General Electric Company

Oliver Crispin Robotics Limited

Keith Anthony Lauria

Bernard Patrick Bewlay

Nicole Jessica Tibbetts

Ambarish Jayant Kulkarni

Byron Andrew Pritchard, Jr

Michael Edward Eriksen

Erica Elizabeth Sampson

Michael Robert Millhaem

Andrew Crispin Graham

William Francis Navojosky

Gongguan Wang

Robert John Zabala

Laurent Cretegny

Mark Alan Rosenzweig

Mark Kevin Meyer

Eric Telfeyan

Jeffrey Jon Schoonover

Andrew James Jenkins

Qi Zhao

Martin Matthew Morra

William R Catlin

Richard Schliem

Timothy Mark Sambor

Brian Ellis

Byron Andrew Pritchard

Eric Scott Huron

Geoffrey Mark Eadon

David Geoffrey Dauenhauer

Nikole Joy Kucza

Jack E Howson

Vijayaraghava Venkata Nalladega

Shantanu M Sane

Daniel Ellestad

Meenakshi Kodali

Aaron P Bloomfield

Rob Ray Anthony

Michael R Mutchler

Brian William Pfeiffer

Katherine Quinn

Aida Amroussia

Shantanu Madhavrao Sane

Byron Pritchard Jr

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.

Methods of cleaning a component within a turbine engine

A dust injection system for engine testing and related methods are provided. The system includes a carrier pipe that defines a fluid flow path between an inlet and an outlet and an injection nozzle disposed within the carrier pipe between the inlet and the outlet. The injection nozzle receives a slurry comprising dust particulates and a carrier liquid, and injects the dust particulates and the carrier liquid into the fluid flow path. The carrier liquid is atomized and evaporates in the fluid flow path prior to the outlet to enable dried version of the dust particulates to exit the outlet.

Slurry-based dust injection system

Systems and methods for treating a component of an installed and assembled gas turbine engine are provided. Accordingly, the system includes a storage vessel configured for containing a treating fluid. The system further includes a delivery assembly operably coupled to the storage vessel and a control unit. The delivery assembly is configured to atomize a portion of the treating fluid to develop a treating mist of atomized droplets having a median diameter facilitating suspension of the atomized droplets within at least one flow path of the core gas turbine engine. A flow generation assembly of the system is configured to facilitate a passage of the treating mist along the at least one flow path of the core gas turbine engine so as to wet and treat the component.

Systems for treating an installed and assembled gas turbine engine

A machine is cleaned by directing a foam detergent into the machine to remove contaminants from inside the machine. An effluent portion of the foam detergent exits from the machine with some of the contaminants. One or more of a turbidity, a salinity, an amount of total dissolved solids, or a concentration the contaminants in the effluent is measured. A cleaning time period during which the foam detergent is to be directed into the machine is determined based on the turbidity, the salinity, the amount of total dissolved solids, and/or the contaminant concentration that is measured from the effluent. The foam detergent continues to be directed into the machine during the cleaning time period, and the flow of the foam detergent into the machine is terminated on expiration of the time period.

Machine foam cleaning system with integrated sensing

Methods of protecting a metallic substrate from corrosion include introducing an aqueous or powder-form composition including at least one corrosion inhibitor into a crevice that traverses one or more layers covering the metallic substrate to deliver the composition via the crevice into contact with a surface of the metallic substrate. The corrosion inhibitors present in the composition bond to the surface of the metallic substrate, resulting in formation of a film on the surface of the metallic substrate. This film protects the surface of the metallic substrate against corrosion.

Systems and methods of protecting metallic engine components from corrosion

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.

System and method for treating an installed and assembled gas turbine engine

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.

System and method for cleaning deposit from a component of an assembled, on-wing gas turbine engine

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.

Turbine component cleaning system and method having detergent recovery and regeneration

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. The foaming nozzle also includes a second row of second through holes disposed axially adjacent to the first row of second through holes with respect to a longitudinal axis of the inner plenum, where the second row of second through holes is fluidly coupled to, and extending between, a second row of second through hole inlets at the inner surface of the wall and a second row of second through hole outlets at the outer surface of the wall. The foaming nozzle also includes cross-sections of the first through holes and the second through holes having regular shapes.

Foaming nozzle of a cleaning system for turbine engines

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.

Method for cleaning components of a turbine engine

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.

Gas turbine engine wash system

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&#x2014;MgO&#x2014;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.

Methods of cleaning a hot gas flowpath component of a turbine engine

A method for joining a filler material to a substrate material includes melting the filler material within a melting chamber of a crucible such that the filler material is molten. The crucible has an outlet fluidly connected to the melting chamber. The method also includes holding the filler material within the melting chamber of the crucible by applying a first pressure differential across the outlet of the crucible, and releasing the filler material from the melting chamber of the crucible by applying a second pressure differential across the outlet of the crucible to deliver the filler material to a target site of the substrate material. The second pressure differential has a different value than the first pressure differential.

Methods and systems for joining materials

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Wells, NY, United States of America

Keith Anthony Lauria