General Electric Company

Babcock & Wilcox Power Generation Group, Inc.

Vivek Venugopal Badami

Mark Edward Dausch

Walter Whipple

Aninda Bhattacharya

Ajay Kumar Behera

Venkatesh Rajagopalan

Rahul Srinivas Prabhu

Jitendra Kumar

Ertugrul Berkcan

Emilie Thorbjorg Saulnier

Nicolas Wadih Chbat

Piero Patrone Bonissone

Vinay Bhaskar Jammu

Yu-To Chen

Nilesh Tralshawala

Scott Mordin Hoyte

Mahalakshmi Shunmugham Balasubramaniam

David Anthony Schneider

Donald Thomas McGrath

Achalesh Kumar Pandey

Nidhi Naithani

Fernando Javier D'Amato

Chayan Mitra

Gregory Owen Miller

Ayan Banerjee

George Charles Goodman

Prashanth D'Souza

Paul Randall Wilson

Nicholas Giannakopoulos

Venkat Subramaniam Venkataramani

Thomas James Batzinger

Charles Erklin Seeley

Daniel White Sexton

Thomas R Payne

Guanghua Wang

Pierino Gianni Bonanni

David F Johnston

Paul Kenneth Houpt

Robert P Alley

Jacob John Kittleson

Rajesh Venkat Subbu

Kai F Goebel

Avinash Vinayak Taware

Gregory Edward Cooper

Richard E Hornung

James F Bedard

John L Schneiter

Neil Colin Widmer

Terry Lewis Farmer

Ravi Yoganatha Babu

Michael McCall Mahler

Maria Cecilia Mazzaro

Dwight William Jacobus

Sameer Vittal

Sudhanshu Rai

Malcolm John Ashby

Venkatarao Ryali

Mandar Diwakar Godbole

Dean Alexander Baker

Peter John Eisenzopf

Steven Craig Kluge

Harold Edward Miller

Mahesh Raveendranatha Panicker

Donald Richard Dickerson, Jr

Sascha Schieke

Wangming Lu

Bernd Artur Westphal

David Forrest Loy

Nuo Sheng

Yogesh Kesrinath Potdar

Scott Francis Johnson

Jordi Estevadeordal

Roopesh Bhaskaran Nagathil

Roger L Hoffman

Harold John Jenkins, Jr

Paul Joseph Martin

James Baldwin Comly

Seth Alexander Capello

Kenneth H-c Chiang

Thomas Arthur Brownell

Joseph Robert Toth

Arul Saravanapriyan

Barbara D Molnar

Timothy Gerald Lawrence

Abhay Sudhakar Rao Kant

Abhay Sudhakarrao Kant

Adrian Gabriel Loghin

Mark M Dimond

Budhaditya Hazra

Daniel Francesco Driscoll

Mahalakshmi Shunmugam Balasubramaniam

Mahalakshmi Shunumugam Balasubramaniam

Jonas Patrik Richard Gustavsson

Limin Song

Sanghum Baik

Cynthia Fanning Forester

Theodore Henry Klotz, Jr

Abhay S Kant

Peter J Elsenzopf

A system for monitoring health of a rotor is presented. The system includes a processing subsystem that generates a measurement matrix based upon a plurality of resonant-frequency first delta times of arrival vectors corresponding to a blade and a first sensing device, and a plurality of resonant-frequency second delta times of arrival vectors corresponding to the blade and a second sensing device, generates a resonant matrix based upon the measurement matrix such that entries in the resonant matrix are substantially linearly uncorrelated and linearly independent, and generates a resonance signal using a first subset of the entries of the resonant matrix, wherein the resonance signal substantially comprises common observations and components of the plurality of resonant-frequency first delta times of arrival vectors and the plurality of resonant-frequency second delta times of arrival vectors.

Methods and systems to monitor health of rotor blades

A creep life management system includes at least one sensor apparatus coupled to a first component. The at least one sensor apparatus is configured with a unique identifier. The creep life management system also includes at least one reader unit coupled to a second component. The at least one reader unit is configured to transmit an interrogation request signal to the at least one sensor apparatus and receive a measurement response signal transmitted from the at least one sensor apparatus. The creep life management system further includes at least one processor programmed to determine a real-time creep profile of the first component as a function of the measurement response signal transmitted from the at least one sensor apparatus.

Creep life management system for a turbine engine and method of operating the same

Various embodiments include systems and apparatuses adapted for detecting two-dimensional turbomachine exhaust temperature. In some embodiments, a system includes a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine, a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid and at least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid.

Systems and methods for planar temperature measurement

A pyrometry imaging system for monitoring a high-temperature asset which includes at least one component is provided. The system includes a lens element in optical communication with the at least one component. The lens element is configured to receive at least a portion of thermal radiation emitted from the at least one component. The system also includes a view limiting device positioned between the lens element and a dispersive element. The dispersive element is configured to split the at least a portion of thermal radiation emitted into a plurality of wavelengths. The system further includes at least one camera device in optical communication with the dispersive element. The at least one camera device is configured to receive at least one wavelength from the dispersive element.

