General Electric Company

Ge Vernova Technology Gmbh

Robert Joseph Iasillo

Michael Joseph Alexander

Steven William Backman

Howard Jay Kaplan

Christopher David Miller

Lewis Berkley Davis, Jr

Kenneth W Beebe

Bruce Gordon Norman

Sanjeev Shyam Heda

Kevin Jon O'Dell

Mark Andrew Cournoyer

Scott Alan Wood

David Martin Johnson

Jason Dean Fuller

Mark Andrew Runkle

Warren James Mick

Kelvin Rafael Estrada

Gregory James Hampson

Robert Scott Traver

Rahul Mohan Joshi

Steven Patrick Junquera

Karen Warren Miller

Stephen Fedor

L Berkly Davis

Jitendra Morankar

Rohan Sharad Pimplikar

Paul David Black

Kevin Andrew Spengler

Daniel D Morrison

David Francis Acquavella

Willy Steve Ziminsky

Christian Lee Vandervort

Kevin Thomas McCarthy

William Forrester Seely

Matthew John McKeever

Minesh Ashok Shah

Jonathan Carl Thatcher

Joseph Vincent Citeno

Charles E Steber

Christopher Eugene Long

Colin Wilkes

Sameer Vittal

Stephen Hugh Black

Ajai Singh

Eric Thomas Pool

William James Lawson

Kotesh Kummamuri Rao

Arthur James Fossum

L Berkley Davis

Troy Joseph Schroeder

Lijie Yu

Christopher Warren Childs

Christopher John Morawski

Praveen Babulal Jain

Mallareddy Soudary

Matthew Francis Lemmon

Steve W Backman

Carlo Angelo Yon

Eric Motter

Tauseef Ahmed Shaikh

Mark Andrew Johnson

KrishnaKumar Pg

Ajith Kizhuthrukovil Radhakrishnan

John E Drazba

Donald Bruce Potter

Nirmal Sahadevan

Danny Lawing

Samuel Ernst-Fortin

Christopher Childs

Eric Steven Norris

David J Van Buren

Urmila Chennuru Reddy

Matthew John Mckeever

Carloa Angelo Yon

Systems and methods for gas turbine combustion profile monitoring are disclosed. In one embodiment, a method for detecting an anomaly in a combustion section of a gas turbine is disclosed. The method includes receiving, from a plurality of thermal sensors disposed around an exhaust section of a gas turbine, exhaust profile data of the gas turbine. The method further analyzes the exhaust profile data to calculate statistical features associated with a peak-trough pattern. The method further determines, using a machine learning algorithm, that the statistical features are abnormal. In response to the determination, the method processes the exhaust profile data for a predetermined period of time and reports an anomaly in a combustion section of the gas turbine if the statistical features remain abnormal for the predetermined period of time.

Gas turbine combustion profile monitoring

A method of monitoring for combustion anomalies in a gas turbomachine includes sensing an exhaust gas temperature at each of a plurality of temperature sensors arranged in an exhaust system of the gas turbomachine, comparing the exhaust gas temperature at each of the plurality of temperature sensors with a mean exhaust gas temperature, determining whether the exhaust gas temperature at one or more of the plurality of temperature sensors deviates from the mean exhaust temperature by a predetermined threshold value, and identifying an instantaneous combustion anomaly at one or more of the temperature sensors sensing a temperature deviating from the mean exhaust temperature by more than the predetermined threshold value.

Method of monitoring for combustion anomalies in a gas turbomachine and a gas turbomachine including a combustion anomaly detection system

A system for remote detection of surge in a fleet of turbine engines includes an on-site monitoring device coupled to each turbine engine of the fleet of turbine engines. The on-site monitoring device is configured to continuously receive operating parameter measurements indicative of operational and thermodynamic conditions of the turbine engine. The operational condition includes a compressor exit condition of the turbine engine compressor. The on-site monitoring device is configured to compile and transmit a snapshot of the operating parameter measurements to a remote monitoring unit. The remote monitoring unit is positioned remote from each turbine engine of the fleet of turbine engines. The remote monitoring unit is configured to receive the snapshot of operating parameter measurements from the on-site monitoring device. The remote monitoring unit is further configured to detect surge in the turbine engine based on analysis of the snapshot of operating parameter measurements.

Method and systems for detection of compressor surge

A power generation plant including a plurality of combustor cans, one or more sensors configured to measure acoustic vibrations from the plurality of combustor cans, and a controller that includes a processor. The processor is programmed to identify a dominant tone of the measured acoustic vibrations, the dominant tone being a frequency where a highest amount of energy lies, determine, for each of the plurality of combustor cans, a frequency of the dominant tone at predefined time intervals, and determine a degradation status of at least one of the plurality of combustor cans based on the frequency of the dominant tone at each of the predefine time intervals for the at least one of the plurality of combustor cans.

