General Electric Company

Oliver Crispin Robotics Limited

Vamshi Krishna Reddy Kommareddy

Sandeep Kumar

Andrew Crispin Graham

Mandar Diwakar Godbole

Byron Andrew Pritchard, Jr

James Vradenburg Miller

Manoharan Venugopal

Debasish Mishra

Kirti Arvind Petkar

Walter V Dixon

Satya Mohan Vamsi Andalam

Prasad Thapa

Biswajit Medhi

Charles Burton Theurer

Thomas James Batzinger

Michael Francis Xavier Gigliotti

Susanne Madeline Lee

Forrest Frank Hopkins

Edward James Nieters

Ui Won Suh

William Robert Ross

Xiaolei Shirley Ao

Baskaran Ganesan

Manoj Kumar Koyithitta Meethal

Richard Eugene Klaassen

William Stewart McKnight

Paul Burchell Glaser

Edward Randall Furlong

Shivappa Ningappa Goravar

Ramakrishna Rao

Sivaramanivas Ramaswamy

Prafull Sharma

Andrzej Michal May

Rajashekar Venkatachalam

Saratchandra Shanmukh

Aditya Bhakta

Shivakumar Basavanna

Michael Everett Keller

Guru Venkata Dattu Jonnalagadda

Nuthi Srinivas

Paul Joseph Martin

Nityanand Gopalika

Nihat Kurkcu

Suneel Tumkur Shankarappa

John Robert Ward

Vishnu Vardhan Tatiparthi

Ashok Kumaraswamy

Mandayam Tondanur Shyamsunder

Anjani Narendra Schrad

Rajani M Poornima

Raja Vardhan Movva

S V Raj Kumar Bolisetti

Lakshmy Narayanan

Vivek Janu

A pulse illumination imaging system is provided. The system includes an image sensor, a light source, and a controller. The image sensor includes a plurality of light sensitive pixel elements that are activatable for a designated exposure time to capture one or more images. The controller is configured to determine an activation time to activate the image sensor based on motion of a target element relative to the image sensor; activate the image sensor at the activation time; and activate the light source during the exposure time of the image sensor to produce a pulse having a preconfigured time duration that is less than the exposure time of the image sensor.

Pulse illumination imaging of a target element

Systems and methods for engine imaging are provided. An imaging system includes an optical sensor coupled to an insertion tool and a light source configured to output alight projection onto a component of the engine assembly. The system includes a processor configured to: receive data comprising a plurality of frames from the optical sensor captured while the component of the engine assembly is rotating, determine an angular displacement of the component between frames, and form a 3D point cloud of the component based on combining the data in the frames based on the angular displacement of the component between the frames.

3D imaging for engine assembly inspection

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

An apparatus for servicing internal components of an aircraft engine includes a flexible hollow tube; a latching mechanism connected to or incorporated with the flexible hollow tube; and a servicing device to be inserted through the flexible hollow tube. The servicing device is freely moveable through the flexible hollow tube and decoupled from the latching mechanism. The flexible hollow tube is shaped and configured so as to enable proximate positioning of the flexible hollow tube with respect to a rotatable component of an aircraft engine allowing attachment of the flexible hollow tube to the rotatable component via the latching mechanism after the flexible hollow tube is inserted through an entry port of the aircraft engine.

System and method for servicing aircraft engines

An airfoil for a gas turbine engine includes an exterior skin layer having a pressure side surface, a suction side surface, a leading edge, and a trailing edge. The exterior skin layer defines an interior volume. The airfoil further includes a primary structure within the interior volume between the pressure and suction side surfaces. The primary structure includes one or more primary meta-structures. The airfoil further includes a secondary structure within the interior volume adjacent to the primary structure between the pressure and suction side surfaces. The secondary structure includes at least one isogrid structure. Further, one or more of the plurality of primary meta-structures of the primary structure is connected to at least a portion of the at least one isogrid structure of the secondary structure.

Airfoil for a gas turbine engine having an inner core structure formed of meta-structures and isogrids

A method of servicing a portion of a gas turbine engine includes inserting a rigid guide tube into an inspection port in a shroud of the gas turbine engine. The flexible guide tube is inserted into and through the rigid guide tube. The flexible guide tube is pre-shaped such that the flexible guide tube is biased towards a predetermined shape after being inserted through the rigid guide tube. A tool is pushed through the flexible guide tube such that the distal end of the tool moves out of and away from an end of the flexible guide tube. An area of interest of the gas turbine engine is then serviced with the tool.