Hyperspectral imaging system for pyrometry applications and method of operating the same

A system is disclosed. The system includes a processing subsystem that determines preliminary voltages corresponding to a plurality of blades based upon blade passing signals (BPS), and generates a plurality of clearance values by normalizing the preliminary voltages for effects of one or more operational parameters, wherein the plurality of clearance values are representative of clearance of the plurality of blades.

Methods and systems for monitoring health of blades

A method is presented. The method includes the steps of generating rotation signals corresponding to a plurality of rotations of a rotor physically coupled to a plurality of blades, and determining peak voltages corresponding to the plurality of blades by applying time synchronous averaging technique to blade passing signals using the rotation signals, wherein the peak voltages are representative of clearances of the plurality of blades.

System and method for monitoring health of airfoils

Various embodiments of the invention include a system having: at least one computing device connected with an array of ultrasonic probes on a gas turbomachine component, the at least one computing device configured to: instruct a first probe in the array of ultrasonic probes to transmit an ultrasonic beam to at least one additional probe in the array of ultrasonic probes; and determine a property of a medium between the first probe and the at least one additional probe based upon a time between transmission of the ultrasonic beam from the first probe and reception of the ultrasonic beam at the at least one additional probe.

Phased array turbomachine monitoring system

Systems and methods of estimating an efficiency of a section of a steam turbine are disclosed. The systems and methods include determining a set of measurement data obtained directly from a set of sensors on the steam turbine, determining a set of derived data relating to measurements that cannot be obtained directly from the set of sensors, and estimating the efficiency of the section using the set of measurement data and the set of derived data. The systems and methods disclosed use physics-based models combined with nonlinear filtering techniques to estimate steam turbines' efficiencies when physical sensors are not available. These models capture the behavior of different components of the power plant, including all steam turbine sections, admission and crossover pipes, flow junctions, admission and control valves.

Virtual sensor systems and methods for estimation of steam turbine sectional efficiencies

A system for monitoring equipment and transmitting data and/or signals from one or more satellite nodes to a base node for transmission to a monitor or controller for the equipment. The system may transmit high frequency acoustic signals from one or more satellite nodes embedded in the equipment through a structural component of the equipment to the base node, eliminating the need to hardwire the satellite nodes in harsh environments.

Acoustic methods for sensor communication

Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Processing the cracked airfoil finite element model includes accessing the cracked airfoil finite element model, computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis, and computing a vibratory SIF based, at least in part, on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.

Methods and systems for assessing residual life of turbomachine airfoils

In one embodiment, a blade monitoring system includes: at least one computing device configured to monitor a compressor during a load change by performing actions comprising: extracting a dynamic component of a blade time-of-arrival (TOA) deviation signal in response to the load change on the compressor; calculating, using the dynamic component, at least one of: a natural frequency of the GT compressor blade during the load change, an overshoot of the GT compressor blade during the load change, a rise time of the compressor blade during the load change, a damping factor of the compressor blade during the load change, or a settling time of the GT compressor blade after the load change; and determining whether the GT compressor blade is damaged based upon the at least one of: the natural frequency, the overshoot, the rise time, the damping factor, or the settling time.

Blade monitoring system

A method for monitoring the health of one or more blades is presented. The method includes the steps of generating a signal representative of delta times of arrival corresponding to the rotating blade, generating a reconstructed signal by decomposing the signal representative of the delta times of arrival utilizing a multi-resolution analysis technique, wherein the reconstructed signal is representative of at least one of static deflection and dynamic deflection in the rotating blade.

A combustion gas measurement apparatus mounted in a gas turbine including: a tunable laser generating a radiation beam passing through a combustion gas path; a controller tuning the laser to emit radiation having at least a first selected wavelength and a second selected wavelength which both correspond to temperature-dependent transitions of a combustion species of the gas, wherein the first selected wavelength and the second selected wavelength are not near absorption peaks of neighboring wavelengths; a detector sensing the radiation beam passing through the combustion gas and generating an absorption signal indicative of an absorption of the beam by the combustion gas at each of the first wavelength and the second wavelength, and a processor executing a program stored on a non-transitory storage medium determining a combustion gas temperature based on a ratio of the adoption signals for the first wavelength and the second wavelength.

Hot gas temperature measurement in gas turbine using tunable diode laser

A method for monitoring the health of a plurality of blades is presented. The method includes determining delta TOAs corresponding to the plurality of blades, determining a standard deviation utilizing the delta TOAs corresponding to the plurality of blades, determining a delta sigmautilizing the standard deviation and an initial standard deviation, determining a normalized delta TOA corresponding to one or more of the plurality of blades utilizing the delta sigma, determining a standard deviation of the normalized delta TOA, determining a delta sigmautilizing the standard deviation of the normalized delta TOA and a previous standard deviation of normalized delta TOA, and determining a corrected delta TOA corresponding to the one or more of the plurality of blades based upon the delta sigma

A method for monitoring the health of one or more blades is presented. The method includes the steps of determining a delta TOA corresponding to each of the one or more blades based upon respective actual time of arrival (TOA) of the one or more blades, determining a normalized delta TOA corresponding to each of the one or more blades by removing effects of one or more operational data from the delta TOA, and determining a corrected delta TOA corresponding to each of the one or more blades by removing effects of reseating of the one or more blades from the normalized delta TOA.

Growing community of inventors

Schenectady, NY, United States of America

Vivek Venugopal Badami