Abstract: A method of cleaning a component within a turbine that includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component.

Abstract: A turbine engine cleaning system includes a foam generator configured to generate foam, from a liquid detergent, to clean a turbine engine. The turbine engine cleaning system also includes an effluent capture and detergent regeneration sub-system having an inlet configured to receive an effluent from the turbine engine, processing components configured to process the effluent to regenerate a liquid detergent, and an outlet fluidly coupled with the foam generator to enable transport of the liquid detergent from the effluent capture and detergent regeneration sub-system to the foam generator.

Abstract: A wash system for a gas turbine engine includes a foam generating device configured for receiving and aerating a flow of wash fluid to generate a flow of foamed wash fluid having particular foam characteristics. The flow of foamed wash fluid passes through a distribution manifold where it is selectively directed through a plurality of wash lines to desired portions of the gas turbine engine. The wash system further includes a controller configured for manipulating the foam characteristics of the flow of foamed wash fluid and using the distribution manifold to selectively direct the flow of foamed wash fluid to desired portions of the gas turbine engine for optimal cleaning and improved engine efficiency.

Abstract: The present disclosure provides methods and systems of generating flows of detergent through a turbine engine to effectuate cleaning of components thereof. The methods include introducing a foamed, acid-including detergent with a pH range of between 2 and 7 into a gas flowpath of the turbine engine. The methods also include creating a pressure differential in an aft portion of the gas flowpath with respect to a forward portion of the gas flowpath to generate a flow of the detergent therethrough. The methods further include creating a pressure differential in a forward portion of the gas flowpath with respect to an aft portion of the gas flowpath to generate a counterflow of the detergent therethrough. The flow and counterflow of the detergent through the gas flowpath interact with components of the turbine engine having foreign material thereon to at least partially remove the foreign material therefrom.

Abstract: A method for cleaning components of a gas turbine engine is presented. The method includes introducing a working fluid into a gas flow path or a cooling circuit defined by the one or more components of the gas turbine engine such that the working fluid impinges upon a surface of the one or more components of the gas turbine engine, wherein the working fluid includes a plurality of detergent droplets entrained in a flow of steam. A system for cleaning components of a gas turbine engine are also presented.

Abstract: Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

Abstract: A method for inspecting a gas turbine engine using a maintenance tool includes assembling a plurality of rail segments of a rail system of the maintenance tool within a core air flowpath of the gas turbine engine. The gas turbine engine includes a compressor section, a combustion section, and a turbine section together defining at least in part the core air flowpath. The method also includes moving a maintenance head of the maintenance tool along the plurality of rail segments of the rail system to perform maintenance operations within the core air flowpath of the gas turbine engine.

Abstract: An atomizing spray device includes a housing having plural inlets and one or more outlets fluidly coupled with each other by an interior chamber. The inlets include a first inlet shaped to receive a first fluid and a second inlet shaped to receive a slurry of ceramic particles and a second fluid. The interior chamber in the housing is shaped to mix the first fluid received via the first inlet with the slurry received via the second inlet inside the housing to form a mixture in a location between the inlets and the one or more outlets. The interior chamber in the housing also is shaped to direct the mixture formed inside the housing as droplets outside of the housing via the one or more outlets such that, based on a discharged amount of the first fluid in the droplets, the first fluid promotes evaporation of the second fluid as the droplets traverse from the housing toward a surface of a component.

Abstract: A coated component, along with methods of its formation, restoration, and use, is provided. The coated component may include a substrate defining a surface; a thermal barrier coating on the surface of the substrate; a layer of environmental contaminant compositions (e.g., CMAS) on the thermal barrier coating; and a chemical barrier coating on the layer of environmental contaminant compositions.

Abstract: Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least one aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

Abstract: An article includes a substrate that is substantially opaque to visible light and a coating disposed on the substrate. The coating includes a coating material having an inherent index of refraction, wherein the coating has an effective index of refraction that is less than the inherent index of refraction, and wherein the effective index of refraction is less than 1.8.

