Abstract: An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.

Abstract: A method and/or system for automated estimation of 3D orientation of a physical asset using deep learning models and computer vision algorithms, according to one or more embodiments. The system may be configured to receive images of the physical asset and camera orientation data as input, use deep learning neural network models to isolate the physical assets across the images, track each physical asset instance throughout the images and derive a 3D point cloud model of each asset by projecting binary masks of the asset contours from different view-points. The 3D point cloud model is further processed and supplemented with camera orientation data to estimate the 3D orientation of one or more assets present in the images.

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: An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.

Abstract: Systems and methods for cleaning deposits from a component of an assembled, on-wing gas turbine engine are provided. Accordingly, the method includes operably coupling a delivery assembly to an annular inlet of a core gas turbine engine. A portion of cleaning fluid is atomized with the delivery assembly to develop a cleaning mist having a plurality of atomized droplets. The atomized droplets are suspended within any path of the core gas turbine engine from the annular inlet to an axial position downstream of a compressor of the core gas turbine engine. A portion of the cleaning mist is impacted or precipitated onto the component so as to wet the component, and a portion of the deposits on the component is dissolved by the cleaning mist.

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: Systems and methods for treating a component of an installed and assembled gas turbine engine are provided. Accordingly, the method includes operably coupling a delivery assembly to an annular inlet of a core gas turbine engine. A portion of treating fluid is atomized with the delivery assembly to develop a treating mist having a plurality of atomized droplets. The atomized droplets are suspended within any path of the core gas turbine engine from the annular inlet to an axial position downstream of a compressor of the core gas turbine engine. A portion of the treating mist is impacted or precipitated onto the component so as to wet the component, and a portion of the deposits on the component is dissolved by the treating mist.

Abstract: Systems and methods for cleaning deposits from a component of an assembled, on-wing gas turbine engine are provided. Accordingly, the method includes operably coupling a delivery assembly to an annular inlet of a core gas turbine engine. A portion of cleaning fluid is atomized with the delivery assembly to develop a cleaning mist having a plurality of atomized droplets. The atomized droplets are suspended within any path of the core gas turbine engine from the annular inlet to an axial position downstream of a compressor of the core gas turbine engine. A portion of the cleaning mist is impacted or precipitated onto the component so as to wet the component, and a portion of the deposits on the component is dissolved by the cleaning mist.

Abstract: A vapor-based system and method for treating one or more components of a gas turbine engine. The system includes a treatment compound contained in a storage vessel. The storage vessel being operably coupled to a delivery module. The delivery module delivering the treatment compound at one or more locations of the gas turbine engine such that the treatment compound is a vapor when exposed to an engine air-path.

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: A sprayable thermal barrier coating powder mixture for a gas turbine engine includes: a dry composition having a low surface area ceramic powder having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture.

Abstract: A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Abstract: An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.

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: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

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: A turbine system includes a foam generating assembly having an in situ foam generating device at least partially positioned within the fluid passageway of the turbine engine, such that the in situ foam generating device is configured to generate foam within the fluid passageway of the turbine engine.

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 turbine engine cleaning system includes a foaming nozzle. The foaming nozzle includes a wall having a thickness between an outer surface of the wall and an inner surface of the wall. The outer surface of the wall is configured to contact a detergent in which the foaming nozzle is configured to be disposed. The inner surface of the wall surrounds an inner plenum of the foaming nozzle, and the inner plenum is configured to receive an aerating gas. The foaming nozzle also includes a first row of first through holes fluidly coupled to, and extending between, a first row of first through hole inlets at the inner surface of the wall and a first row of first through hole outlets at the outer surface of the wall.