General Electric Company

Ge Aviation Systems Limited

Thoughtspot, Inc.

Oliver Crispin Robotics Limited

Unison Industries, Inc.

Samsung Electronics Co., Ltd.

Alcatel Lucent

Infinera Corporation

Sandvine Corporation

Edgeverve Systems Limited

Ale USA Inc.

Centre for Liquid Crystal Research

Sandeep Kumar

Merin Sebastian

Vamshi Krishna Reddy Kommareddy

Andrew Crispin Graham

Gordon Tajiri

Ravindra Shankar Ganiger

David Raju Yamarthi

Rakesh Kothari

Emily Marie Phelps

Ramana Reddy Kollam

Mandar Diwakar Godbole

Amit Arvind Kurvinkop

Kirti Arvind Petkar

Rajendra Vishwanath Pawar

Bajarang Agrawal

Nagashiresha G

Murugesan Periasamy

Byron Andrew Pritchard, Jr

Dattu Gv Jonnalagadda

Dattu Guru Venkata Jonnalagadda

Tushar Mahale

Naresh Kumar

Siva Singaram

Satya Mohan Vamsi Andalam

Srinidhi Ramanujam

Jasmeet Singh Jaggi

Rahul Paliwal

Pradeep Karanth

Deepak Trivedi

David Mulford Shaddock

Dattu G V Jonnalagadda

Amit Prakash

Manoj Kumar Koyithitta Meethal

Archit Bansal

Karthick Vilapakkam Gourishankar

Vinod Shashikant Chaudhari

Manikanta Balakavi

Grover Andrew Bennett

Vaibhav Agarwal

Shivakumar Basavanna

Rachamadugu Sivaprasad

Edgard Vargas

Sagar Paramashivaiah

Nuthi Srinivas

Greedaran Kubendran Jankin

Guru Venkata Dattu Jonnalagadda

Madhusudan Govindarajan

Rahul Manikanta Balakavi

Sphurti Rajesh Pendke

Sridhar Rajagopal

Jayasankar Madhusoodanan Nair

Dattu GuruVenkata Jonnalagadda

Stephen Paul Leclerc, Jr

Vivek Janu

Soven Kumar Dana

Chander Prakash Singh Dogra

Eric Heistermann

Anil Nagarajan

Arvind Kubendran

Jagjeet S Bhatia

Abhishek Sinha

Zhiquan Sui

Swati Kwatra

Pushpita Dutta

Mayandithevar Manickam

Doddamane Sreenivasamurthy Shankar Rao

Geetha Gopinathan Nair

Subbarao Krishna Prasad

Sivaramakrishna Chandrasekhar

Amrutha Bailuri

Deepinder Dhuria

Guha Ramasubramanian

Vamshi Kommareddy

Dattu Guruvenkata Jonnalagadda

An insertion apparatus for use with a rotary machine includes a body extending from an insertion end to a steering end and sized to fit within an annular cavity. The body has a first stiffness and curves along a circumference of the annular cavity as the insertion end travels through the annular cavity. The insertion apparatus also includes a stiffener coupled to the body and extending from the steering end to the insertion end. The stiffener has a second stiffness greater than the first stiffness. The insertion apparatus further includes at least one maintenance device coupled to the insertion end of the insertion apparatus and a displacement mechanism configured to adjust a position of the at least one maintenance device relative to the body.

Insertion apparatus for use with rotary machines

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 tool stabilization mechanism is disclosed including a stabilizing device connected to a tool and movable between a deployed position and a non-deployed position, and an actuator for actuating the stabilizing device to move between the deployed position and the non-deployed position. In some forms the tool stabilization mechanism is integrated into a borescope unit, while in other forms it may be an accessory attachable to conventional borescope units. Related methods to the above are also disclosed herein.

Tool stabilization mechanism and related methods

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

A method for managing Quality of Experience (QoE) for video streaming traffic flow on a network, the method including: collecting data associated with a plurality of video streaming traffic flows; creating a model based on the collected data; determining factors associated with a new video streaming traffic flow; analyzing the factors based on the model; determining a QoE score based on the analysis. A system for managing QoE for video streaming traffic flow on a network, the system including: a factor determination module configured to collect data associated with a plurality of video streaming traffic flows; a model module configured to create a model based on the collected data; an analysis module configured to determine factors associated with a new video streaming traffic flow and analyze the factors based on the model; and a QoE engine configured to determine a QoE score based on the analysis.

System and method for managing video streaming quality of experience

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 and system may be implemented for automatically analyzing data in a database. A method for use in a low-latency database analysis system may include generating a schema. The schema may be based on a portion of an external database. The method may include storing the schema in an in-memory database. The method may include receiving a data-query. The method may include generating a resolved-request. The resolved-request may be based on the data-query and the stored schema. The stored schema may be used for executing the query on the external database. The method may include receiving results data responsive to the data-query from the external database. The method may include outputting the results data for display on a user interface.

Low-latency database analysis using external data sources

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

The present disclosure relates to a method for determining optimal process flow () for a process performed by users () in a computing system. The method comprises receiving plurality of keystroke level events for each of plurality of process flows associated with the process, performed by plurality of users (). Further, the method comprises determining one or more subtasks () for each of the plurality of process flows (). A subtask comprises a set of events occurring together in the plurality of keystroke level events (). Furthermore, the method comprises grouping one or more process flows from the plurality of process flows () to form one or more clusters (), based on the one or more subtasks (). Each cluster comprises the one or more process flows with similar subtasks. Thereafter, the method comprises determining an optimal process flow () in each cluster.

Method and system for analyzing process flows for a process performed by users

A method for compensating a Power Supply Rejection Ratio (PSRR) in an image sensor, the method includes receiving, by processing circuitry, at least one analog signal from an active pixels sensor (APS) array, the at least one analog signal including power supply noise, combining, by the processing circuitry, amplified power supply noise with at least one ramp signal to obtain combined power supply noise, and compensating, by the processing circuitry, the PSRR of the APS array by cancelling the power supply noise of the at least one analog signal using the combined power supply noise.

Methods and systems for increasing PSRR compensation range in an image sensor

A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.

OGV electroformed heat exchangers

A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.

Tube coupling assembly

Growing community of inventors

Bengaluru, India

Sandeep Kumar