General Electric Company

Oliver Crispin Robotics Limited

Byron Andrew Pritchard, Jr

Ambarish Jayant Kulkarni

Bernard Patrick Bewlay

Nicole Jessica Tibbetts

Michael Edward Eriksen

Andrew Crispin Graham

Corey Bourassa

Keith Anthony Lauria

David Scott Diwinsky

Michael Robert Millhaem

Mehmet Muhittin Dede

Hrishikesh Keshavan

Robert Carl Murray

Gregory Michael Laskowski

Robert Francis Manning

Victor Hugo Silva Correia

Jonathan Russell Ratzlaff

Jared Peter Buhler

Curtis Walton Stover

Robert Proctor

Erich Alois Krammer

Timothy Deryck Stone

Andrew James Jenkins

Wayne Ray Grady

Margeaux Wallace

Satoshi Atsuchi

Julian Matthew Foxall

Erica Elizabeth Sampson

William Francis Navojosky

Brian Kalb

Gongguan Wang

Curtis Alan Johnson

Stephen Francis Rutkowski

Todd William Danko

Allen Michael Danis

Sandeep Kumar

Mark Alan Rosenzweig

Sean Robert Keith

Giridhar Jothiprasad

Shankar Sivaramakrishnan

Jeremy Clyde Bailey

Vamshi Krishna Reddy Kommareddy

Eric Telfeyan

Richard Wade Stickles

Gary Lee Ward

Evan Jarrett Dolley

Michael Dean Fullington

David Vickery Parker

Trevor Owen Hawke

Mandar Diwakar Godbole

William Collins Vining

Kirti Arvind Petkar

Hongqiang Chen

Martin Matthew Morra

Raymond Gust Holm

Joseph F Savelli

Marc Metz

Timothy Mark Sambor

Alistair Searing

Thomas Ory Moniz

Hendrik Pieter Jacobus De Bock

Brian Ellis

James Thompson

Deepak Trivedi

Craig Alan Gonyou

Atanu Saha

Larry Steven Rosenzweig

Hukam Chand Mongia

James Neil Cooper

John Carl Glessner

Peter John Wood

Steven Alan Ross

Donald Lee Gardner

Mark David Durbin

Willard J Dodds

Liangde Xie

Philip Paul Beauchamp

Stephen Aleshin

Eric John Kress

Rudolf Konrad Selmeier

Shourya Prakash Otta

Christopher Jon Potokar

Chiong Siew Tan

Grover Andrew Bennett

Krzysztof Jacek Lesnicki

Ahmed Mostafa ELKady

Mamatha Nagesh

Jeffrey David Erno

Ajay Keshava Rao

Stephen Anthony Wilton

Eugene F Adiutori

Allan George Van De Wall

Keith K Taylor

Mark M Glevicky

Paul James Ogden

Michael Jerome Foust

David Elson Caldwell

Julie Marie Chapman

David Geoffrey Dauenhauer

Swati Saxena

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

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 engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.

Inducer assembly for a turbine engine

A system and method of using a tool assembly is provided. The system includes a body, a first camera and a second camera fixed to the body, and a controller. The controller is configured to receive data indicative of images of a reference feature from the first camera, determine data indicative of a first spatial position of the first camera based at least in part on the received data indicative of the images of the reference feature, and determine data indicative of a second spatial position of the second camera based on the first spatial position, a known spatial relationship between the first location and the second location, or both. Further, the controller may be configured to receive data indicative of images of a target feature using the second camera, derive dimensions of the target feature based on the images, and generate a three-dimensional representation of the target feature.

System and method of using a tool assembly

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 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 computer implemented method for servicing an engine including receiving information including an initial condition profile, CP1, of the engine; forming a workscope associated with a servicing operation of the engine in view of the initial condition profile, CP1; servicing the engine in view of the workscope; determining at least in part an updated condition profile, CP2, of the engine in view of information acquired during the service; and storing the updated condition profile, CP2, for use in a subsequent service operation.

Systems and methods of servicing equipment

Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.

A robotic assembly configured to service an engine, wherein the robotic assembly includes an environmental capture device configured to provide information associated with an environment in which the engine is disposed to one or more computing devices, and wherein the one or more computing devices are configured to use the information to inspect the engine before and after repair operations associated with the service to check for repair equipment, or parts thereof, left in the engine after the repair.

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

A coated component for a gas turbine engine is provided. The coated component includes a substrate having a surface and a ceramic coating. The ceramic coating includes one or more linear slots and one or more non-linear slots. The one or more non-linear slots intersect the one or more linear slots. The plurality of linear slots and the plurality of non-linear slots form segments of ceramic coating material.

Slotted ceramic coatings for improved CMAS resistance and methods of forming the same

Growing community of inventors

Loveland, OH, United States of America

Byron Andrew Pritchard, Jr