality of rotatable components while the immersion portion is immersed in the buffered electrolytic solution, wherein an electrical flux to the immersion portion electro-polishes the immersion portion, separating the immersion portion from the buffered electrolytic solution, and applying a corrosion inhibitor to the plurality of rotatable components.