General Electric Company

Oliver Crispin Robotics Limited

Nicole Jessica Tibbetts

Bernard Patrick Bewlay

Byron Andrew Pritchard, Jr

Ambarish Jayant Kulkarni

Michael Edward Eriksen

Keith Anthony Lauria

Evan Jarrett Dolley

Eric Telfeyan

Andrew James Jenkins

Michael Robert Millhaem

Erica Elizabeth Sampson

Brian Kalb

John Watt

William Francis Navojosky

Denise Anne Anderson

Nathan David McLean

Frank Wagenbaugh

Christopher Perrett

Vincent Gerard Lauria

Gongguan Wang

Andrew Crispin Graham

Brian Ellis

Stephen Francis Rutkowski

Mark Alan Rosenzweig

Sean Robert Keith

Stephen Anthony Wilton

Martin Matthew Morra

Richard Schliem

Timothy Mark Sambor

Alistair Searing

Lawrence Bernard Kool

Peter William Lorraine

David Vincent Bucci

David Martin Mills

Byron Andrew Pritchard

Waseem Ibrahim Faidi

Siavash Yazdanfar

Mohamed Ahmed Ali

Edward James Nieters

David A Mills

Ying Fan

Manuel Kenneth Bueno

David James Monk

Krzysztof Jacek Lesnicki

David Elson Caldwell

David E Caldwell

David Geoffrey Dauenhauer

Shantanu M Sane

Patrick James McCluskey

Brian William Pfeiffer

Matthew Bos

Michael Scheper

Eric Zeltwanger

Ever Reyes

Noel Bates

Rob Ray Anthony

Jr Byron Andrew Pritchard

Manuel K Bueno

Ambarishjayant Kulkarni

Nathan David Mclean

Eric John Telfeyan

Byron Andrew Pritchard Jr

Brain Michael Elllis

Shantanu Madhavrao Sane

Byron Pritchard Jr

Brian Alan Kalb

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.

Methods and system for cleaning gas turbine engine

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

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 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.

In situ foam generation within a turbine engine

A cleaning solution for a turbine engine includes water; a first organic acidic component that comprises citric acid; a second organic acidic component that comprises glycolic acid; isopropylamine sulphonate; alcohol ethoxylate; triethanol amine; and sodium lauriminodipropionate. The cleaning solution has a pH value between about 2.5 and about 7.0.

Cleaning solution and methods of cleaning a 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

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&#xd7;10inches inches) and 5 millimeters (0.2 inches), having a half-life within a range of 5 minutes and 180 minutes, or a combination thereof.

Meta-stable detergent based foam cleaning system and method for gas turbine engines

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.

System and methods for selective cleaning of turbine engine components

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

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&#xd7;10inches) and 5 millimeters (0.2 inches), having a half-life within a range of 5 minutes and 180 minutes, or a combination thereof.

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

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Delanson, NY, United States of America

Nicole Jessica Tibbetts