Multi-tube servicing tool and method of servicing gas turbine engine components

There are provided methods and systems for assessing the health of an asset. For example, a system is provided. The system may include a processor and a memory including instructions that, when executed by the processor, cause the processor to perform operations consistent with identifying a defect in a component of an asset. The operations may include fetching from an inspection system, a plurality of images acquired from an inspection of the component of the asset by the inspection system. The operations may include identifying, based on an image processing technique codified and included as part of the instructions, a subset of images from the plurality of images. The subset of images is representative of the defect in the component of the asset, and the image processing technique is selected from the group consisting of an auto-distress ranking technique, a structural similarity technique, a mean-subtracted filtering technique, and a Hessian norm computation technique.

System and method for assessing the health of an asset

A torsional sensor including a high-pressure sealing mechanism for sensing at least one parameter of a high-pressure fluid. The torsional sensor includes a torsional portion including a torsional rod sensor, a reference portion coupled to the torsional portion and including a transducer device and a high-pressure sealing mechanism coupled to the reference portion and the torsional portion and in sealing arrangement therewith. The high-pressure sealing mechanism is configured to provide for sealing therein the transducer device and allow for protrusion therethrough of a torsional rod sensor. At least a portion of the torsional sensor is mountable for immersion in the high-pressure fluid and operable to propagate a torsional wave that interacts with the high-pressure fluid along the at least portion of the torsional sensor so as to affect propagation of the torsional wave in a manner dependent on the at least one parameter of the high-pressure fluid.

Torsional sensor including a high-pressure sealing mechanism and system for measurement of fluid parameters

A torsional sensor for sensing at least one parameter of a fluid is disclosed. The torsional sensor includes a torsional portion coupled to a reference portion and including a plurality of projections extending outward and spaced apart from each other. At least a portion of the torsional sensor is mountable for immersion in the fluid and operable to propagate a torsional wave that interacts with the fluid along the at least portion of the torsional sensor so as to affect propagation of the torsional wave in a manner dependent on the at least one parameter of the fluid.

Torsional sensor, method thereof, and system for measurement of fluid parameters

An imaging technique is provided for acquiring scatter free images of an object. The technique includes acquiring a plurality of projection images of the object using a source and a detector oriented at a plurality of projection angles relative to the object, and generating a plurality of scatter free projection images by correcting the plurality of projection images based on respective ones of a plurality of stored scatter images. The scatter images are generated and stored for each of the projection angles by positioning a scatter rejection plate between the object and the detector. The technique further includes reconstructing a three-dimensional image of the object based on the scatter free projection images.

Imaging system and method with scatter correction

A system to detect a plurality of elements is proposed. The system includes one or more X-ray sources for transmitting X-rays towards a sample and also includes plurality of photon detectors. An array of crystals are arranged in a curvature with appropriate geometry for receiving a plurality of photon energies emitted from the sample and focusing the photon energy on the plurality of detectors. The plurality of photon detectors are spatially arranged at Bragg angles corresponding to signature photon energies to detect the plurality of elements simultaneously.

Elemental composition detection system and method

A method and system for microstructural evaluation and degradation evaluation of an object are provided. The method comprises insonifying at least one subvolume of the object with ultrasonic energy at a fundamental frequency and acquiring receive energy from the object at the fundamental frequency and at least one harmonic frequency thereof. A nonlinearity parameter is determined using the receive energy. The nonlinearity parameter is then used to determine a grain size for the subvolume of the object and a variation of the grain size within the object. The nonlinearity parameter is also used to determine fatigue damage or a residual stress.

Ultrasonic inspection system and method

A method for generating a scanplan for inspection of a component is provided. The method includes loading a geometric model of the component and generating the scanplan of the component based on the geometric model and at least one scanning parameter. A method of inspecting a component is also provided and includes loading a geometric model of the component, generating a scanplan of the component based on the geometric model and at least one scanning parameter, mounting the component on an inspection system manipulator and inspecting the component including moving an inspection probe relative to the component using the scanplan.

Method for performing model based scanplan generation of a component under inspection

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Bengaluru, India

Vamshi Krishna Reddy Kommareddy