Abstract: The present disclosure is directed to a system and method for in-situ (e.g. on-wing) cleaning of gas turbine engine components. The method includes injecting a dry cleaning medium into the gas turbine engine at one or more locations. The dry cleaning medium includes a plurality of abrasive microparticles. Thus, the method also includes circulating the dry cleaning medium through at least a portion of the gas turbine engine such that the abrasive microparticles abrade a surface of the one or more components so as to clean the surface.

Abstract: The present disclosure is directed to a method for in-situ (e.g. on-wing) cleaning one or more components of a gas turbine engine. The method includes injecting a dry detergent into the gas turbine engine. Further, the dry detergent contains a plurality of detergent particles having varying particle sizes. More specifically, the plurality of detergent particles includes a first set of particles having a median particle diameter within a first micron range and a second set of particles having a median particle diameter within a second micron range. Further, a median of the second micron range is larger than a median of the first micron range. In addition, the method includes circulating the dry detergent through at least a portion of the gas turbine engine so as to clean the one or more components thereof.

Abstract: The present disclosure is directed to a method for in-situ cleaning one or more components of a gas turbine engine using an abrasive gel detergent. More specifically, the gel detergent includes a plurality of abrasive particles suspended in a gel composition. Further, the abrasive particles include organic material. Moreover, the gel composition is formed of a mixture of detergent particles dissolved in a gel reactant. Thus, the method includes injecting the gel detergent into at least a portion of the gas turbine engine at a predetermined pressure. In addition, the method includes allowing the gel detergent to flow across or within one or more of the components of the gas turbine engine so as to clean one or more of the components.

Abstract: Embodiments in accordance with the present disclosure include a meta-stable detergent based foam generating device of a turbine cleaning system includes a manifold configured to receive a liquid detergent and an expansion gas, a gas supply source configured to store the expansion gas, and one or more aerators fluidly coupled with, and between, the gas supply source and the manifold. Each aerator of the one or more aerators comprises an orifice through which the expansion gas enters the manifold, and wherein the orifice of each aerator is sized to enable generation of a meta-stable detergent based foam having bubbles with bubble diameters within a range of 10 microns (3.9×10?4 inches) and 5 millimeters (0.2 inches), having a half-life within a range of 5 minutes and 180 minutes, or a combination thereof.

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

Abstract: An apparatus for enhancing the coalescence of a dispersed phase from a continuous phase in an emulsion is presented. The apparatus includes at least one inlet for receiving the emulsion, at least one outlet for discharging the emulsion after coalescing the dispersed phase, and at least one article disposed between the inlet and the outlet. The article includes a plurality of regions disposed on a surface in a predefined pattern, wherein a portion of the plurality of regions is substantially wetting with respect to the dispersed phase, and a portion of the plurality of regions is substantially non-wetting with respect to the dispersed phase, and wherein the pattern includes a plurality of inter-connected regions that are substantially non-wetting with respect to the dispersed phase. A related article is also presented.

Abstract: Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

Abstract: An apparatus for enhancing the coalescence of a dispersed phase from a continuous phase in an emulsion is presented. The apparatus includes at least one inlet for receiving the emulsion, at least one outlet for discharging the emulsion after coalescing the dispersed phase, and at least one article disposed between the inlet and the outlet. The article includes a plurality of regions disposed on a surface in a predefined pattern, wherein a portion of the plurality of regions is substantially wetting with respect to the dispersed phase, and a portion of the plurality of regions is substantially non-wetting with respect to the dispersed phase, and wherein the pattern includes a plurality of inter-connected regions that are substantially non-wetting with respect to the dispersed phase. A related article is also presented.

Abstract: An article includes a substrate with a coating having asperities such that an average spacing between the asperities is between about 0.01 and about 1.5 micron. An average surface roughness of the coating is up to about 2 microns, and an average porosity of the coating is in the range from about 35% to about 70%. A material to reduce surface energy is disposed on the coating. A method for making such an article and a method for decreasing fluid drag across such an article are also provided.