General Electric Company

Oliver Crispin Robotics Limited

Ambarish Jayant Kulkarni

Bernard Patrick Bewlay

Byron Andrew Pritchard, Jr

Hrishikesh Keshavan

Byron Andrew Pritchard

Nicole Jessica Tibbetts

Mehmet Muhittin Dede

Michael Edward Eriksen

Keith Anthony Lauria

Margeaux Wallace

Andrew Crispin Graham

Larry Steven Rosenzweig

Michael Robert Millhaem

Todd William Danko

Michael Solomon Idelchik

Shankar Sivaramakrishnan

Krzysztof Jacek Lesnicki

Guanghua Wang

Trevor Owen Hawke

Jay Morgan

Michael Dean Fullington

Julian Matthew Foxall

Erica Elizabeth Sampson

William Francis Navojosky

Gongguan Wang

Jose Sanchez

David Scott Diwinsky

Atanu Saha

Mark Alan Rosenzweig

Shyam Sivaramakrishnan

Jeremy Clyde Bailey

Eric Telfeyan

Andrew James Jenkins

Mamatha Nagesh

Stephen Anthony Wilton

Brian Kalb

Martin Matthew Morra

Timothy Mark Sambor

Ronald Scott Bunker

Christopher Edward Wolfe

James Anthony Ruud

Brian Ellis

Robert Proctor

Deepak Trivedi

Matthew David Butts

Biao Fang

Robert David Briggs

Mark Howard Giammattei

Wayne Ray Grady

David Bruce Hall

Gulcharan Singh Brainch

Curtis Walton Stover

Roderick Mark Lusted

Kevin Paul McEvoy

Omprakash Samudrala

Liangde Xie

Paul Russell Wilson

Manuel Kenneth Bueno

Satoshi Atsuchi

Cathleen Ann Hoel

Jonathan Michael Rausch

Ahmed Mostafa ELKady

Vaibhav Bahadur

Luc Stephane Leblanc

David Elson Caldwell

Henry Ng

Geoffrey Mark Eadon

Julie Marie Chapman

David E Caldwell

David Geoffrey Dauenhauer

Noel Bates

Oscar Max Sittner

Terje Glomsaker

Yifan Gao

Almed M Elkady

Michael Robert Millheam

Chiara Mellucci

Stuart James Briggs

Daniel Ellestad

Shantanu M Sane

Meenakshi Kodali

Aaron P Bloomfield

Michael R Mutchler

Patrick James McCluskey

Rob Ray Anthony

Ahmed M Elkady

Brian William Pfeiffer

Matthew Charles Sabo

Michael Alan Meade

Ever Reyes

Shantanu Madhavrao Sane

Manuel K Bueno

Jr Byron Andrew Pritchard

Byron Pritchard Jr

Brian Alan Kalb

Byron Andrew Pritchard Jr

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

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

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 method of repairing a component of a gas turbine engine in situ, wherein the component includes a deposit, includes directing a flow of gas, which may be an oxygen-containing gas, to the deposit of the component; and heating the component including the deposit while the component is installed in the gas turbine engine and for a duration sufficient to substantially remove the deposit.

Component repair system and method

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

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.

Insertion tool and method

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

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 the 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.

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.

Spray nozzle device for delivering a restorative coating through a hole in a case of a turbine engine

Growing community of inventors

Glenville, NY, United States of America

Ambarish Jayant Kulkarni