General Electric Company

Oliver Crispin Robotics Limited

Other

Ge Infrastructure Technology, LLC

Bernard Patrick Bewlay

Ambarish Jayant Kulkarni

Melvin Robert Jackson

Nicole Jessica Tibbetts

Byron Andrew Pritchard, Jr

Brian Ellis

Guanghua Wang

Michael James Weimer

James Scott Vartuli

James Anthony Brewer

Ji-Cheng Zhao

Mohamed Rahmane

Michael Francis Xavier Gigliotti

Bruce Alan Knudsen

Pazhayannur Ramanathan Subramanian

Thomas Joseph Kelly

Timothy John Sommerer

Andrew Crispin Graham

Stephen Francis Rutkowski

Ann Melinda Ritter

David Scott Diwinsky

Frederic Joseph Klug

Todd William Danko

John Broddus Deaton, Jr

Robert S Gilmore

Mark Gilbert Benz

Joseph David Rigney

Don Mark Lipkin

Todd Garrett Wetzel

Andrew Lee Trimmer

Stephen Joseph Ferrigno

Michael Francis Xavier Gigliotti, Jr

Ramgopal Darolia

Bin Wei

Lawrence Bernard Kool

Curtis Alan Johnson

Peter William Lorraine

James Alfred Day

Timothy Joseph Trapp

Colin Richard Wilson

David Martin Mills

William Thomas Carter

Kevin George Harding

Thomas James Batzinger

Huan Tan

David Ulrich Furrer

Michael F Henry

Thomas Robert Raber

Reed Roeder Corderman

Walter Vincent Dixon, Iii

Craig Douglas Young

Hrishikesh Keshavan

Byron Andrew Pritchard

Joan McKiever

Mehmet Muhittin Dede

Michael Edward Eriksen

Dennis Joseph Dalpe

Keith Anthony Lauria

Stephen Francis Bancheri

Xiao Bian

Larry Steven Rosenzweig

Eric Telfeyan

Shankar Sivaramakrishnan

Michael Solomon Idelchik

Laurent Cretegny

Luana Emiliana Iorio

Michael Robert Millhaem

Arpit Jain

Brandon Stephen Good

Richard DiDomizio

Alberto Santamaria-Pang

Naveenan Thiagarajan

Shaopeng Liu

John Karigiannis

Waseem Ibrahim Faidi

Siavash Yazdanfar

Atanu Saha

Edward James Nieters

Mohamed Ahmed Ali

Peter G Frischmann

Mark Alan Rosenzweig

Sean Robert Keith

Andrew Joseph Detor

Feng Xue

Clifford Bueno

Ernest Wayne Balch

Paul Leonard Dupree

Wayne Ray Grady

Christopher Allen Nafis

Nirm Velumylum Nirmalan

David A Mills

Judson Sloan Marte

Thomas Charles Adcock

William Paul Minnear

Robert Edward Schafrik

Younkoo Jeong

Robert Arthur Giddings

Agoston Boroczki

Timothy Hanlon

Svetlana Selezneva

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

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.

Inspection and repair tool

Methods, apparatus, systems, and articles of manufacture are disclosed to autonomously detect thermal anomalies. Disclosed examples include an example apparatus to detect engine anomalies comprising: at least one memory; instructions in the apparatus; and processor circuitry to execute the instructions to: control a plurality of infrared cameras to capture a baseline image set, the baseline image set including at least two thermal images; generate emissivity data based on the baseline image set; provide the baseline image set and the emissivity data to an artificial intelligence model, the artificial intelligence model to generate a reconstructed image set; determine a difference between the baseline image set and the reconstructed image set; and in response to the difference exceeding a threshold, generate an alert indicating detection of an engine anomaly.

Methods and apparatus to autonomously detect thermal anomalies

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 reactive phase spray formulation coating is configured to be disposed on the thermal barrier coating of an article. The reactive phase spray formulation coating comprises a base material and a binder material. The base material has a compliance that is higher than a compliance of the binder material, the binder material has a cohesive strength that is greater than a cohesive strength of the base material, the binder material has an adhesive strength that is greater than an adhesive strength of the base material, and the binder material has a surface area of at least ten square-meters per gram that is greater than a surface area of the base material. The binder material is configured to improve a cohesive strength level, an adhesive strength level, and a compliance of the formulation coating of the thermal barrier coating relative to the formulation coating not including the binder material.

Reactive phase spray formulation coatings

Methods for repairing the conventional physical barrier coating barrier on a component having a damaged portion. Applying a coating on the outer surface of the damaged portion of the component. The coating containing a reactive oxide. Initiating a reaction between the coating and the molten sulfates within the outer surface of the component. The reaction catalytically decomposes molten sulfates at the outer surface of the damaged portion of the component.

Anti-corrosion material and application method

A spray nozzle includes a first conduit that provides a first flow path for a first type of fluid, a second conduit that provides a second flow path for a second fluid that is different from the first fluid, a first dispensing aperture that ejects therefrom a spray that includes the first type of fluid and/or the second type of fluid, and at least one balancing outlet in fluid communication with the second conduit. The at least one balancing outlet permit the second type of fluid to exit therefrom to balance a force of ejection of the spray from the first dispensing aperture.

Force-balancing spray nozzle devices

A coating system configured to be applied to a thermal barrier coating of an article includes an infiltration coating configured to be applied to the thermal barrier coating. The infiltration coating infiltrates at least some pores of the thermal barrier coating. The infiltration coating decomposes within at least some pores of the thermal barrier coating to coat a portion of the at least some pores of the thermal barrier coating. The infiltration coating reduces a porosity of the thermal barrier coating. The coating system also includes a reactive phase spray formulation coat configured to be applied to the thermal barrier coating. The reactive phase spray formulation coating reacts with dust deposits on the thermal barrier coating.

Coating systems including infiltration coatings and reactive phase spray formulation coatings

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 niobium-silicide based alloy and a turbine having at least a turbine component formed from the niobium-silicide based alloy are provided. The niobium-silicide based alloy comprises: between about 14 atomic percent and about 24 atomic percent titanium (Ti); between about 11 atomic percent and about 19 atomic percent silicon (Si); between about 4 atomic percent and about 8 atomic percent chromium (Cr); between about 2 atomic percent and about 6 atomic percent hafnium (Hf); up to about 4 atomic percent aluminum (Al); between about 0.5 atomic percent and about 1 atomic percent tin (Sn); between about 5 atomic percent and about 15 atomic percent tantalum (Ta); between about 1 atomic percent and about 5 atomic percent tungsten (W); up to about 5 atomic percent rhenium (Re); up to about 5 atomic percent zirconium (Zr); up to about 6 atomic percent yttrium (Y); and a balance of niobium (Nb).

Niobium-based alloy strengthened by silicide and turbine having turbine component formed from

A servicing tool for a turbine engine and a method for using thereof are provided. A method includes inserting the tool into an access opening of the turbine engine, contacting a blade of the turbine engine, and removing material from the blade. The tool may comprise a wiper mount and a wiper, including a wiper surface, configured to contact and remove material from the blades. The tool may further comprise a body, an actuator, and fluid flowpaths for deploying the wiper and providing fluid locally to the blades of the turbine engine.

Turbine engine servicing tool and method for using thereof

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Niskayuna, NY, United States of America

Bernard Patrick Bewlay