Abstract: System for selectively contacting a cleaning composition with a surface of a turbine engine component is presented. The system includes a cleaning apparatus and a manifold assembly. The cleaning apparatus includes an upper portion and a lower portion defining a cleaning chamber configured to allow selective contact between the cleaning composition and a surface of the first portion of the turbine engine component. The upper portion includes a plurality of fill holes in fluid communication with the cleaning chamber, and the lower portion includes a plurality of drain holes in fluid communication with the cleaning chamber. The manifold assembly is configured to selectively circulate the cleaning composition from a reservoir to the cleaning chamber via the plurality of fill holes, and recirculate the cleaning composition from the cleaning chamber to the reservoir via the plurality of drain holes. Methods for selectively cleaning a turbine engine component is also presented.

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 cleaning solution for a turbine engine includes water within a range between about 68.65 percent and about 99.63 percent by volume of the cleaning solution; a first organic acidic component within a range between about 0.1 percent and about 15 percent by volume of the cleaning solution; wherein the organic acid comprises citric acid; a second organic acidic component within a range between about 0.1 percent and about 15 percent by volume of the cleaning solution; wherein the organic acid comprises glycolic acid; isoropylamine sulphonate within a range between about 0.07 percent and 0.14 percent by volume of the cleaning solution; alcohol ethoxylate within a range between about 0.035 percent and 0.07 percent by volume of the cleaning solution; triethanol amine within a range between about 0.035 percent and 0.07 percent by volume of the cleaning solution; sodium lauriminodipropionate within a range between about 0.03 percent and 1.0 percent by volume of the cleaning solution.

Abstract: A system and method of cleaning a turbine engine are provided. The method may include inserting, directing and evacuating a cleaning agent. Inserting may include inserting the cleaning agent through a predefined access port into a cooling cavity defined by an internal wall of an assembled turbine component, while directing may include directing the cleaning agent against the internal wall to remove a foreign material therefrom. Evacuating may include evacuating the cleaning agent from the cooling cavity.

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: The present disclosure provides methods and systems for in situ cleaning of hot gas flowpath components of a turbine engine that form portions of a hot gas flowpath extending through the turbine. The hot gas flowpath components may include a layer of accumulated contaminants on first portions thereof that form a respective portion of the hot gas flowpath. The first portions may include a thermal battier coating (TBC), and the layer of accumulated contaminants may overlie the TBC and at least partially infiltrate into the TBC. The accumulated contaminants may include CaO—MgO—Al2O3-SiO2 (CMAS) partial melt. The methods may include introducing an acid-including detergent into the hot gas flowpath of the turbine engine and onto the hot gas flowpath components to clean the accumulated contaminants from the first surfaces of the components.

Abstract: A cleaning composition, and method for use of the cleaning composition to clean metal surfaces, such as the surfaces of turbomachinery components, is presented. For example, a method includes contacting a surface of an article with a cleaning composition, wherein the article comprises a metal and wherein the surface includes an oxide; and removing the cleaning composition from the surface. The cleaning composition has a viscosity of at least 104 poise, and comprises a thickening agent and an acidic matrix having selective reactivity with the oxide.

Abstract: The present disclosure provides methods and systems for in situ cleaning of hot gas flowpath components of a turbine engine that form portions of a hot gas flowpath extending through the turbine. The hot gas flowpath components may include a layer of accumulated contaminants on first portions thereof that form a respective portion of the hot gas flowpath. The first portions may include a thermal battier coating (TBC), and the layer of accumulated contaminants may overlie the TBC and at least partially infiltrate into the TBC. The accumulated contaminants may include CaO—MgO—Al2O3-SiO2 (CMAS) partial melt. The methods may include introducing an acid-including detergent into the hot gas flowpath of the turbine engine and onto the hot gas flowpath components to clean the accumulated contaminants from the first surfaces of the components.

Abstract: A method of cleaning a turbine engine includes directing a cleaning solution towards a component of the turbine engine having a layer of foreign material thereon, the cleaning solution including water, a first organic acidic component, a second organic acidic component, isopropylamine sulphonate, alcohol ethoxylate, triethanol amine, and sodium lauriminodipropionate. The cleaning solution has a pH between 2.5 and 7.0.

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 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 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: A system and method of cleaning a turbine engine are provided. The method may include inserting, directing and evacuating a cleaning agent. Inserting may include inserting the cleaning agent through a predefined access port into a cooling cavity defined by an internal wall of an assembled turbine component, while directing may include directing the cleaning agent against the internal wall to remove a foreign material therefrom. Evacuating may include evacuating the cleaning agent from the cooling cavity.

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.