System and method for detecting combustion hardware damage

An approach for detecting rotor anomalies is disclosed. An on-site monitoring unit monitors vibration measurements obtained from a rotor during a transient speed operation. In one aspect, the on-site monitoring unit classifies the vibration measurements into predetermined ranges of rotor speed during the transient speed operation, determines maximum vibration data for each of the predetermined ranges of rotor speed during the transient speed operation and compiles the maximum vibration data into a snapshot of the vibration measurements obtained during the transient speed operation. A remote monitoring unit detects a rotor anomaly from the snapshot of vibration measurements generated by the on-site monitoring unit.

Detecting rotor anomalies

Systems and methods for protecting rotating machines are provided. Measurements data collected by a plurality of sensors may be received by a controller that includes one or more computers. The plurality of sensors may be configured to monitor vibrations associated with the rotating machine. Based at least in part upon the measurements data, the controller may determine that a respective amplitude change for at least two of the plurality of sensors exceeds a threshold condition. The controller may also determine that the threshold condition is exceeded for a predetermined period of time. Based at least in part upon determining that the threshold condition is exceeded for a predetermined period of time, the controller may identify an alarm event.

Systems and methods for protecting rotating machines

The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, and wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold.

Primary manifold dual gas turbine fuel system

A system and method for enhancing operation of a power generation system. The method includes receiving forecasts at a predictive control unit. The method also includes accessing via a controller real-time lifing models or near real-time lifing models in the predictive control unit. Additionally, the method includes accessing via the controller an enhancer configured to simulate operation of a power generating unit in the power generation system to generate an enhancement of the power generation system based on the forecasts and the real-time or near real-time lifing models.

System and method for enhancement of power generation facilities

A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Water injection manifold pressure relief vent

A method is provided for performing a transfer from gas fuel operation to liquid fuel operation in a gas turbine with a dual fuel system. The method includes initiating a predetermined uncontrolled liquid fuel prefill flow rate through the liquid fuel system, sensing an onset of the uncontrolled liquid fuel flow to the combustor nozzles, and initiating transfer from gas fuel operation to liquid fuel operation when the flow of uncontrolled liquid fuel at the combustor nozzles is sensed. The onset of uncontrolled liquid fuel flow to the combustor nozzles is determined by monitoring changes of Fuel Normalized Power (FNP), a parameter sensitive to uncontrolled liquid fuel flow, and determining when FNP exceeds a threshold algorithm value.

Method for detecting onset of uncontrolled fuel in a gas turbine combustor

The present application provides a method of operating a dual gas fuel delivery system comprising selecting a manifold and fuel flow split; setting the stroke of a high-energy gas control valve based on the fuel split; measuring the primary manifold nozzle pressure ratio across a primary manifold nozzle outlet; comparing the primary manifold nozzle pressure ratio against a primary manifold specification limit; adjusting the stroke of a primary low energy gas control valve to maintain the pressure ratio across the primary manifold nozzle outlet within the primary manifold specification limit; measuring the secondary manifold nozzle pressure ratio across a secondary manifold nozzle outlet; comparing the secondary manifold nozzle pressure ratio against a secondary manifold specification limit; and adjusting the stroke of a secondary low energy gas control valve to maintain the pressure ratio across the secondary manifold nozzle outlet within the secondary manifold specification limit.

Operation of dual gas turbine fuel system

A method for controlling the rate of transfer between operation with gas and liquid fuel types to minimize the time in undesirable operational mode, thereby preventing excessive wear and damage to gas turbine hardware. The method includes completing a fuel prefill for the oncoming fuel type through the fuel system and determining if a total fuel demand for the oncoming fuel type is greater than a predetermined flow rate for the oncoming fuel type. The method also includes selecting a fuel transfer rate and transferring from the offgoing fuel type to the oncoming fuel type at the selected fuel transfer rate. Further, the method includes determining if the offgoing fuel flowrate has decreased below a predetermined flow rate for the offgoing fuel type, selecting a final fuel transfer rate and completing the transfer from offgoing fuel type to oncoming fuel type at a selected final fuel transfer rate.

Non-linear fuel transfers for gas turbines

A method of operating a gas turbine engine is provided. The method includes introducing a fuel into a combustor, detecting a failure of ignition of the fuel, and preventing ignition until the introduced fuel is substantially removed from the gas turbine engine.

System for detecting ignition failure in a gas turbine engine

Methods and systems for a dry low NOgas turbine engine system include a gas turbine engine including at least one dry low NOcombustor. The combustor includes a plurality of injection points wherein at least some of the injection points are configured to inject a fuel into the combustor at a plurality of different locations. The system includes a water source coupled to the combustor and operable to inject water into others of the plurality of injection points. The system also includes a control system that includes a sensor configured to measure an exhaust gas concentration of the turbine, a processor programmed to receive a signal indicative of the turbine exhaust gas concentration, and to automatically control the water injection using the received exhaust gas concentration signal. Such systems in use together can mitigate visible emissions from the exhaust stack.

Systems for low emission gas turbine energy generation

Growing community of inventors

Atlanta, GA, United States of America

Robert Joseph Iasillo